Aeronautical Engineer Data Book Episode 14 ppt

� Lp Rolling moment due to roll rate (i) wing contribution s – ᎏᎏ (ay + CDy)cyy2dy 2Ss2 Np Yawing moment due to roll rate (i) wing contribution – ᎏᎏ 2Ss2 Yr Sideforce due to yaw rate (i) fin contribution VFa1F � Lr Rolling moment due to yaw rate (i) wing contribution s ᎏᎏ CLycyy2dy Ss2 (ii) fin contribution h lF � F a1FVF ᎏᎏ � – Lv(fin) ᎏᎏ b b (i) wing contribution ᎏᎏ CDycyy2dy Nr Yawing moment due to yaw rate s Ly � dCD – ᎏᎏ cyy2dy day Many contributions, but often negligible � Ss (ii) fin contribution � � C Roll damping wing effects dominate but fin and tailplane contribute � s l l a1FVF ᎏF � – ᎏF Nv(fin) � ᎏ ᎏ b b Yaw damping, for large aspect ratio rectangular wing, wing contribution is approximately CD/6 251 252 Aeronautical Engineer’s Data Book Table A3.3 Longitudinal aerodynamic control derivatives Small perturbation derivatives referred to aircraft wind axes Derivative Description Expression Comments X␩ Axial force due to elevator ST – ᎏᎏ kTCLTa2 S Usually insignificantly small Z␩ Normal force due to elevator ST – ᎏᎏ a2 S M␩ Pitching moment due to elevator – �Ta2 V Principal measure of pitch control power Appendix 4: Compressible flow tables Table A4.1 Subsonic flow (isentropic flow, ␥ = 7/5) Notation: M = Local flow Mach number P/Po = Ratio of static pressure to total pressure ␳/␳o = Ratio of local flow density to stagnation density T/To = Ratio of static temperature to total temperature ␤ = (1 – M2) = Compressibility factor V/a* = Local velocity/speed of sound at sonic point q/Po = Dynamic pressure/total pressure A/A* = Local flow area/flow area at sonic point M P/Po ␳/␳o T/To ␤ q/Po A/A* V/a* 0.00 0.01 0.02 0.03 0.04 0.05 0.06 0.07 0.08 0.09 0.10 0.11 0.12 0.13 0.14 0.15 0.16 0.17 0.18 0.19 0.20 0.21 0.22 0.23 0.24 0.25 0.26 0.27 0.28 0.29 0.30 1.0000 0.9999 0.9997 0.9994 0.9989 0.9983 0.9975 0.9966 0.9955 0.9944 0.9930 0.9916 0.9900 0.9883 0.9864 0.9844 0.9823 0.9800 0.9776 0.9751 0.9725 0.9697 0.9668 0.9638 0.9607 0.9575 0.9541 0.9506 0.9470 0.9433 0.9395 1.0000 1.0000 0.9998 0.9996 0.9992 0.9988 0.9982 0.9976 0.9968 0.9960 0.9950 0.9940 0.9928 0.9916 0.9903 0.9888 0.9873 0.9857 0.9840 0.9822 0.9803 0.9783 0.9762 0.9740 0.9718 0.9694 0.9670 0.9645 0.9619 0.9592 0.9564 1.0000 1.0000 0.9999 0.9998 0.9997 0.9995 0.9993 0.9990 0.9987 0.9984 0.9980 0.9976 0.9971 0.9966 