1、 . British Standard 2G 199: 1984 UDC 629.7.058.41083.51 British Standards Institution. No part of this publication may be photocopied or otherwise “produced without the priur permission in “,riUng of BSI British Standard Aerospace Series: Schedule for Tables relating to altitudes, airspeed and Mach
2、numbers for use in aeronautical instrument design and calibration Serie aerospatiale, Plan normalise des tables d altitudes, vitesss., de I air et nombres de Mach utilisees pour la conception et Ietalonnage des instruments aeronautiques Luft- und Raumfahrt-Reihe, Tabellen Qber H6hen, Fluggeschwindig
3、keiten und Machzahlen fUrdie Konstruktion und Kalibrierung von aeronautischen Instrumenten Contents Foreword Committees responsible Schedule 1 Scope 2 Basis of tables 2.1 Notation and standard values 2.2 Pressure units 2.3 Notes on the tables Foreword Page 1 Back page 2 2 2 2 3 Over the years a numb
4、er of pressure altitude anti pressure airspeed tables have been publisher.:. The former differ from one another according to the temperature altitude convention adopted, and they have been identified by a particular Standard or Model atmosphere. The latter differ principally in the values assigned t
5、o the basic constants. This revision of the British Standard has been prepared under the direction of the Aerospace Standards Committee and superscd,s British Standard G 199: 1967, which is withdrawn. Terminology has been rationalized to align with accepted international practice. New formulae have
6、been included which enable individual calculations and table compilation to be made and additional tables have been inciuded.,Known errors in tables in the earlier issue of the standard. have been corrected. A series of tables is presented which can be used by all concerned in the aircraft instrumen
7、t field and so eliminate British Standards Institution Page Tables 1 Altitude 6 2 Calibrated airspeed 10 3 Mach number 17 4 True airspeed 21 5 Speed of sound 30 .6 Ratio of measured/free stream temperatures 31 7 Rtio of impact pressure to static pressure qc/Ps as values of Mach number 32 8 Pressure
8、units relationship 38 any possible confusion. The altitude. tables and altitude parameterswhere used in other tables are based on the now universally accepted ICAO Standard Atmosphere, 1964:which is identical to ISO 2533 over the tabulated altitude range. The airspeed tables and those where airspeed
9、 is a parameter are calculated from the de St. Venant and Rayleigh formulae, the values of the base constants being those of ICAO Document 7488/2, ISO 2533 and BS 350. The tables are primarily for use in the aircraft instrument field and do not provide for other special interests, e.g. aerodynamics
10、or space technology. The information is therefore not comprehensive and ranges are confined to probable aircraft reqldrements in the foreseeable future. Althou9h the main purpose of the tables is for calibration work, sufficient :1formation is given to enable the tables to be of assistance In instru
