ZH
RU
ES

RM

RM, Total:499 items.

In the international standard classification, RM involves: Lubricants, industrial oils and related products, Milk and milk products, Welding, brazing and soldering, Microbiology, Products of the textile industry, Analytical chemistry, Industrial furnaces, Applications of information technology, Non-ferrous metals, Components for electrical equipment, Materials for aerospace construction, Prepackaged and prepared foods, Magnetic materials, Iron and steel products, Beverages.


AWS - American Welding Society, RM

  • CC-RM-2006 Code Clinic for Study of AWS D1.1/D1.1M:2006 Structural Welding Code-Steel; REFERENCE MANUAL
  • CC-RM -2000 Code Clinic for Study of AWS D1.1 Structural Welding Code-Steel - Reference Manual
  • CC-RM-2002 Code Clinic for Study of AWS D1.1 Structural Welding Code-Steel - Reference Manual

RU-GOST R, RM

International Dairy Federation (IDF), RM

  • IDF/RM 25-2008 Milk and milk products - Determination of nitrogen content and crude protein calculation - Kjeldahl method
  • IDF/RM 225-2009 Milk and milk products - Method for the enumeration of Pseudomonas spp.
  • IDF/RM 228-2009 Dried milk - Enumeration of the specially thermoresistant spores of thermophilic bacteria
  • IDF/RM 216-2009 Milk and milk products - Determination of hen's egg white lysozyme by HPLC
  • IDF/RM 217-2009 Cheese - Determination of nisin A content by LC-MS and LC-MS-MS
  • IDF/RM 51-2013 Processed cheese products - Calculation of content of added phosphate expressed as phosphorus
  • IDF/RM 34-2006 Cheese and processed cheese products - Determination of citric acid content - Enzymatic method
  • IDF/RM 82-2004 Milk and dried milk, buttermilk and buttermilk powder, whey and whey powder - Detection of phosphatase activity
  • IDF/RM 160-2003 Milk and canned evaporated milk - Determination of tin content - Spectrometric method
  • IDF/RM 160-2005 Milk and canned evaporated milk - Determination of tin content - Spectrometric method
  • IDF/RM 210-2006 Milk and milk products - Detection of Enterobacter sakazakii
  • IDF/RM 133-2006 Milk and milk products. Determination of lead content. Graphite furnace atomic absorption spectrometric method
  • IDF/RM 215-2006 Milk and milk products. Determination of antimicrobial residues.Tube diffusion test
  • IDF/RM 208-2011 Milk - Determination of the Lactoperoxidase Activity - Photometric Method (Reference Method)
  • IDF/RM 87-2014 Instant dried milk - Determination of the dispersibility and wettability
  • IDF/RM 150-2012 Fremented milks - Determination of titratable acidity - Potentiometric method
  • IDF/RM 205-2006 Cheese - Determination of rheological properties by uniaxial compression at constant displacement rate

American Welding Society (AWS), RM

  • AWS CC-RM-2006 Code Clinic for Study of AWS D1.1/D1.1M:2006 Structural Welding Code-Steel; REFERENCE MANUAL
  • AWS CC-RM-2002 Code Clinic for Study of AWS D1.1 Structural Welding Code-Steel - Reference Manual Second Printing October 2003

ACI - American Concrete Institute, RM

  • ACI 318RM-1989 Commentary on Building Code Requirements for Reinforced Concrete (Supplement - 1986)
  • ACI 318.1RM-1992 Commentary on Building Code Requirements for Structural Plain Concrete SYNOPSIS ONLY
  • ACI 318M/318RM-1999 Building Code Requirements for Structural Concrete (ACI 318M-99) and Commentary (ACI 318RM-99)
  • ACI 318M/318RM-2002 Building Code Requirements for Structural Concrete (ACI 318M-02) and Commentary (ACI 318RM-02) (First Printing September 2002)
  • ACI 350M/350RM-2001 Code Requirements for Environmental Engineering Concrete Structures (ACI 350M-01) and Commentary (ACI 350RM-01)
  • ACI 318M/318RM-1992 Building Code Requirements for Reinforced Concrete (ACI 318M-89) (Revised 1992) and Commentary (ACI 318RM-89) (Revised 1992)