0.9961 0.9955 0.9949 0.9943 0.9936 0.9928 0.9921 0.9913 0.9904 0.9895 0.9886 0.9877 0.9867 0.9856 0.9846 0.9835 0.9823 1.0000 0.9999 0.9998 0.9995 0.9992 0.9987 0.9982 0.9975 0.9968 0.9959 0.9950 0.9939 0.9928 0.9915 0.9902 0.9887 0.9871 0.9854 0.9837 0.9818 0.9798 0.9777 0.9755 0.9732 0.9708 0.9682 0.9656 0.9629 0.9600 0.9570 0.9539 0.0000 7.000e–5 2.799e–4 6.296e–4 1.119e–3 1.747e–3 2.514e–3 3.418e–3 4.460e–3 5.638e–3 6.951e–3 8.399e–3 9.979e–3 1.169e–2 1.353e–2 1.550e–2 1.760e–2 1.983e–2 2.217e–2 2.464e–2 2.723e–2 2.994e–2 3.276e–2 3.569e–2 3.874e–2 4.189e–2 4.515e–2 4.851e–2 5.197e–2 5.553e–2 5.919e–2 – 57.8738 28.9421 19.3005 14.4815 11.5914 9.6659 8.2915 7.2616 6.4613 5.8218 5.2992 4.8643 4.4969 4.1824 3.9103 3.6727 3.4635 3.2779 3.1123 2.9635 2.8293 2.7076 2.5968 2.4956 2.4027 2.3173 2.2385 2.1656 2.0979 2.0351 0.0000 0.0110 0.0219 0.0329 0.0438 0.0548 0.0657 0.0766 0.0876 0.0985 0.1094 0.1204 0.1313 0.1422 0.1531 0.1639 0.1748 0.1857 0.1965 0.2074 0.2182 0.2290 0.2398 0.2506 0.2614 0.2722 0.2829 0.2936 0.3043 0.3150 0.3257 254 Aeronautical Engineer’s Data Book Table A4.1 Continued M P/Po ␳/␳o T/To ␤ q/Po 0.31 0.32 0.33 0.34 0.35 0.36 0.37 0.38 0.39 0.40 0.41 0.42 0.43 0.44 0.45 0.46 0.47 0.48 0.49 0.50 0.51 0.52 0.53 0.54 0.55 0.56 0.57 0.58 0.59 0.60 0.61 0.62 0.63 0.64 0.65 0.66 0.67 0.68 0.69 0.70 0.71 0.72 0.73 0.74 0.75 0.76 0.77 0.78 0.79 0.80 0.81 0.82 0.83 0.84 0.85 0.86 0.9355 0.9315 0.9274 0.9231 0.9188 0.9143 0.9098 0.9052 0.9004 0.8956 0.8907 0.8857 0.8807 0.8755 0.8703 0.8650 0.8596 0.8541 0.8486 0.8430 0.8374 0.8317 0.8259 0.8201 0.8142 0.8082 0.8022 0.7962 0.7901 0.7840 0.7778 0.7716 0.7654 0.7591 0.7528 0.7465 0.7401 0.7338 0.7274 0.7209 0.7145 0.7080 0.7016 0.6951 0.6886 0.6821 0.6756 0.6691 0.6625 0.6560 0.6495 0.6430 0.6365 0.6300 0.6235 0.6170 0.9535 0.9506 0.9476 0.9445 0.9413 0.9380 0.9347 0.9313 0.9278 0.9243 0.9207 0.9170 0.9132 0.9094 0.9055 0.9016 0.8976 0.8935 0.8894 0.8852 0.8809 0.8766 0.8723 0.8679 0.8634 0.8589 0.8544 0.8498 0.8451 0.8405 0.8357 0.8310 0.8262 0.8213 0.8164 0.8115 0.8066 0.8016 0.7966 0.7916 0.7865 0.7814 0.7763 0.7712 0.7660 0.7609 0.7557 0.7505 0.7452 0.7400 0.7347 0.7295 0.7242 0.7189 0.7136 0.7083 0.9811 0.9799 0.9787 0.9774 0.9761 0.9747 0.9733 0.9719 0.9705 0.9690 0.9675 0.9659 0.9643 0.9627 0.9611 0.9594 0.9577 0.9559 0.9542 0.9524 0.9506 0.9487 0.9468 0.9449 0.9430 