11、ment development and design. Compliance with a 8ritish Standad does not of itself confer immunity from legal obligations . ttiZI53 3120 I , “ . _ ,.: : to“ British Standard 2G 199: 1984 1 Scope This British Standard provides a schedule of tables relating to altitudes. airspeeds and Mach numbers for
12、use in aeronautical instrument design and calibration. The size of the tables have been restricted and the units used for the various parameters have been kept to a minimum. namely, altitude in geopotential feet, pressures in millibars and inches of mercury, airspeed in knots, and temperature in deg
13、roes Celsius. NOTE. Altitude measurements are based on the geopotential foot. and, in speed measurements where the knot is involved. this is t3ken to mean one international nautical mile per hour. 2 Basis oftables 2.1 Notation and standard values Altitude Igeopotential) H Free stream static pressure
14、 Atmospheric temperature lapse rate where (a) L = 6.50 “C/1 000 m for - 3000 ft “,-H 1 Ps L p, Ratio of specific heflts of air Specific gas constant r = 1.4 (exactly) R=287.0529 m2K-1.o-2 NOTE. R“ = RiM where C Density of air Speed of sound P a I nter“ational knot kn = 6076.1155 ft/h Ibased on a nau
15、t;cal mile of 1852 m lexactly) . Temperalure lin Kelvin) Temp.rature lin degrees Celsius) Acceleration due to gravity Subscript a denotes standard value at zero altitude Ifrom ICAO Document 748B/2) Pso = 1013.25 mbar Po = 1.2250 kg/m3 00 = + 15“C . To =2B8.15 K ao = 340.294 m/s = 661.47B6 kn T .() 9
16、 90 = 9.80665 mis2 = 32.17405 It/s2 Free stream ambient air temperature Temperature measured by aircraft sensor Total temperature Ts and Os Tmand Om T,and II, Recovery factor of sensor where r = - - - 1 5 (Tm ) . M2 Ts 2.2 Pressure units Pressures are given throughout the table in millibars where 1
17、mbar = 100 Pa. In tables 1 and 2 pressures are also given in inches of mercury IinHg). the relationship with millibars being a3 defined in BS 350. Le.: r 1 inHg = 0.0254 x 13595.1 x 9.80665 =3386.39 Pa (33.B639 mbar) To satisfy this relationship themercury is assumed to be at O“C with a density of e
18、xactly 13595.1 kg/rn3 and to be under standard gravity conditions of 9.806 65 m/s2lsee also BS 2520). . R is the universal gas constant= 8,314315 JK -1 mol- and Table 8 gives conversion factors for pressures in terms of length of a column of water. The relationships are derived Vc . from the definit
19、ion in BS 350. Le.: M is the mean rrolar mass of air: 28,9644 gmol-1 Calibrated airspeed. in knots. True airspeed Mach number V, . 1 mmH20 = 9.880665 Pa (0.0980665 rnbar) M T . satisfy this relationship it is assumed that the water is upproximately + 4 C with a uniform density of 1000 kg/m3 (e“actly
20、) and under standard gravity conditions of 9.80665 m/s2 2 ttl Zl53 3 1 2 1 , , . , ., . “, “ : ., . .) “ . ,“ . . . “ ; ( 2.3 Notes on the tables u : British Standard 2G 199: 1984 2.3.1 Table 1. Altitude (range - 3000 It to 105000 It). The table conforms to thd ICAO Standard Atmospher 1964 (Geopoten
21、tial aitit“de). For other altitude related quantities. reference should be n:lade to leAD Document. 7488/2. The table is based on the following formulae: P -p *1 To * I :;. ,-, T“ + L(H - H*) 10910P,=1091OP,-10910exp 1 (H-Hll R*Ts where Ps, Ts *. H-“ are datum values of these variables, For Fie alti