Group Standards of the People's Republic of China, RM

International Organization for Standardization (ISO), RM

American Society of Mechanical Engineers (ASME), RM

National Aeronautics and Space Administration (NASA), RM

  • NASA NACA-RM-A53A30-1953 Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds
  • NASA NACA-RM-A55A28-1955 Wind-tunnel measurements at subsonic speeds of the static and dynamic-rotary stability derivatives of a triangular-wing airplane model having a triangular vertical tail
  • NASA NACA-RM-A8A20-1948 An investigation of submerged air inlets on a 1/4-scale model of a typical fighter-type airplane
  • NASA NACA-RM-A9A24-1949 A preliminary experimental investigation of a submerged cascade inlet
  • NASA NACA-RM-A51D02-1951 Investigation in the Ames 12-foot pressure wind tunnel of a model horizontal tail of aspect ratio 3 and taper ratio 0.5 having the quarter-chord line swept back 45 degrees
  • NASA NACA-RM-A51D25-1951 Low-speed characteristics of a wing having 63 degrees sweepback and uniform camber
  • NASA NACA-RM-A51D27-1951 Characteristics throughout the subsonic speed range of a plane wing and of a cambered and twisted wing, both having 45 degrees of sweepback
  • NASA NACA-RM-A51G31-1951 The forces and pressure distribution at subsonic speeds on a plane wing having 45 degrees of sweepback, an aspect ratio of 3, and a taper ratio of 0.5
  • NASA NACA-RM-A51H02-1951 Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds - plane triangular wing of aspect ratio 3 with NACA 0003-63 section
  • NASA NACA-RM-A51J11-1951 The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil
  • NASA NACA-RM-A52B20-1952 The effects of Reynolds number at Mach numbers up to 0.94 on the loading on a 35 degree swept-back wing having NACA 65(1)A012 streamwise sections
  • NASA NACA-RM-A52F18-1952 The longitudinal characteristics at Mach numbers up to 0.92 of a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10
  • NASA NACA-RM-A52K13-1953 Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls
  • NASA NACA-RM-A52K14-1953 Experimental investigation of the aerodynamic characteristics of an air-to-air missile employing cruciform wings and tail of rectangular plan form at Mach numbers of 1.4 and 1.9
  • NASA NACA-RM-A52K20-1953 Pressure distribution at Mach numbers up to 0.90 on a cambered and twisted wing having 40 degrees of sweepback and an aspect ratio of 10, including the effects of fences
  • NASA NACA-RM-A52L15-1953 Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail - longitudinal and lateral characteristics
  • NASA NACA-RM-A52L16-1953 Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20
  • NASA NACA-RM-A53B06-1953 An investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type cowling at Mach numbers up to 0.83
  • NASA NACA-RM-A53C19-1953 Experimental investigation of the effects of plan-form taper on the aerodynamic characteristics of symmetrical unswept wings of varying aspect ratio
  • NASA NACA-RM-A53C20-1953 Subsonic static longitudinal stability and control characteristics of a wing-body combination having a pointed wing of aspect ratio 2 with constant-percent-chord trailing-edge elevons
  • NASA NACA-RM-A53H17-1953 Comparison of theoretical and experimental zero-lift drag-rise characteristics of wing-body-tail combinations near the speed of sound
  • NASA NACA-RM-A53I17-1953 A study of the effects of body shape on the vortex wakes of inclined bodies at a Mach number of 2
  • NASA NACA-RM-A53J07-1954 The effects of horizontal-tail height and a partial-span leading-edge extension on the static longitudinal stability of a wing-fuselage-tail combination having a sweptback wing
  • NASA NACA-RM-A53J23-1954 The effects of operating propellers on the longitudinal characteristics at high subsonic speeds of a four-engine tractor airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10
  • NASA NACA-RM-A53L22-1954 An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0.6, 0.9, 1.4, and 1.7
  • NASA NACA-RM-A54B08-1954 The effect of lip shape on a nose-inlet installation at Mach numbers from 0 to 1.5 and a method for optimizing engine-inlet combinations
  • NASA NACA-RM-A54D19-1954 Pressure distributions on triangular and rectangular wings to high angles of attack - Mach numbers 1.45 and 1.97
  • NASA NACA-RM-A54D22-1954 Investigation of the normal force accompanying thrust-axis inclination of the NACA 1.167-(0)(03)-058 and the NACA 1.167-(0)(05)-058 three-blade propellers at forward Mach numbers to 0.90
  • NASA NACA-RM-A54F18-1954 A comparison of the longitudinal aerodynamic characteristics at mach numbers up to 0.94 of sweptback wings having NACA 4-digit or NACA 64A thickness distributions
  • NASA NACA-RM-A54J12-1955 Pressure distributions on triangular and rectangular wings to high angles of attack - Mach numbers 2.46 and 3.36
  • NASA NACA-RM-A54J19-1955 Application of wing-body theory to drag reduction at low supersonic speeds
  • NASA NACA-RM-A54J20-1955 Effect of taper ratio on lift, drag, and pitching-moment characteristics of thin wings of aspect ratio 3 with 53.1 degrees sweepback of leading edge at subsonic and supersonic speeds
  • NASA NACA-RM-A55D11-1955 Investigation of the effects of an airfoil section modification on the aerodynamic characteristics at subsonic and supersonic speeds of a thin swept wing of aspect ratio 3 in combination with a body
  • NASA NACA-RM-A55G19-1955 A study of conical camber for triangular and sweptback wings
  • NASA NACA-RM-A55K09-1956 Force, moment, and pressure-distribution characteristics of rectangular wings at high angles of attack and supersonic speeds
  • NASA NACA-RM-A56I04-1957 The static and dynamic-rotary stability derivatives at subsonic speeds of an airplane model with an unswept wing and a high horizontal tail
  • NASA NACA-RM-A7K03-1948 Low-speed investigation of a small triangular wing of aspect ratio 2.0 I : the effect of combination with a body revolution and height above a ground plane
  • NASA NACA-RM-A8B11-1948 Wind-tunnel investigation of horizontal tails. II - unswept and 35 degrees swept-back plan forms of aspect ratio 4.5
  • NASA NACA-RM-A8F21-1948 An experimental investigation at large scale of several configurations of an NACA submerged air intake
  • NASA NACA-RM-A9B17-1949 Chordwise and spanwise loadings measured at low speed on large triangular wings
  • NASA NACA-RM-A9F16-1949 A comparison of two submerged inlets at subsonic and transonic speeds
  • NASA NACA-RM-A51L03-1952 Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics
  • NASA NACA-RM-A52D22-1952 The forces and pressure distribution at subsonic speeds on a cambered and twisted wing having 45 degrees of sweepback and aspect ratio of 3 and a taper ratio of 0.5
  • NASA NACA-RM-E51A25-1951 Investigation of altitude ignition, acceleration and steady-state operation with single combustor of J47 turbojet engine
  • NASA NACA-RM-L7A30-1947 Wind-tunnel investigation of air loads over a double slotted flap on the NACA 65(216)-215, a = 0.8 airfoil section
  • NASA NACA-RM-L9A07-1949 Low-speed investigation of aileron and spoiler characteristics of a wing having 42 degrees sweepback of the leading edge and circular-arc airfoil sections at Reynolds numbers of approximately 6.0 x 10(exp 6)
  • NASA NACA-RM-L50A04-1950 Longitudinal characteristics of two 47.7 degrees sweptback wings with aspect ratios of 5.1 and 6.0 at Reynolds numbers up to 10 x 10(exp 6)
  • NASA NACA-RM-A6K15-1947 An investigation of the low-speed stability and control characteristics of swept-forward and swept-back wings in the Ames 40- by 80-foot wind tunnel
  • NASA NACA-RM-A7F06-1947 An investigation at low speed of a large-scale triangular wing of aspect ratio two - I. characteristics of a wing having a double-wedge airfoil section with maximum thickness at 20-percent chord
  • NASA NACA-RM-A7H29-1948 High-speed aerodynamic characteristics of horn and overhang balances on a full-scale elevator
  • NASA NACA-RM-A7I30-1948 An experimental investigation of the design variables for NACA submerged duct entrances
  • NASA NACA-RM-A7J22-1948 High-speed aerodynamic characteristics of a model tail plane with modified NACA 65-010 sections and 0 degrees and 45 degrees sweepback
  • NASA NACA-RM-A7K24-1948 Wind-tunnel investigation of horizontal tails. I - unswept and 35 degrees swept-back plan forms of aspect ratio 3
  • NASA NACA-RM-A7K28-1948 High-speed stability and control characteristics of a fighter airplane model with a swept-back wing and tail
  • NASA NACA-RM-A7L02-1948 A summary and analysis of wind-tunnel data on the lift and hinge-moment characteristics of control surfaces up to a Mach number of 0.90
  • NASA NACA-RM-A7L11-1948 Low-speed investigation of a small triangular wing of aspect ratio 2.0 II : flaps on flat-plate models
  • NASA NACA-RM-A7L16-1948 A WIND-TUNNEL INVESTIGATION AT LOW SPEED OF VARIOUS LATERAL CONTROLS ON A 45° SWEPT-BACK WING
  • NASA NACA-RM-A8C03-1948 Low-speed investigation of a small triangular wing of aspect ratio 2.0. III - static stability with twin vertical fins
  • NASA NACA-RM-A8D02-1949 Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees - investigation of a large-scale model at low speed
  • NASA NACA-RM-A8E03-1948 Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. II - the effectiveness and hinge moments of a constant-chord plain flap
  • NASA NACA-RM-A8E21-1948 Tests of a triangular wing of aspect ratio 2 in the Ames 12-foot pressure wind tunnel. III - the effectiveness and hinge moments of a skewed wing-tip flap
  • NASA NACA-RM-A8F15-1948 Investigation of a thin wing of aspect ratio 4 in the Ames 12-foot pressure wind tunnel. II - the effect of constant-chord leading-and trailing-edge flaps on the low-speed characteristics of the wing
  • NASA NACA-RM-A8H30-1948 Wind-tunnel investigation of horizontal tails. III - unswept and 35 degrees swept-back plan forms of aspect ratio 6
  • NASA NACA-RM-A8I29-1948 Ram-recovery characteristics of NACA submerged inlets at high subsonic speeds
  • NASA NACA-RM-A8J21-1948 Wind-tunnel investigation of horizontal tails IV : unswept plan form of aspect ratio 2 and a two-dimensional model
  • NASA NACA-RM-A9C21-1949 Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : effects of split flaps, elevons, and leading-edge devices at low speed
  • NASA NACA-RM-A50C13-1950 Preliminary investigation of the transonic characteristics of an NACA submerged inlet
  • NASA NACA-RM-A50E02-1950 Pressure-distribution and ram-recovery characteristics of NACA submerged inlets at high subsonic speeds
  • NASA NACA-RM-A50K20-1951 Lift, drag, and pitching moment of low-aspect-ratio wings at subsonic and supersonic speeds - plane triangular wing of aspect ratio 2 with NACA 0008-63 section
  • NASA NACA-RM-A51B21-1951 Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : longitudinal characteristics
  • NASA NACA-RM-A51C14-1951 A semi-empirical method for calculating the pitching moment of bodies of revolution at low Mach numbers
  • NASA NACA-RM-L57A30-1957 Experimental determination at subsonic speeds of the oscillatory and static lateral stability derivatives of a series of delta wings with leading-edge sweep from 30 degrees to 86.5 degrees
  • NASA NACA-RM-L56A10-1956 Low-speed longitudinal aerodynamic characteristics of a 45 degrees sweptback wing with double slotted flaps
  • NASA NACA-RM-L51A19-1951 The torsional deflections of several propellers under operating conditions
  • NASA NACA-RM-L52A23-1952 Preliminary investigation at transonic speeds of the effect of balancing tabs on the hinge-moment and other aerodynamic characteristics of a full-span flap on a tapered 45 degrees sweptback wing of aspect ratio 3
  • NASA NACA-RM-53L22-1954 Additional fatigue tests on effects of design details in 355-T6 sand-cast aluminum alloy
  • NASA NACA-RM-E50D05-1950 Experimental investigation of supersonic flow with detached shock waves for Mach numbers between 1.8 and 2.9
  • NASA NACA-RM-E50H23-1950 Correlation of forced-convection heat-transfer data for air flowing in smooth platinum tube with long-approach entrance at high surface and inlet-air temperatures
  • NASA NACA-RM-E51C06-1951 Aerodynamic characteristics of four bodies of revolution showing some effects of afterbody shape and fineness ratio at free-stream Mach numbers from 1.50 to 1.99
  • NASA NACA-RM-E51H13-1951 Aerodynamics of slender bodies at Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 15 x 10(exp 6) I - body of revolution with near-parabolic forebody and cylindrical afterbody
  • NASA NACA-RM-E51L26-1954 Some observations of shock-induced turbulent separation on supersonic diffusers
  • NASA NACA-RM-E53E28-1953 Experimental investigation of the effects of support interference on the pressure distribution of a body of revolution at a Mach number of 3.12 and Reynolds numbers from 2 x 10(exp 6) to 14 x 10(exp 6)
  • NASA NACA-RM-E53H25-1953 Jet effects on flow over afterbodies in supersonic stream
  • NASA NACA-RM-E53J07-1954 Measurement of heat-transfer and friction coefficients for flow of air in noncircular ducts at high surface temperatures
  • NASA NACA-RM-E54F11-1954 Experimental heat-transfer and friction coefficients for air flowing through stacks of parallel flat plates
  • NASA NACA-RM-E54I13-1954 Experimental investigation of drag of afterbodies with exiting jet at high subsonic Mach numbers
  • NASA NACA-RM-E57E06-1957 Jet effects on base pressures of conical afterbodies at Mach 1.91 and 3.12
  • NASA NACA-RM-H56C20-1956 Time-vector determined lateral derivatives of a swept-wing fighter-type airplane with three different vertical tails at Mach numbers between 0.70 and 1.48
  • NASA NACA-RM-H56H03-1957 Dynamic longitudinal stability characteristics of a swept-wing fighter-type airplane at Mach numbers between 0.36 and 1.45
  • NASA NACA-RM-L6L27-1947 Effects of a fuselage and various high-lift and stall-control flaps on aerodynamic characteristics in pitch of an NACA 64-series 40 degrees swept-back wing
  • NASA NACA-RM-L7C11-1947 Aerodynamic characteristics of a 45 degrees swept-back wing with aspect ratio of 3.5 and NACA 2S-50(05)-50(05) airfoil sections
  • NASA NACA-RM-L7D08-1947 Pressure-distribution measurements on a full-scale horizontal tail surface for a Mach number range of 0.20 to 0.70
  • NASA NACA-RM-L7D11-1947 Wind-tunnel investigation of bomb-bay configurations intended to minimize the tumbling of light-weight bombs
  • NASA NACA-RM-L7E13-1947 Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degrees Sweptback Wing at Reynolds Numbers to 8,000,000
  • NASA NACA-RM-L7G09-1947 Investigation of high-lift and stall-control devices on a NACA 64-series 42 degrees sweptback wing with and without fuselage