0.9410 0.9390 0.9370 0.9349 0.9328 0.9307 0.9286 0.9265 0.9243 0.9221 0.9199 0.9176 0.9153 0.9131 0.9107 0.9084 0.9061 0.9037 0.9013 0.8989 0.8964 0.8940 0.8915 0.8890 0.8865 0.8840 0.8815 0.8789 0.8763 0.8737 0.8711 0.9507 0.9474 0.9440 0.9404 0.9367 0.9330 0.9290 0.9250 0.9208 0.9165 0.9121 0.9075 0.9028 0.8980 0.8930 0.8879 0.8827 0.8773 0.8717 0.8660 0.8602 0.8542 0.8480 0.8417 0.8352 0.8285 0.8216 0.8146 0.8074 0.8000 0.7924 0.7846 0.7766 0.7684 0.7599 0.7513 0.7424 0.7332 0.7238 0.7141 0.7042 0.6940 0.6834 0.6726 0.6614 0.6499 0.6380 0.6258 0.6131 0.6000 0.5864 0.5724 0.5578 0.5426 0.5268 0.5103 6.293e–2 6.677e–2 7.069e–2 7.470e–2 7.878e–2 8.295e–2 8.719e–2 9.149e–2 9.587e–2 0.1003 0.1048 0.1094 0.1140 0.1186 0.1234 0.1281 0.1329 0.1378 0.1426 0.1475 0.1525 0.1574 0.1624 0.1674 0.1724 0.1774 0.1825 0.1875 0.1925 0.1976 0.2026 0.2076 0.2127 0.2177 0.2226 0.2276 0.2326 0.2375 0.2424 0.2473 0.2521 0.2569 0.2617 0.2664 0.2711 0.2758 0.2804 0.2849 0.2894 0.2939 0.2983 0.3026 0.3069 0.3112 0.3153 0.3195 A/A* 1.9765 1.9219 1.8707 1.8229 1.7780 1.7358 1.6961 1.6587 1.6234 1.5901 1.5587 1.5289 1.5007 1.4740 1.4487 1.4246 1.4018 1.3801 1.3595 1.3398 1.3212 1.3034 1.2865 1.2703 1.2549 1.2403 1.2263 1.2130 1.2003 1.1882 1.1767 1.1656 1.1552 1.1451 1.1356 1.1265 1.1179 1.1097 1.1018 1.0944 1.0873 1.0806 1.0742 1.0681 1.0624 1.0570 1.0519 1.0471 1.0425 1.0382 1.0342 1.0305 1.0270 1.0237 1.0207 1.0179 V/a* 0.3364 0.3470 0.3576 0.3682 0.3788 0.3893 0.3999 0.4104 0.4209 0.4313 0.4418 0.4522 0.4626 0.4729 0.4833 0.4936 0.5038 0.5141 0.5243 0.5345 0.5447 0.5548 0.5649 0.5750 0.5851 0.5951 0.6051 0.6150 0.6249 0.6348 0.6447 0.6545 0.6643 0.6740 0.6837 0.6934 0.7031 0.7127 0.7223 0.7318 0.7413 0.7508 0.7602 0.7696 0.7789 0.7883 0.7975 0.8068 0.8160 0.8251 0.8343 0.8433 0.8524 0.8614 0.8704 0.8793 Appendix 255 Table A4.1 Continued M P/Po ␳/␳o T/To ␤ q/Po 0.87 0.88 0.89 0.90 0.91 0.92 0.93 0.94 0.95 0.96 0.97 0.98 0.99 0.6106 0.6041 0.5977 0.5913 0.5849 0.5785 0.5721 0.5658 0.5595 0.5532 0.5469 0.5407 0.5345 0.7030 0.6977 0.6924 0.6870 0.6817 0.6764 0.6711 0.6658 0.6604 0.6551 0.6498 0.6445 0.6392 0.8685 0.8659 0.8632 0.8606 0.8579 0.8552 0.8525 0.8498 0.8471 0.8444 0.8416 0.8389 0.8361 0.4931 0.4750 0.4560 0.4359 0.4146 0.3919 0.3676 0.3412 0.3122 0.2800 0.2431 0.1990 0.1411 0.3235 0.3275 0.3314 0.3352 0.3390 0.3427 0.3464 0.3499 0.3534 0.3569 