22、tude range considered refer to equations (7) to (12). T, = T, + L (H - H*) Ts = T;j * L= P. Po PoR“T, = (!,_)O.5 00 To L=O c, L “,0 L=O Numericallyevalueted: “; . (a) - 3000 ft ,;, H ,;, 36089 ft. L = .:. 6.50 e/l 000 m or - 1.9812 e/l 000 ft: p, = 1013.25 . mbar I 288 15 - ) - 5,250879 288.15 -(1.9
23、812x 1O-3H) .-T, = 288.15 -(1.9812x 10-3H) K (b) 36089 It ,;,H 1) =(y + 1)M21 il + 112M2 I). 1 _ 1 Ps 2 4),M2.,.2y+2 Numerically evaluated: Subsonic. !.s.= 11 + 0.2 M2)7/2 - 1 Ps Supersonic. !: Ps = 1 166.92 158M7!_1 (7M2 _ 1 )5/2 .“ “ c :; . ,. (19) , . c. (20) (211 (22) The relationship between M
24、and Ve is obtained by equating,the common value qe in equations (17) or (1 8)with thatin equations (21) or (221. according to the magnitude of M and Velao: it will be “oted that there is a condition where Mean be 1 while Velao is 1 and known recovery factor other them 1 then: _ r 1 1,-1IM,“ ,. Tm =
25、j2YM_IY_11Ij2+1)-1IMl T, (y _112M ) 1(-11 +- . 1+r 2 . , 2 M. (,-11 2 ;“.-, 2,3.7 Table 7. Ratio ofimp.ctpressure to static pressure. Varia(ion of ;he“atio qclp, is ,abled for v8Iu.;of Mfrom C.l 00 to 4.000, calculated from equations 12,1) and 122).ISee 2.3.3.) , . 2.3.8 Table 8. Relationship of var
26、ious pressure units. These values have been derived from Bf; 350: units in torms of length of a column of mercury or water being defined therein. (See also 2.2.1 5 ItiZ5331241 British Standard 2G 199: 1984 Table 1. Altitude P,;.itude Il,eopotentialJ H Static pressure p! TemperatmB o Density ratio ,1
27、“0 I (L) os Po Speed (f sound Pressure ratio p.lP.o 11 -3000 -2500 -20()0 -1500 -1000 -900 -800 -700 -600 -500 -400 -300 -200 -100 o 100 200 300 400 500 600 700 800 900 1000 1100 1200 1300 1400 1500 ,600 1700 1800 1900 2000 2100 2200 2300 2400 2500 mbar inHg c It/mbar 1128.029 33.3107 ,20.94 25.04 1
28、.0908 1108.201 32.7252 19.95 25.40 1.0752 1088.657 32.1480 18.96 25.77 1.0598 1069.393 31.5791 17.97 26.14 1.0446 1.0444 1.0369 1.0295 1.0221 i.0147 1.0103 1.0086 1.0069 1.0051 1.0034 . 1050.406 31.0185 16.98, 26.53 11.0296 1046.641 30.9073 16.78 26.60 1.0256 1.0132 1.0031 1042.888 30.7964 16.58 .26
29、.681.0236 1.0117 1.0027 1039.145 30.61359 16.39 26.76 1.0206 1.0103 1.0J24 1035.413 30.5757 16.19 26.84 1.0177 1.0088 1.0021 1031.692 30.4658 15.99 26.91 1.0147 1.0073 1.0017 1027.982 30.3563 15.79 26.99 1.0118 1.0059 1.0014 1024.283 30.2471 15.59 27.07 I 1.0088 1.0044 1.0010 1020.595 30.1381 15.40
30、27.15 I 1.0059 1.0029 1.0007 1016.917 30.0295 15.20 27.23 1.0029 1.0015 1.0003 1013.250 29.9212 15.00 27.31 1.0000 1.0000 1.0000 1009.594 29.8133 14.80 27.39 0.9971 0.9985 0.99!? 1005.948 29.7056 14.60 27.47 0.9942 0.9971 0.9993 1002.3 I 3 29.5983 14.41 27.55 0.9913 0.9956 0.9990 998.689 29.4913 14.
31、21 27.63 0.9883 0.9942 0.g986 935.075 29.3845 14.01 27.71 I 0.9855 0.9927 0.9983 991.472 29.2782 13.81 27.80 0.9826 0.9912 0.9979 987.880 29.1721 13.61 27.88 0.9797 0.9898 0.9976 984.298 29.0663 13.42 27.96 0.9768 0.g883 0.9972 977.166 28.855- 13.0213.1.2.1 U.9711 0.9854 0.9966 I 1 1133 1.0937 1.074