  • NASA NACA-RM-L7G31-1947 Lateral stability and control characteristics of an airplane model having 42.8 degrees sweptback circular-arc wing with aspect ratio 4.00, taper ratio 0.50, and sweptback tail surfaces
  • NASA NACA-RM-L7I30-1947 Yaw characteristics and sidewash angles of a 42 degrees sweptback circular-arc wing with a fuselage and with leading-edge and split flaps at a Reynolds number of 5,300,000
  • NASA NACA-RM-L7K06-1948 Two-dimensional wind-tunnel investigation at high Reynolds numbers of an NACA 65A006 airfoil with high-lift devices
  • NASA NACA-RM-L7K07-1948 Flight characteristics at low speed of delta-wing models
  • NASA NACA-RM-L8D06-1948 Effect of high-lift devices on the longitudinal and lateral characteristics of a 45 degrees sweptback wing with symmetrical circular-arc sections
  • NASA NACA-RM-L8D29-1948 Wind-tunnel investigation of high-lift and stall-control devices on a 37 degrees sweptback wing of aspect ratio 6 at high Reynolds numbers
  • NASA NACA-RM-L8G05-1948 Full-scale investigation of an equilateral triangular wing having 10-percent-thick biconvex airfoil sections
  • NASA NACA-RM-L9B02-1949 Full-scale investigation of a wing with the leading edge swept back 47.5 degrees and having circular-arc and finite-trailing-edge-thickness ailerons
  • NASA NACA-RM-L9D06-1949 Wing-tunnel investigation at high subsonic speeds of the lateral-control characteristics of an aileron and a stepped spoiler on a wing with leading edge swept back 51.3 degrees
  • NASA NACA-RM-L9E02-1949 The effect of span and deflection of split flaps and leading-edge roughness on the longitudinal stability and gliding characteristics of a 42 degrees sweptback wing equipped with leading-edge flaps
  • NASA NACA-RM-L9E10-1949 Effects of Mach number and sweep on the damping-in-roll characteristics of wings of aspect ratio 4
  • NASA NACA-RM-L9E24-1949 Investigation of low-speed aileron control characteristics at a Reynolds number of 6,800,000 of a wing with leading edge swept back 42 degrees with and without high-lift devices
  • NASA NACA-RM-L9F14-1949 Effect of sweepback on the low-speed static and rolling stability derivatives of thin tapered wings of aspect ratio 4
  • NASA NACA-RM-L9J04-1949 Effect of airfoil section and tip tanks on the aerodynamic characteristics at high subsonic speeds of an unswept wing of aspect ratio 5.16 and taper ratio 0.61
  • NASA NACA-RM-L9K11-1950 Measurements of aerodynamic characteristics of a 35 degrees sweptback NACA 65-009 airfoil model with 1/4-chord bevelled-trailing-edge flap and trim tab by the NACA wing-flow method
  • NASA NACA-RM-L50E26-1950 Damping in roll of rectangular wings of several aspect ratios and NACA 65A-series airfoil sections of several thickness ratios at transonic and supersonic speeds as determined with rocket-powered models
  • NASA NACA-RM-L50F16-1950 Low-speed aerodynamic characteristics of a series of swept wings having NACA 65A006 airfoil sections
  • NASA NACA-RM-L55I20-1955 Effect of large negative dihedral of the horizontal tail on longitudinal and lateral stability characteristics of a swept-wing configuration at transonic speeds
  • NASA NACA-RM-L55J06-1956 Low-Speed Static Stability Characteristics of a Complete Model with an M-Wing in Mid and High Positions and with Three Horizontal-Tail Heights
  • NASA NACA-RM-L55J25-1956 Wind-tunnel investigation at high subsonic speeds of some effects of fuselage cross-section shape and wing height on the static longitudinal and lateral stability characteristics of a model having a 45 degrees swept wing
  • NASA NACA-RM-L55K11-1956 Experimental investigation at high subsonic speed of the rolling stability derivatives of a complete model having a clipped-delta wing and a high horizontal tail
  • NASA NACA-RM-L56C21-1956 Jet effects on base and afterbody pressures of a cylindrical afterbody at transonic speeds
  • NASA NACA-RM-L56G02-1956 Effect of a fuselage on the low-speed longitudinal aerodynamic characteristics of a 45 degrees sweptback wing with double slotted flaps
  • NASA NACA-RM-L56G12-1956 Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies
  • NASA NACA-RM-L56H06-1956 Longitudinal and lateral stability characteristics of a low-aspect-ratio unswept-wing airplane model at Mach numbers of 1.82 and 2.01
  • NASA NACA-RM-L56J04-1957 Effectiveness at transonic speeds of flap-type ailerons for several spanwise locations on a 4-percent-thick sweptback-wing-fuselage model with and without tails
  • NASA NACA-RM-L56K22-1957 Drag of conical and circular-arc boattail afterbodies at Mach numbers from 0.6 to 1.3
  • NASA NACA-RM-L57B07-1957 A transonic investigation of the mass-flow and pressure recovery characteristics of several types of auxiliary air inlets
  • NASA NACA-RM-L57B21-1957 Jet effects on the drag of conical afterbodies for Mach numbers of 0.6 to 1.28
  • NASA NACA-RM-L57C08-1957 An experimental study at high subsonic speeds of several tail configurations on a model having a 45 degrees sweptback wing
  • NASA NACA-RM-L57C20-1957 Results of an investigation at high subsonic speeds to determine lateral-control and hinge-moment characteristics of a spoiler-slot-deflector configuration on a 35 degrees sweptback wing
  • NASA NACA-RM-L57E02-1957 Experimental and theoretical aerodynamic characteristics of two low-aspect-ratio delta wings at angles of attack to 50 degrees at a Mach number of 4.07
  • NASA NACA-RM-L57F07-1957 Effect of frequency of sideslipping motion on the lateral stability derivatives of a typical delta-wing airplane
  • NASA NACA-RM-L57H13-1957 BUFFET TESTS OF AN ATTACK-AIRPLANE MODEL WITH EMPHASIS ON ANALYSIS OF DATA FROM WIND-TUNNEL TESTS
  • NASA NACA-RM-L58B05-1958 Low-subsonic investigation to determine the chordwise pressure distribution and effectiveness of spoilers on a thin, low-aspect-ratio, unswept, untapered, semispan wing and on the wing with leading and trailing-edge flaps
  • NASA NACA-RM-L58C11-1958 Wind-tunnel investigation at a Mach number of 2.01 of forebody strakes for improving directional stability of supersonic aircraft
  • NASA NACA-RM-L58C18-1958 Effects of vertical location of the wing and horizontal tail on the static lateral and directional stability of a trapezoidal-wing airplane model at Mach numbers of 1.41 and 2.01
  • NASA NACA-RM-L8D30-1948 Effect of leading-edge high-lift devices and split flaps on the maximum-lift and lateral characteristics of a rectangular wing of aspect ratio 3.4 with circular-arc airfoil sections at Reynolds numbers from 2.9 x 10(exp 6) to 8.4 x 10(exp 6)
  • NASA NACA-RM-L8I03-1948 The effects of high-lift devices on the low-speed stability characteristics of a tapered 37.5 degree sweptback wing of aspect ratio 3 in straight and rolling flow
  • NASA NACA-RM-L8K19-1949 Wind-tunnel investigation at low speeds of various plug-aileron and lift-flap configurations on a 42 degrees sweptback semispan wing
  • NASA NACA-RM-L8K22-1949 Two-dimensional wind-tunnel investigation of two NACA 6-series airfoils with leading-edge slats
  • NASA NACA-RM-L8L29-1949 Low-speed static-stability and rolling characteristics of low-aspect-ratio wings of triangular and modified triangular plan forms
  • NASA NACA-RM-L55L19-1956 Transonic wind-tunnel measurements of static lateral and directional stability and vertical-tail loads for a model with a 45 degrees sweptback wing
  • NASA NACA-RM-L55L21-1956 A free-flight investigation of the effects of a sonic jet on the total-drag and base-pressure coefficients of a boattail body of revolution from Mach number 0.83 to 1.70
  • NASA NACA-RM-L56D03-1956 Low-speed wind-tunnel results for a thin aspect-ratio-1.85 pointed-wing-fuselage model with double slotted flaps
  • NASA NACA-RM-L56D05-1956 Static lateral stability and control characteristics of a model of a 45 degrees swept-wing fighter airplane with various vertical tails at Mach numbers of 1.41, 1.61, and 2.01
  • NASA NACA-RM-L56E29-1956 Investigation at high subsonic speeds of the static lateral and directional stability and tail-loads characteristics of a model having a highly tapered swept wing of aspect ratio 3 and two horizontal-tail positions
  • NASA NACA-RM-L56F18-1956 Low-speed investigation of the lateral-control characteristics of a flap-type spoiler and a spoiler-slot deflector on a 30 degrees sweptback wing-fuselage model having an aspect ratio of 3, a taper ratio of 0.5, and NACA 65A004 airfoil section
  • NASA NACA-RM-L50H29-1950 Positioning investigation of single slotted flaps on a 47.7 degrees sweptback wing at Reynolds numbers of 4.0 x 10(exp 6) and 6.0 x 10(exp 6)
  • NASA NACA-RM-L50K06-1951 Horizontal-tail effectiveness and downwash surveys for two 47.7 degrees sweptback wing-fuselage combinations with aspect ratios of 5.1 and 6.0 at a Reynolds number of 6.0 x 10(exp 6)
  • NASA NACA-RM-L50L29-1951 Summary of spin and recovery characteristics of 12 models of flying wing and unconventional type airplanes
  • NASA NACA-RM-L51B13-1951 The effect of end plates, end struts, and depth of submergence on the characteristics of a hydrofoil
  • NASA NACA-RM-L51F22-1951 Investigation of low-speed lateral control and hinge-moment characteristics of a 20-percent-chord plain aileron on a 47.7 degrees sweptback wing of aspect ratio 5.1 at a Reynolds number of 6.0 x 10(exp 6)
  • NASA NACA-RM-L51J04-1952 Low-speed longitudinal characteristics of a 45 degrees sweptback wing of aspect ratio 8 with high-lift and stall-control devices at Reynolds numbers from 1,500,000 to 4,800,000
  • NASA NACA-RM-L51K26-1952 Force and pressure investigation at large scale of a 49 degrees sweptback semispan wing having NACA 65A006 sections and equipped with various slat arrangements
  • NASA NACA-RM-L52E02-1952 Longitudinal frequency-response and stability characteristics of the Douglas D-558-II airplane as determined from transient response to a Mach number of 0.96
  • NASA NACA-RM-L52G07-1952 Wind-tunnel investigation of the low-speed static and rotary stability derivatives of a 0.13-scale model of the Douglas D-558-II airplane in the landing configuration
  • NASA NACA-RM-L52G18-1952 Investigation of the effects of variations in the Reynolds number between 0.4 x 10(exp 6) and 3.0 x 10(exp 6) on the low-speed aerodynamic characteristics of three low-aspect-ratio symmetrical wings with rectangular plan forms
  • NASA NACA-RM-L52K06-1952 Pressure distribution and pressure drag for a hemispherical nose at Mach numbers 2.05, 2.54, and 3.04
  • NASA NACA-RM-L52K20-1952 Summary of pitch-damping derivatives of complete airplane and missile configurations as measured in flight at transonic and supersonic speeds
  • NASA NACA-RM-L52L05-1952 Wind-tunnel investigation of stall control by suction through a porous leading edge on a 37 degrees sweptback wing of aspect ratio 6 at Reynolds numbers from 2.50 x 10(exp 6) to 8.10 x 10(exp 6)
  • NASA NACA-RM-L53B26-1953 Low-speed aileron effectiveness as determined by force tests and visual-flow observations on a 52 degrees sweptback wing with and without chord-extensions
  • NASA NACA-RM-L53F24-1953 Effect of reduction in thickness from 6 to 2 percent and removal of the pointed tips on the subsonic static longitudinal stability characteristics of a 60 degrees triangular wing in combination with a fuselage
  • NASA NACA-RM-L53H21-1953 Investigation of Reynolds number effects for a series of cone-cylinder bodies at Mach numbers of 1.62, 1.93, and 2.41
  • NASA NACA-RM-L53J21-1953 Wind-tunnel investigation at transonic speeds of a spoiler-slot-deflector combination on an unswept NACA 65A006 wing
  • NASA NACA-RM-L54C16-1954 Experimental effects of propulsive jets and afterbody configurations on the zero-lift drag of bodies of revolution at a Mach number of 1.59
  • NASA NACA-RM-L54I13-1954 Comparison of low-speed rotor and cascade performance for medium-camber NACA 65-(C(sub lo)A(sub 10) 10 compressor-blade sections over a wide range of rotor blade-setting angles at solidities. of 1.0 and 0.5
  • NASA NACA-RM-L55D08-1955 Exploratory investigation at Mach number 4.06 of an airplane configuration having a wing of trapezoidal plan form effects of various tail arrangements on wing-on and wing-off static longitudinal and lateral stability characteristics
  • NASA NACA-RM-L55F21-1955 Wind-tunnel investigation at low speed of sideslipping, rolling, yawing, and pitching characteristics for a model of a 45 degrees swept-wing fighter-type airplane
  • NASA NACA-RM-L8E24-1948 Aerodynamic characteristics of a two-blade NACA 10-(3)(08)-03R propeller
  • NASA NACA-RM-E52H15-1952 Pressure limits of flame propagation of pure hydrocarbon-air mixtures at reduced pressure
  • NASA NACA-RM-L50L04-1951 Effects of several arrangements of rectangular vortex generators on the static-pressure rise through a short 2:1 diffuser
  • NASA NACA-RM-L51E02-1951 Flight determination of drag and pressure recovery of a nose inlet of parabolic profile at Mach numbers from 0.8 to 1.7
  • NASA NACA-RM-L51G09-1951 Preliminary investigation of the effects of rectangular vortex generators on the performance of a short 1.9:1 straight-wall annular diffuser
  • NASA NACA-RM-L51H13-1951 Low-speed characteristics of a 45 degree sweptback wing of aspect ratio 8 from pressure distributions and force tests at Reynolds numbers from 1,500,000 to 4,800,000
  • NASA NACA-RM-L52B13-1952 Effects of some primary variables of rectangular vortex generators on the static-pressure rise through a short diffuser
  • NASA NACA-RM-L54G21-1954 Effects of diffuser and center-body length on performance of annular diffusers with constant-diameter outer walls and with vortex-generator flow controls
  • NASA NACA-RM-L54K18-1955 Investigation of two short annular diffuser configurations utilizing section and injection as a means of boundary-layer control
  • NASA NACA-RM-A51H20 REV A-1951 Comparison of drag, pressure recovery, and surface pressure of a scoop-type inlet and an NACA submerged inlet at transonic speeds
  • NASA NACA-RM-A54H26 REV A-1954 The application of a simplified lifting-surface theory to the prediction of the rolling effectiveness of plain spoiler ailerons at subsonic speeds
  • NASA NACA-RM-A54H27 REV A-1954 Longitudinal aerodynamic characteristics to large angles of attack of a cruciform missile configuration at a Mach number of 2
  • NASA NACA-RM-A50J09 REV A-1950 Preliminary flight investigation of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane
  • NASA NACA-RM-A50K28 REV A-1951 The effects of increasing the leading-edge radius and adding forward camber on the aerodynamic characteristics of a wing with 35 degrees of sweepback

GB-REG, RM

  • REG NACA-RM-A51A16-1951 Low-speed investigation of a 0.16 scale model of the X-3 airplane : lateral and directional characteristics
  • REG NACA-RM-A55J28-1956 Application of Tchebichef form of harmonic analysis to the calculation of zero-lift wave drag of wing-body-tail combinations
  • REG NACA-RM-A9L01-1950 Wing-tunnel investigation at Mach numbers from 0.50 to 1.29 of an all-movable triangular wing of aspect ratio 4 alone and with a body
  • REG NACA-RM-A9D05-1949 Wind-tunnel investigation of horizontal tails V : 45 degree swept-back plan form of aspect ratio 2
  • REG NACA-RM-A8D20-1948 Aerodynamic study of a wing-fuselage combination employing a wing swept back 63 degrees : subsonic Mach and Reynolds number effects on the characteristics of the wing and on the effectiveness of an elevon
  • REG NACA-RM-A50J26-1950 Experimental damping in pitch of 45 degree triangular wings
  • REG NACA-RM-L9F10-1949 Preliminary aerodynamic investigation of the effect of camber on a 60 degrees delta wing with round and beveled leading edges
  • REG NACA-RM-L8K12-1949 Lateral-control investigation on a 37 degrees sweptback wing of aspect ratio 6 at a Reynolds number of 6,800,000
  • REG NACA-RM-L8F29-1948 An investigation at low speed of a 51.3 degrees sweptback semispan wing with a raked tip and with 16.7-percent-chord ailerons having three spans and three trailing-edge angles
  • REG NACA-RM-L8H20-1948 An investigation at low speed of a 51.3 degree sweptback semispan wing equipped with 16.7-percent-chord plain flaps and ailerons having various spans and three trailing-edge angles
  • REG NACA-RM-L8H10-1948 Effect of airfoil profile of symmetrical sections on the low-speed static-stability and yawing derivatives of 45 degrees sweptback wing models of aspect ratio 2.61
  • REG NACA-RM-L55L14-1956 Preliminary measurements of the aerodynamic yawing derivatives of a triangular, a swept, and an unswept wing performing pure yawing oscillations, with a description of the instrumentation employed