32、4 1.05E4 1.0367 1.0330 1.0293 1.0256 1.0219 1.0182 1.O14! 1.0109 1.0072 1.0036 11.0000 0.9964 0.9928 0.9892 0.9856 0.9821 0.9785 0.9750 , 0.9714 0.9679 0.9544 980.727 28.9608 13.2228.04 0.9739 I 0.9869 0.9969 973.615 28.7508 12.82 28: 0.9682 0.9840 0.9962 0.9609 970.075 28.6463 12.62 :28.29 0.9654 0
33、.9825 0.9959 0.9574 966.546 28.5421 12.42 28.37 0.9625 0.9811 0.9955 0.9539 963.027 28.4381 12.23 28.46 0.9597 0.9796 0.9952 0.9504 959.518 28.3345 12.03 2.8.54 0.9568 0.9782 0.9948 0.9470 956.019 28.2312 11.83 28.63 0.9540 0.9767 0.9945 0.9435 952.531 28.1282 11.63 28.71 0.9512 0.9753 0.9941 0.9401
34、 949.054 28.0255 11.43 I 28.80 0.9484 0.9738 0.9938 0.9366 945.586 27.9231 11.24 28.88 0.9456 0.9724 0.9934 0.9332 942.129 7.8210 11.04 28.970.9428 0.9710 0.9931 0.9298 938.682 27.7193 10.84 29.05 0.9400 0.9695 0.9928 0.9264 935.245 27.6178 10.64 29.14 0.9372 0.9681 0.9924 0.9230 I 931.819 27.5166 1
35、0.44 29.23 0.9344 0.9666 0.9921 0.9196 928.402 27.4157 10.25 29.31 0.9316 0.9652 0.9917 10.9163 I 924.996 27.3151 10.05 29.40 0.9289 0.9638 0.9914 0.9129 2(,00 921.600 27.2148 9.84 29.49 0.9261 0.9623 0.9910 0.9095 I 2700 918.214 27.1148 9.65 29.58 0.92:3 0.9609 0.9907 0.9062 280-1 914.838 27.0151 9
36、.45 29.67 0.9206 0.9595 0.9903 0.9029 2900 911.472 26.9158 9.25 29.75 0.9179 U.9580 0.9900 0.8996 ,-1 _ 3_0_0_0_ ,_.9_0_8_._1 _17_1-2_6_.8 _ 1_6.7 _ -_9_ 0 _ 6 _-L-=29.84 0=-.9_1_5_1_L.0._9_56_6_-“-1_0_.9_8_9. _ L-0._8_96_2-, G. itiI ZI53 , British Stmdara 2G 199: 1984 -Table 1. (continued) Altitude
37、 Static pressure p. Tomperatre !l.HIAP. Density (I!-) “ Speed of :. Pressure (geopotentiall (/ ratio I, sound ratio H pl/Jn ratio p./P1O alBa It mbar inHg C It/mbar I -3100 904.771 26.7179 8.86 29.93 I 0.9124 0.9552 0.9993 0.8929 3200 901.435 26.6194 8.66 30.02 0.9097 0.9538 0.9889 0.8896 3300 898.1
38、09 26.5211 8.46 30.11 0.9069 0.9523 0.9886 0.B864 3400 894.793 26.4232 8.26 30.20 0.9042 0.9509 0.9882 0.8831 3500 891.487 26.3256 8.07 30.29 0.9015 0.9495 0.9879 0.8793 3600 888.191 26.2283 7.87 30.38 I 0.8988 0.9481 0.9875 0.8766 3700 884.905 26.1312 7.67 30.48 I 0.8961 0.9466 0.9872 0.8733 3800 8
39、81.629 26.0345 7.47 30.57 I 0.8934 0.9452 0.9868 0.8701 I 3900 878.362 25.9380 7.27 30.66 I 0.8908 0.9438 0.9865 0.8669 4000 875.105 25.8418 7.08 30.75 I 0.8881 I 0.9424 0.9862 0.8637 I 4100 871.859 257460 6.88 30.84 0.8854 0.9410 0.9858 0.8605 4200 868.621 25.65()4 6.68 30.94 0.8828 0.9396 0.9855 0
40、.8573 4300 865.394 25.5551 6.48 31.03 0.8801 0.9381 0.9851 0.8541 4400 I 862.176 25.4600 6.28 31.12 0.8774 0.9367 0.9848 I 0.8509 4500 I 858.968 25.3653 6.08 31.22 I 0.8748 I 0.9353 0.9.874 4.797 4.722 4.650 4.530 4.512 4.446 4.382 I Calibrated Dyn,“ic pressure tJ.VJIlQr. airspeed Q, V, -kn mbar inH
41、g kn/mbar 71 8.195 0.2420 4.319 72 8.428 0.2489 4.259 73 8.665 0.2559 4.200 74 8.904 0.2629 ,.142 75 9.147 0.2701 , 4.086 76 0.394 0.2774 4.032 77 9.644 0.2848 3.979 78 9.896 0.2922 3.927 79 10.153 0.2998 3.877 80 10.412 0.3075 3.827 81 10.675 0.3152 3.“180 82 10.942 0.3231 3.733 83 11.211 0.3311 3.