PH-BPS, RM

European Committee for Standardization (CEN), RM

  • prEN 2313-1981 Steel FE-PM42, R<(Index)m> 1350 MPa; bars D<(Index)e> 100 mm; aerospace series
  • prEN 2206-1981 Steel FE-PL43 S, 650 MPa R<(Index)m> 850 MPa; bars D<(Index)e> 150 mm; aerospace series
  • prEN 2274-1979 Aerospace series; steel FE-PA 95; 1750 MPa <(kursiv)R><(Index)m> 2000 MPa; bars <(kursiv)D><(Index)e> 150 mm
  • prEN 2278-1981 Steel FE-PM37, 900 MPa R<(Index)m> 1100 MPa; bars D<(Index)e> 150 mm; aerospace series
  • prEN 2136-1981 Aerospace series; steel FE-PM 42; 900 MPa R<(Index)m> 1100 MPa; bars D<(Index)e> 100 mm
  • prEN 2171-1981 Heat resisting steel FE-PA92-HT, R<(Index)m> 900 MPa; bars; aerospace series
  • prEN 2213-1981 Steel FE-PL52 S, 980 MPa R<(Index)m> 1180 MPa; bars D<(Index)e> 16 mm; aerospace series
  • prEN 2214-1981 Steel FE-PL52 S, 1080 MPa R<(Index)m> 1250 MPa; bars D<(Index)e> 100 mm; aerospace series
  • prEN 2228-1977 Aerospace series; steel FE-PA 12; 500 MPa <(kursiv)R><(Index)m> 700 MPa; sheets 0,5 mm <(kursiv)a> 6 mm
  • prEN 2280-1981 Steel FE-PM37, 900 MPa R<(Index)m> 1100 MPa; sheet a 6 mm; aerospace series
  • prEN 2205-1981 Steel FE-PL43 S, 900 MPa R<(Index)m> 1100 MPa; bars D<(Index)e> 40 mm; aerospace series
  • prEN 2216-1981 Steel FE-PL52 S, 1050 MPa R<(Index)m> 1250 MPa; sheets a 2 mm; aerospace series
  • prEN 2215-1981 Steel FE-PL52 S, 980 MPa R<(Index)m> 1180 MPa; sheets 0,5 mm a 6 mm; aerospace series
  • prEN 2231-1981 Steel FE-PA12, R<(Index)m> 850 MPa; tubes for structures 1,25 mm a 5 mm; aerospace series
  • prEN 2232-1981 Steel FE-PA12, R<(Index)m> 1050 MPa; tubes for structures 1,25 mm a 5 mm; aerospace series
  • prEN 2273-1981 Steel FE-PM13 S, 1800 MPa R<(Index)m> 2000 MPa; sheet and plate a 30 mm; aerospace series
  • prEN 2276-1981 Steel FE-PA95, 1750 MPa R<(Index)m> 2000 MPa; sheet and plate a 40 mm; aerospace series
  • EN 2280:2018 Aerospace series - Steel FE-PM37 - 900 MPa ��Rm ��1 100 MPa - Sheet - a ��6 mm
  • EN 2206:2008 Aerospace series - Steel FE-PL1502 (25CrMo4) - 650 MPa less than or equal to Rm less than or equal to 850 MPa - Bars - De less than or equal to 150 mm
  • EN 2478:2008 Aerospace series - Steel FE-PL2107 (30NiCrMo16) - 1220 MPa <= Rm <= 1370 MPa - Bars - De <= 40 mm
  • EN 2480:2008 Aerospace series - Steel FE-PL2108 (36NiCrMo16) - 1250 MPa <= Rm <= 1400 MPa - Bars - De <= 75 mm
  • EN 2438:2008 Aerospace series - Steel FE-PL2102 (35NiCr6) - 900 MPa less than or equal to Rm less than or equal to 1 100 MPa - Bars - De less than or equal to 40 mm
  • EN 2446:2008 Aerospace series - Steel FE-PL1503 (35CrMo4) - 1 100 MPa less than or equal to Rm less than or equal to 1 300 MPa - Bars - De less than or equal to 25 mm
  • prEN 2212-1981 Steel FE-PL43 S, 670 MPa R<(Index)m> 870 MPa; sheets, strips and plates 0,5 mm a 20 mm; aerospace series
  • prEN 2218-1981 Steel FE-PL52 S, 980 MPa R<(Index)m> 1180 MPa; tubes for structures a 4 mm d 5 a; aerospace series
  • prEN 2219-1981 Steel FE-PL52 S, 1030 MPa R<(Index)m> 1230 MPa; tubes for structures a 2 mm d 5 a; aerospace series
  • prEN 2229-1981 Steel FE-PA12, 500 MPa R<(Index)m> 700 MPa; tubes for structures 0,5 mm a 5 mm; aerospace series
  • prEN 2230-1981 Steel FE-PA12, 730 MPa R<(Index)m> 960 MPa; tubes for structures 0,5 mm a 3 mm; aerospace series
  • EN 2205:2009 Aerospace series - Steel FE-PL1502 (25CrMo4) - 900 MPa less than or equal to Rm less than or equal to 1 100 MPa - Bars - De less than or equal to 40 mm
  • EN 2448:2008 Aerospace series - Steel FE-PL1503 (35CrMo4) - 900 MPa less than or equal to Rm less than or equal to 1 100 MPa - Bars - De less than or equal to 40 mm
  • EN 2460:2009 Aerospace series - Steel FE-PM1901 (X12CrNi13) - 600 MPa less than or equal to Rm less than or equal to 800 MPa - Bars - De less than or equal to 70 mm
  • prEN 2209-1981 Steel FE-PL43 S, 900 MPa R<(Index)m> 1100 MPa; sheets, strips and plates 0,5 mm a 20 mm; aerospace series
  • prEN 2251-1981 Steel FE-PL52 S, R<(Index)m> 700 MPa; tubes for structures 0,8 mm a 12,5 mm d 5 a; aerospace series
  • EN 2278:2014 Aerospace series - Steel X12CrNiMoV12-3 (1.4933) - 900 MPa <= Rm <= 1100 MPa - Bars - De <= 150 mm
  • prEN 4904-2021 Aerospace series - Steel 36NiCrMo16 - 1000 MPa ≤ Rm ≤ 1200 MPa - Bars - 100 mm ≤ D ≤ 250 mm
  • EN 2465:2007 Aerospace series - Steel FE-PA3901 (X2CrNi18-9) - Softened - 450 MPa Less than or equal to Rm Less than or equal to 680 MPa - Bar for machining - 4 mm Less than or equal to De Less than or equal to 100 mm
  • EN 2461:2009 Aerospace series - Steel FE-PM1901 (X12CrNi13) - 600 MPa less than or equal to Rm less than or equal to 800 MPa - Forgings - De less than or equal to 70 mm
  • prEN 2217-1981 Steel FE-PL52 S, 1080 MPa R<(Index)m> 1250 MPa; sheets and plates 2 mm a 20 mm; aereospace series
  • prEN 2247-1981 Steel FE-PL43 S, 650 MPa R<(Index)m> 850 MPa; tubes for structures 0,5 mm a 12 mm d 5 a; aerospace series

Professional Standard - Machinery, RM

Association Francaise de Normalisation, RM

AENOR, RM

KR-KS, RM

YU-JUS, RM

  • JUS N.R8.052-1981 Magnetic materiah and components. RM-cores. General requirements.
  • JUS N.R8.052-1979 Magnetic materiak and components. RM-cores. General requirements.
  • JUS N.R8.054-1979 Magnetic materktkand components. RM-cores. Shape and dimemions for coilformers.
  • JUS N.R8.053-1979 Magnetic materiah and components. RM-cores. Shape anddimensions of square cores.

ASD-STAN - Aerospace and Defence Industries Association of Europe - Standardization, RM

  • PREN 3312-1988 Titanium Alloy TI-P63 Annealed 900 Less Than or Equal to Rm Less Than or Equal to 1160 MPa Forgings De Less Than or Equal to 150 mm
  • PREN 2762-2010 Aerospace series Steel FE-PL80 1900 ≤ Rm ≤ 2100 MPa Bar De ≤ 75 mm (Edition P2)
  • PREN 2769-1988 Aerospace Series Steel FE-PL53S Hardened and Tempered 1030 Less Than or Equal to Rm Less Than or Equal to 1180 MPa Forgings De Less Than or Equal to 70 mm (Issue P 1)
  • PREN 2507-2010 Aerospace series Steel FE-PM66 1270 ≤ Rm ≤ 1470 MPa Forgings De ≤ 100 mm (Edition 2)
  • PREN 2172-2010 Aerospace series Heat resisting steel FE-PA92-HT Rm ≥ 900 MPa Forgings (Edition P2)
  • PREN 2506-2010 Aerospace series Steel FE-PM66 1270 ≤ Rm ≤ 1470 MPa Bars De ≤ 100 mm (Edition 2)
  • PREN 2303-1980 Heat Resisting Steel FE-PA92-HT Rm Greater Than or Equal to 960 MPa Bars Aerospace Series (Edition 1)
  • PREN 2303-1999 Heat Resisting Steel FE-PA92-HT Rm Greater Than or Equal to 960 MPa Bars Aerospace Series (Edition 2)
  • PREN 2171-1979 Heat Resisting Steel FE-PA92-HT Rm Greater Than or Equal to 900 MPa Bars Aerospace Series (Edition 1)
  • PREN 3320-1988 Titanium Alloy TI-P64 Annealed Rm Greater Than or Equal to 1000 MPa Forgings De Less Than or Equal to 150 mm
  • PREN 2771-2010 Aerospace series Steel FE-PL53S Hardened and tempered 1100 ≤ Rm ≤ 1250 MPa Bar De ≤ 110 mm (Edition P2)

RO-ASRO, RM

  • STAS 10918-1977 Fcromagnetic oxide materials.FERRITE SQUARE CORES (RM) Dimensions
  • STAS 7836/2-1977 Cold formed steel sections EQUAL-ANGLES STEEL WITH Rm OVER 490 N/mm2 Dimensions

PL-PKN, RM

ES-UNE, RM

  • UNE-EN 4685:2011 Aerospace series - Titanium Ti10V2Fe3Al - Bars - D < 110 mm - Rm >= 1 240 MPa (Endorsed by AENOR in August of 2011.)
  • UNE-EN 2279:2018 Aerospace series - Steel FE-PM37 - 900 MPa <= Rm <= 1 100 MPa - Forgings - De <= 150 mm (Endorsed by Asociación Española de Normalización in September of 2018.)
  • UNE-EN 2280:2018 Aerospace series - Steel FE-PM37 - 900 MPa = Rm = 1 100 MPa - Sheet - a = 6 mm
  • UNE-EN 2450:2018 Aerospace series - Steel 31Ni10 - 1 230 MPa = Rm = 1 420 MPa - Bars - De = 40 mm
  • UNE-EN 2451:2019 Aerospace series - Steel 31Ni10 - 1 230 MPa = Rm = 1 420 MPa - Forgings - De = 40 mm
  • UNE-EN 2476:2019 Aerospace series - Steel 30CrNiMo8 (1.6580) - 1 100 MPa <= Rm <= 1 300 MPa - Forgings - De <= 100 mm (Endorsed by Asociación Española de Normalización in January of 2020.)
  • UNE-EN 2206:2008 Aerospace series - Steel FE-PL1502 (25CrMo4) - 650 MPa <= Rm <= 850 MPa - Bars - De <= 150 mm (Endorsed by AENOR in January of 2009.)
  • UNE-EN 2480:2008 Aerospace series - Steel FE-PL2108 (36NiCrMo16) - 1 250 MPa <= Rm <= 1 400 MPa - Bars - De <= 75 mm (Endorsed by AENOR in May of 2008.)
  • UNE-EN 2448:2008 Aerospace series - Steel FE-PL1503 (35CrMo4) - 900 MPa <= Rm <= 1 100 MPa - Bars - De <= 40 mm (Endorsed by AENOR in January of 2009.)
  • UNE-EN 2461:2009 Aerospace series - Steel FE-PM1901 (X12CrNi13) - 600 MPa <= Rm <= 800 MPa - Forgings - De <= 70 mm (Endorsed by AENOR in March of 2009.)
  • UNE-EN 2483:2010 Aerospace series. Steel FE-PL2108 (36NiCrMo16). 1 100 MPa <= Rm <= 1 300 MPa. Forgings. De <= 100 mm (Endorsed by AENOR in February of 2011.)
  • UNE-EN 2481:2010 Aerospace series. Steel FE-PL2108 (36NiCrMo16). 1 250 MPa <= Rm <= 1 400 MPa. Forgings. De <= 75 mm (Endorsed by AENOR in February of 2011.)
  • UNE-EN 2478:2008 Aerospace series - Steel FE-PL2107 (30NiCrMo16) - 1 220 MPa <= Rm <= 1 370 MPa - Bars - De <= 40 mm (Endorsed by AENOR in May of 2008.)
  • UNE-EN 2439:2009 Aerospace series - Steel FE-PL2102 (34NiCr6) - 900 MPa <= Rm <= 1 100 MPa - Forgings - De <= 40 mm (Endorsed by AENOR in March of 2009.)
  • UNE-EN 4904:2022 Aerospace series - Steel 36NiCrMo16 (1.6773) - 1 000 MPa = Rm = 1 200 MPa - Bars - 100 mm = D = 250 mm
  • UNE-EN 2460:2009 Aerospace series - Steel FE-PM1901 (X12CrNi13) - 600 MPa <= Rm <= 800 MPa - Bars - De <= 70 mm (Endorsed by AENOR in March of 2009.)
  • UNE-EN 2252:2012 Aerospace series - Steel FE-PL1505 (15CrMoV6) - 1 080 MPa <= Rm <= 1 250 MPa - Forgings - De <= 100 mm (Endorsed by AENOR in March of 2012.)
  • UNE-EN 2503:2019 Aerospace series - Steel X5CrNoMoCuNb14-5 (1.4594) - 930 MPa = Rm = 1 080 MPa - Forgings - De = 150 mm
  • UNE-EN 2278:2014 Aerospace series - Steel X12CrNiMoV12-3 (1.4933) - 900 MPa <= Rm <= 1 100 MPa - Bars - De <= 150 mm (Endorsed by AENOR in December of 2014.)
  • UNE-EN 4675:2011 Aerospace series - Titanium Ti-P63002 (Ti5Al5Mo5V3Cr0.4Fe) - Rm >= 1 300 MPa - Bars - De < 110 mm (Endorsed by AENOR in August of 2011.)
  • UNE-EN 2438:2008 Aerospace series - Steel FE-PL2102 (35NiCr6) - 900 MPa <= Rm <= 1 100 MPa - Bars - De <= 40 mm (Endorsed by AENOR in January of 2009.)
  • UNE-EN 2482:2010 Aerospace series. Steel FE-PL2108 (36NiCrMo16). 1 100 MPa <= Rm <= 1 300 MPa. Bars. De <= 100 mm (Endorsed by AENOR in February of 2011.)
  • UNE-EN 2205:2009 Aerospace series - Steel FE-PL1502 (25CrMo4) - 900 MPa <= Rm <= 1 100 MPa - Bars - De <= 40 mm (Endorsed by AENOR in April of 2009.)
  • UNE-EN 2446:2008 Aerospace series - Steel FE-PL1503 (35CrMo4) - 1 100 MPa <= Rm <= 1 300 MPa - Bars - De <= 25 mm (Endorsed by AENOR in January of 2009.)
  • UNE-EN 2502:2019 Aerospace series - Steel X5CrNoMoCuNb14-5 (1.4594) - 930 MPa = Rm = 1 080 MPa - Bars - De = 150 mm

European Association of Aerospace Industries, RM

  • AECMA PREN 3311-1988 Titanium Alloy TI-P63 Annealed 900 Less Than or Equal to Rm Less Than or Equal to 160 Mpa Bar for Machining De Less Than or Equal to 150 mm
  • AECMA PREN 2659-1988 Heat Resisting Cobalt Base Alloy Co-P93HT Solution Treated Rm Greater Than or Equal to 860 MPa Forgings
  • AECMA PREN 2772-1986 Aerospace Series Steel FE-PM61 Rm Greater Than or Equal to 960 MPa Forging De Less Than or Equal to 90 mm Issue P 1
  • AECMA PREN 3315-1988 Aerospace Series Titanium Alloy TI-P63 Solution Treated and Aged Rm Greater Than or Equal to 1070 MPa Forgings De Less Than or Equal to 50 mm Issue P 1
  • AECMA PREN 3316-1995 Aerospace Series Titanium Alloy TI-P64 Annealed Rm Greater Than or Equal to 1070 MPa Sheet and Strip a Less Than or Equal to 6 mm Edition P 2; WITHDRAWN
  • AECMA PREN 3317-1995 Aerospace Series Titanium Alloy TI-P64 Annealed Rm Greater Than or Equal to 1000 MPa Plate 6 Less Than a Less Than or Equal to 100 mm Edition P 2; WITHDRAWN
  • AECMA PREN 2171-1999 Heat Resisting Steel FE-PA92-HT Rm Greater Than or Equal to 900 MPa Bars Aerospace Series Edition 2; Supersedes Edition 1: January 1979 [Refer To: ASD-STAN PREN 4317, ASD-STAN PREN 4318]
  • AECMA PREN 2171-1979 Heat Resisting Steel FE-PA92-HT Rm Greater Than or Equal to 900 MPa Bars Aerospace Series Edition 1
  • AECMA PREN 2303-1980 Heat Resisting Steel FE-PA92-HT Rm Greater Than or Equal to 960 MPa Bars Aerospace Series Edition 1
  • AECMA PREN 2774-1986 Aerospace Series Steel FE-PM61 Rm Greater Than or Equal to 1310 MPa Bar De Less Than or Equal to 200 mm Issue P 1
  • AECMA PREN 3352-1988 Aerospace Series Titanium Alloy TI-C63 Hot Isostatic Pressed (Annealed) Rm Greater Than or Equal to 880 MPa High Strength Investment Casting a Less Than or Equal to 25 mm Issue P 1
  • AECMA PREN 2773-1986 Aerospace Series Steel FE-PM61 Rm Greater Than or Equal to 1310 MPa Sheet and Plate a Less Than or Equal to 12 mm Issue p 1
  • AECMA PREN 2775-1986 Aerospace Series Steel FE-PM61 Rm Greater Than or Equal to 1310 MPa Forging De Less Than or Equal to 150 mm Issue P 1
  • AECMA PREN 3363-1988 Aerospace Series Steel FE-CM68 Solution Treated Rm Greater Than or Equal to 485 MPa Sand or Investment Casting Issue P 1