42、687 84 11.484 I 0.3391 3.642 85 11.760 I 0.3473 I 3599 86 12.040 0.3555 3.556 87 12.323 0.3639 3.515 8e 12.609 0.3723 3.474 89 12.898 0.3809 I 3.434 90 13.191 0.3895 . 3.396 13.487 0.3983 I 3.358 91 I 92 13.787 0.4071 3.320 93 14.089 0.4161 3.284 94 14.396 0.4251 3.248 95 14.705 0.4342 3.214 96 15.0
43、16 0.4435 I 3.179 97 15.334 0.4528 3.146 98 15.654 0.4623 3.113 99 I 15.977 0.4718 3.081 100 I 16.303 0.4814 3.049 101 I 16.632 0.4912 3.019 102 I 16.965 0.5010 2.988 103 17.302 0.5109 2.959 104 17.641 0.5209 2.929 105 17.984 0.5311 2.901 106 18.331 0.5413 2.873 I 107 18.681 0.5516 2.845 108 19.034
44、0.5621 2.818 109 18.390 0.5726 2.792 110 19.750 0.5832 2.766 111 20.113 0.5939 2.740 112 20.480 0.6048 2.715 113 20.850 0.6157 2.690 114 21.223 0.6267 2.666 115 21.600 0.6379 2.642 nftI 10_ Lti,Z1533129 “ f- ,. “ . Table 2. (continued) Calibrated Dynamic pras;uro AVc/ AQc airspeed Q, V, kn mbar inHg
45、 kn/mbar 116 21.980 0.6491 2.619 117 22.364 0.6604 2.595 118 22.751 0.6718 2.573 119 23.141 0.6834 2.550 120 23.535 0.6950 2.529 121 23.932 07067 2.507 122 24.333 0.7185 2.486 123 24.737 0.7305 2.465 124 25.144 0.7425 2.444 125 25.555 0.746 2.424 126 25.969 0.7669 2.404 127 26.387 0.7792 2.38 128 26
46、.808 0.7916 2.365 129 27.233 0.8042 2.346 130 27.660 0.a168 2.327 131 28.092 0.8296 2.309 132 28.527 0.8424 2.291 133 28.965 0.8553 2.273 134 29.407 0.8684 2.255 135 29.852 0.8815 2.238 136 30.300 0.8948 2.221 137 30.752 0.9081 2.204 138 21.208 0.9216 2.187 139 31.657 0.9351 2.171 140 32.129 0.9488
47、2.155 141 32.595 0.9625 2.139 142 33.064 0.9764 2.123 143 33.537 0.9903 2.107 144 34.013 1.0044 2.092 145 34.493 1.0186 2.077 146 34.976 1.0328 2.062 147 35.463 1.0472 2.047 148 35.953 1.0617 2.033 149 36.447 1.0763 2.018 150 36.944 1.0909 2.004 151 37.444 1.1057 1.990 152 37.949 1.1206 1.977 153 38
48、.456 1.1356 1.963 154 38.967 1.1507 1.950 155 39.482 1.1659 1.936 156 40.000 1.1812 1.923 157 40.522 1.1966 1.910 158 41.047 1.2121 1.8SS 159 41.576 1.2277 1.885 160 42.106 1.2435 1.873 11 Calibrcted airspeed V, kn 161 162 163 164 165 166 167 168 169 170 171 172 173 174 175 176 177 178 179 180 181 1
49、82 183 184 185 186 187 188 189 190 191 192 193 194 195 196 197 198 199 200 201 202 203 204 205 Dynamic pressure Q, mbar inHg 42.644 1.2593 43.183 1.2752 43.726 1.2912 44.273 1.3074 44.822 1.3236 45.376 1.3400 45.933 1.3564 46.494 13730 47.058 1.3896 47.626 1.4064 48.197 1.4233 48.772 1.4402 49.350 1.4573 49.93 lA745 50.518 1.4918 51.107 1.5092 51.700 1.5267 52.296 1.5443 52.896 1.5620 53.500 1.5798 54