Korean Agency for Technology and Standards (KATS), RM

Professional Standard - Electron, RM

  • SJ 51931/7-1998 Detail specification for R7K Soft-ferrite RM type serial cores

Standard Association of Australia （SAA）, RM

British Standards Institution (BSI), RM

  • BS ISO 19153:2014 Geospatial Digital Rights Management Reference Model (GeoDRM RM)
  • BS EN 60424-2:1998 Guidance of the limits of surface irregularities of ferrite cores - RM-cores
  • BS EN 60424-2:2016 Ferrite cores. Guidelines on the limits of surface irregularities. RM-cores
  • BS EN 2502:2019 Aerospace series. Steel X5CrNoMoCuNb14-5 (1.4594). 930 MPa ≤ Rm ≤ 1 080 MPa. Bars
  • BS EN 62317-4:2005 Ferrite cores - Dimensions - Part 4: RM-cores and associated parts
  • BS EN 62317-4:2006 Ferrite cores - Dimensions - RM-cores and associated parts
  • BS EN 2461:2009 Aerospace series - Steel FE-PM1901 (X12CrNi13) - 600 MPa Rm 800 MPa - Forgings - De 70 mm
  • BS EN 2465:2007 Aerospace series - Steel FE-PA3901 (X2CrNi18-9) - Softened - 450 MPa Rm 680 MPa - Bar for machining - 4 mm De 100 mm
  • BS EN 2481:2011 Aerospace series. Steel FE-PL2108 (36NiCrMo16). 1250 MPa Rm 1400 MPa. Forgings. De 75 mm
  • BS EN 2480:2009 Aerospace series - Steel FE-PL2108 (36NiCrMo16) - 1250 MPa Rm 1400 MPa - Bars - De 75 mm
  • BS EN 2478:2009 Aerospace series - Steel FE-PL2107 (30NiCrMo16) - 1220 MPa Rm 1370 MPa - Bars - De 40 mm
  • BS EN 2448:2009 Aerospace series - Steel FE-PL1503 (35CrMo4) - 900 MPa Rm 1100 MPa - Bars - De 40 mm
  • BS EN 2438:2009 Aerospace series - Steel FE-PL2102 (35NiCr6) - 900 MPa Rm 1100 MPa - Bars - De 40 mm
  • BS EN 2206:2009 Aerospace series - Steel FE-PL1502 (25CrMo4) - 650 MPa Rm 850 MPa - Bars - De 150 mm
  • BS EN 2446:2009 Aerospace series - Steel FE-PL1503 (35CrMo4) - 1100 MPa Rm 1300 MPa - Bars - De 25 mm
  • BS EN 2448:2008 Aerospace series - Steel FE-PL1503 (35CrMo4) - 900 MPa Rm 1100 MPa - Bars - De 40 mm
  • BS EN 2439:2009 Aerospace series - Steel FE-PL2102 (34NiCr6) - 900 MPa Rm 1100 MPa - Forgings - De 40 mm
  • BS EN 2446:2008 Aerospace series - Steel FE-PL1503 (35CrMo4) - 1100 MPa Rm 1300 MPa - Bars - De 25 mm
  • BS EN 2438:2008 Aerospace series - Steel FE-PL2102 (35NiCr6) - 900 MPa Rm 1100 MPa - Bars - De 40 mm
  • BS EN 2478:2008 Aerospace series - Steel FE-PL2107 (30NiCrMo16) - 1220 MPa Rm 1370 MPa - Bars - De 40 mm
  • BS EN IEC 63093-4:2019 Ferrite cores. Guidelines on dimensions and the limits of surface irregularities - RM-cores
  • BS EN 2206:2008 Aerospace series - Steel FE-PL1502 (25CrMo4) - 650 MPa Rm 850 MPa - Bars - De 150 mm
  • BS EN 2480:2008 Aerospace series - Steel FE-PL2108 (36NiCrMo16) - 1250 MPa Rm 1400 MPa - Bars - De 75 mm
  • BS EN 2482:2011 Aerospace series. Steel FE-PL2108 (36NiCrMo16). 1100 MPa Rm 1300 MPa. Bars. De 100 mm
  • BS EN 2483:2011 Aerospace series. Steel FE-PL2108 (36NiCrMo16). 1100 MPa Rm 1300 MPa. Forgings. De 100 mm
  • BS EN 2460:2009 Aerospace series - Steel FE-PM1901 (X12CrNi13) - 600 MPa Rm 800 MPa - Bars - De 70 mm

Aerospace, Security and Defence Industries Association of Europe (ASD), RM

  • ASD-STAN PREN 2762-2010 Aerospace series Steel FE-PL80 1900 = Rm = 2100 MPa Bar De = 75 mm Edition P2
  • ASD-STAN PREN 2172-2010 Aerospace series Heat resisting steel FE-PA92-HT Rm = 900 MPa Forgings Edition P2
  • ASD-STAN PREN 2507-2010 Aerospace series Steel FE-PM66 1270 = Rm = 1470 MPa Forgings De = 100 mm Edition 2
  • ASD-STAN PREN 2228-1977 Steel FE-PA12 500 MPa Less Than or Equal to Rm Less Than or Equal to 700 MPa Sheets 0.5 mm Less Than or Equal to a Less Than or Equal to 6 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2502-1984 Steel FE-PM66 930 Less Than or Equal to Rm Less Than or Equal to 1080 MPa Bars De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2441-2010 Aerospace series Steel FE-PL711 1250 MPa = Rm = 1450 MPa Forgings De = 16 mm Edition 2
  • ASD-STAN PREN 2455-2010 Aerospace series Steel FE-PL73 880 MPa = Rm = 1080 MPa Forgings De = 150 mm Edition 2
  • ASD-STAN PREN 2472-2010 Aerospace series Steel FE-PL74 1250 MPa = Rm = 1450 MPa Forgings De = 40 mm Edition 2
  • ASD-STAN PREN 2474-2010 Aerospace series Steel FE-PL74 900 MPa = Rm = 1100 MPa Forgings De = 150 mm Edition 2
  • ASD-STAN PREN 2505-2010 Aerospace series Steel FE-PM66 1130 MPa = Rm = 1330 MPa Forgings De = 150 mm Edition 2
  • ASD-STAN PREN 2506-2010 Aerospace series Steel FE-PM66 1270 = Rm = 1470 MPa Bars De = 100 mm Edition 2
  • ASD-STAN PREN 2136-1979 Steel FE-PM42 900 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Bars De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2137-1981 Steel FE-PL75 1100 MPa Less Than or Equal to Rm Less Than or Equal to 1250 MPa Bars De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2312-1979 Steel FE-PM42 Rm Greater Than or Equal to 1350 MPa Forgings De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2313-1979 Steel FE-PM42 Rm Greater Than or Equal to 1350 MPa Bars De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2504-2010 Aerospace series Steel FE-PM66 1130 MPa = Rm = 1330 MPa Bars De = 150 mm Edition 2
  • ASD-STAN PREN 2274-1979 Steel FE-PA95 1750 MPa Less Than or Equal to Rm Less Than or Equal to 2000 MPa Bars De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2275-1979 Steel FE-PA95 1750 MPa Less Than or Equal to Rm Less Than or Equal to 2000 MPa Forgings De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2279-1979 Steel FE-PM37 900 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Forgings De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2281-1979 Steel FE-PM42 900 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Forgings De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2494-1981 Heat Resisting Steel FE-PM38 1000 MPa Less Than or Equal to Rm Less Than or Equal to 1140 MPa Forgings Aerospace Series (Edition 1)
  • ASD-STAN PREN 2503-1984 Steel FE-PM66 930 Less Than or Equal to Rm Less Than or Equal to 1080 MPa Forgings De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2438-1981 Steel FE-PL62 900 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Bars De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2439-1981 Steel FE-PL62 900 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Forgings De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2443-1981 Steel FE-PL711 1100 MPa Less Than or Equal to Rm Less Than or Equal to 1300 MPa Forgings De Less Than or Equal to 25 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2447-1981 Steel FE-PL45 1100 MPa Less Than or Equal to Rm Less Than or Equal to 1300 MPa Forgings De Less Than or Equal to 25 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2448-1981 Steel FE-PL45 900 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Bars De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2449-1981 Steel FE-PL45 900 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Forgings De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2450-1981 Steel FE-PL73 1230 MPa Less Than or Equal to Rm Less Than or Equal to 1420 MPa Bars De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2451-1981 Steel FE-PL73 1230 MPa Less Than or Equal to Rm Less Than or Equal to 1420 MPa Forgings De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2452-1981 Steel FE-PL73 1080 MPa Less Than or Equal to Rm Less Than or Equal to 1280 MPa Bars De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2454-1981 Steel FE-PL73 880 MPa Less Than or Equal to Rm Less Than or Equal to 1080 MPa Bars De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2456-1981 Steel FE-PL48 1050 MPa Less Than or Equal to Rm Less Than or Equal to 1250 MPa Bars De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2457-1981 Steel FE-PL48 1050 MPa Less Than or Equal to Rm Less Than or Equal to 1250 MPa Forgings De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2458-1981 Steel FE-PL48 950 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Bars De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2459-1981 Steel FE-PL48 950 MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Forgings De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2471-1981 Steel FE-PL74 1250 MPa Less Than or Equal to Rm Less Than or Equal to 1450 MPa Bars De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2473-1981 Steel FE-PL74 900MPa Less Than or Equal to Rm Less Than or Equal to 1100 MPa Bars De Less Than or Equal to 150 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2476-1981 Steel FE-PL74 1100 MPa Less Than or Equal to Rm Less Than or Equal to 1300 MPa Forgings De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2477-1981 Steel FE-PL75 1100 MPa Less Than or Equal to Rm Less Than or Equal to 1250 MPa Forgings De Less Than or Equal to 100 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2478-1981 Steel FE-PL75 1250 MPa Less Than or Equal to Rm Less Than or Equal to 1400 MPa Bars De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2479-1981 Steel FE-PL75 1250 MPa Less Than or Equal to Rm Less Than or Equal to 1400 MPa Forgings De Less Than or Equal to 40 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2480-1981 Steel FE-PL76 1250 MPa Less Than or Equal to Rm Less Than or Equal to 1400 MPa Bars De Less Than or Equal to 75 mm Aerospace Series (Edition 1)
  • ASD-STAN PREN 2759-1986 Aerospace Series Steel FE-PL80 1900 Less Than or Equal to Rm Less Than or Equal to 2100 MPa Forging De Less Than or Equal to 75 mm (Issue P 1)
  • ASD-STAN PREN 2760-1986 Aerospace Series Steel FE-PL78 1760 Less Than or Equal to Rm Less Than or Equal to 2000 MPa Bar De Less Than or Equal to 75 mm (Issue P 1)
  • ASD-STAN PREN 2761-1986 Aerospace Series Steel FE-PL78 1760 Less Than or Equal to Rm Less Than or Equal to 2000 MPa Forging De Less Than or Equal to 75 mm (Issue P 1)
  • ASD-STAN PREN 4675-2009 Aerospace series Titanium Ti-P63002 (Ti5Al5Mo5V3Cr0,4Fe) Rm >= 1300 MPa Bars De <= 100 mm (Edition P 1)

Danish Standards Foundation, RM

  • DS/EN 4685:2011 Aerospace series - Titanium Ti10V2Fe3Al - Bars - D < 110 mm - Rm + 1 240 MPa
  • DS/EN 62317-4:2006 Ferrite cores - Dimensions -- Part 4: RM-cores and associated parts
  • DS/EN 4675:2011 Aerospace series - Titanium Ti-P63002 (Ti5Al5Mo5V3Cr0.4Fe) - Rm + 1 300 MPa - Bars - De < 110 mm
  • DS/EN 2206:2009 Aerospace series - Steel FE-PL1502 (25CrMo4) - 650 MPa <= Rm <= 850 MPa - Bars - De <= 150 mm
  • DS/EN 2460:2009 Aerospace series - Steel FE-PM1901 (X12Cr13) - 600 MPa <= Rm <= 800 MPa - Bars - De <= 70 mm
  • DS/EN 2461:2009 Aerospace series - Steel FE-PM1901 (X12Cr13) - 600 MPa <= Rm <= 800 MPa - Forgings - De <= 70 mm
  • DS/EN 2205:2009 Aerospace series - Steel FE-PL1502 (25CrMo4) - 900 MPa <= Rm <= 1 100 MPa - Bars - De <= 40 mm
  • DS/EN 2438:2009 Aerospace series - Steel FE-PL2102 (35NiCr6) - 900 MPa <= Rm <= 1 100 MPa - Bars - De <= 40 mm
  • DS/EN 2439:2009 Aerospace series - Steel FE-PL2102 (34NiCr6) - 900 MPa <= Rm <= 1 100 MPa - Forgings - De <= 40 mm
  • DS/EN 2448:2009 Aerospace series - Steel FE-PL1503 (35CrMo4) - 900 MPa <= Rm <= 1 100 MPa - Bars - De <= 40 mm

Lithuanian Standards Office , RM

  • LST EN 4685-2011 Aerospace series - Titanium Ti10V2Fe3Al - Bars - D < 110 mm - Rm ? 1 240 MPa
  • LST EN 2573-2007 Aerospace series - Steel FE-PA3601 (X6CrNiTi18-10) - Softened - Rm ? 780 MPa - Wire - 0,25 mm ? De ? 3 mm
  • LST 1983-1-2005 Beer. Determination of carbon dioxide content. Part 1: Titration method (RM) (EBC 9.28.1)

German Institute for Standardization, RM

  • DIN EN 2480:2009 Aerospace series - Steel FE-PL2108 (36NiCrMo16) - 1 250 MPa R<(Index)m> 1400 MPa - Bars - D<(Index)e> 75 mm; German and English version EN 2480:2008
  • DIN EN 2478:2009 Aerospace series - Steel FE-PL2107 (30NiCrMo16) - 1220 MPa R<(Index)m> 1370 MPa - Bars - D<(Index)e> 40 mm; German and English version EN 2478:2008
  • DIN EN 2206:2009 Aerospace series - Steel FE-PL1502 (25CrMo4) - 650 MPa R<(Index)m> 850 MPa - Bars - D<(Index)e> 150 mm; German and English version EN 2206:2008
  • DIN EN 2137:2017 Aerospace series - Steel FE-PL75 - 1100 MPa <= Rm <= 1250 MPa - Bars - De <= 100 mm; German and English version FprEN 2137:2017
  • DIN EN 2279:2018 Aerospace series - Steel FE-PM37 - 900 MPa <= Rm <= 1100 MPa - Forgings - De <= 150 mm; German and English version EN 2279:2018
  • DIN EN 2280:2018 Aerospace series - Steel FE-PM37 - 900 MPa <= Rm <= 1 100 MPa - Sheet - a <= 6 mm; German and English version EN 2280:2018

未注明发布机构, RM

  • BS EN 4675:2011(2015) Aerospace series — Titanium Ti - P63002 (Ti5Al5Mo5V3Cr0.4Fe) — Rm > 1300 MPa — Bars — De < 110 mm
  • BS EN 2450:2018(2019) Aerospace series — Steel 31Ni10 — 1230 MPa ≤ Rm ≤ 1420 MPa — Bars — De ≤ 40 mm
  • BS EN 62317-4:2005(2018) Ferrite cores - Dimensions Part 4 : RM - cores and associated parts
  • BS EN 2482:2010(2011) Aerospace series — Steel FE - PL2108 (36NiCrMo16) — 1100 MPa Rm 1300 MPa — Bars — De 100 mm
  • BS EN 2483:2010(2011) Aerospace series — Steel FE - PL2108 (36NiCrMo16) — 1100 MPa Rm 1300 MPa — Forgings — De 100 mm
  • BS EN 2481:2010(2011) Aerospace series — Steel FE - PL2108 (36NiCrMo16) — 1250 MPa Rm 1400 MPa — Forgings — De 75 mm

(U.S.) Telecommunications Industries Association , RM

  • TIA-707.03-B-2010 Data Service Options for Spread Spectrum Systems: AT Command Processing and the Rm Interface

AT-ON, RM

  • OENORM EN 4904-2021 Aerospace series - Steel 36NiCrMo16 - 1000 MPa <= Rm <= 1200 MPa - Bars - 100 <= D <= 250 mm

International Electrotechnical Commission (IEC), RM

  • IEC 60424-2:1997 Guidance on the limits of surface irregularities of ferrite cores - Part 2: RM-cores
  • IEC 60424-2:2015 Ferrite cores - Guidelines on the limits of surface irregularities - Part 2: RM-cores

ES-AENOR, RM

General Administration of Quality Supervision, Inspection and Quarantine of the People‘s Republic of China, RM

  • GB/T 9634.2-2002 Ferrite cores--Guide on the limits of surface irregularities--Part 2: RM-cores

CEN - European Committee for Standardization, RM

  • EN 2450:2018 Aerospace series - Steel 31Ni10 - 1 230 MPa ≤ Rm ≤ 1 420 MPa - Bars - De ≤ 40 mm

工业和信息化部, RM

  • SJ/T 3172.4-2016 Dimensions of ferrite cores Part 4: RM type cores and accessories

  RM, rm-200a, rm1220, rm1220, rm-odp, idf/rm+87, idf/rm51, idf/rm, material rm, rm50, RM 100, material rm, rm-200, rm2016, rm.5, rm《5, rm2014, rm1050mpa, eight rm, rm208.

 



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