0.3602 0.3635 0.3667 A/A* 1.0153 1.0129 1.0108 1.0089 1.0071 1.0056 1.0043 1.0031 1.0021 1.0014 1.0008 1.0003 1.0001 V/a* 0.8882 0.8970 0.9058 0.9146 0.9233 0.9320 0.9407 0.9493 0.9578 0.9663 0.9748 0.9833 0.9916 Table A4.2 Supersonic flow (isentropic flow, ␥ = 7/5) Notation: M = Local flow Mach number P/Po = Ratio of static pressure to total pressure ␳/␳o = Ratio of local flow density to stagnation density (r/ro) T/To = Ratio of static temperature to total temperature ␤ = ͙ෆ2ෆ = Compressibility factor 1–M V/a* = Local velocity/speed of sound at sonic point q/Po = Dynamic pressure/total pressure A/A* = Local flow area/flow area at sonic point M P/Po ␳/␳o T/To ␤ q/Po A/A* V/a* 1.00 1.01 1.02 1.03 1.04 1.05 1.06 1.07 1.08 1.09 1.10 1.11 1.12 1.13 1.14 1.15 1.16 1.17 1.18 1.19 1.20 1.21 1.22 0.5283 0.5221 0.5160 0.5099 0.5039 0.4979 0.4919 0.4860 0.4800 0.4742 0.4684 0.4626 0.4568 0.4511 0.4455 0.4398 0.4343 0.4287 0.4232 0.4178 0.4124 0.4070 0.4017 0.6339 0.6287 0.6234 0.6181 0.6129 0.6077 0.6024 0.5972 0.5920 0.5869 0.5817 0.5766 0.5714 0.5663 0.5612 0.5562 0.5511 0.5461 0.5411 0.5361 0.5311 0.5262 0.5213 0.8333 0.8306 0.8278 0.8250 0.8222 0.8193 0.8165 0.8137 0.8108 0.8080 0.8052 0.8023 0.7994 0.7966 0.7937 0.7908 0.7879 0.7851 0.7822 0.7793 0.7764 0.7735 0.7706 0.0000 0.1418 0.2010 0.2468 0.2857 0.3202 0.3516 0.3807 0.4079 0.4337 0.4583 0.4818 0.5044 0.5262 0.5474 0.5679 0.5879 0.6074 0.6264 0.6451 0.6633 0.6812 0.6989 0.3698 0.3728 0.3758 0.3787 0.3815 0.3842 0.3869 0.3895 0.3919 0.3944 0.3967 0.3990 0.4011 0.4032 0.4052 0.4072 0.4090 0.4108 0.4125 0.4141 0.4157 0.4171 0.4185 1.0000 1.0001 1.0003 1.000 1.0013 1.0020 1.0029 1.0039 1.0051 1.0064 1.0079 1.0095 1.0113 1.0132 1.0153 1.0175 1.0198 1.0222 1.0248 1.0276 1.0304 1.0334 1.0366 1.0000 1.0083 1.0166 1.0248 1.0330 1.0411 1.0492 1.0573 1.0653 1.0733 1.0812 1.0891 1.0970 1.1048 1.1126 1.1203 1.1280 1.1356 1.1432 1.1508 1.1583 1.1658 1.1732 256 Aeronautical Engineer’s Data Book Table A4.2 Continued M P/Po ␳/␳o T/To ␤ q/Po A/A* V/a* 1.23 1.24 1.25 1.26 1.27 1.28 1.29 1.30 1.31 1.32 1.33 1.34 1.35 1.36 1.37 1.38 1.39 1.40 1.41 1.42 1.43 1.44 1.45 1.46 1.47 1.48 1.49 1.50 1.51 1.52 1.53 1.54 1.55 1.56 1.57 1.58 1.59 1.60 1.61 1.62 1.63 1.64 1.65 1.66 1.67 1.68 1.69 1.70 1.71 1.72 1.73 1.74 1.75 1.76 1.77 1.78 0.3964 0.3912 0.3861 0.3809 0.3759 0.3708 0.3658 0.3609 0.3560 0.3512 0.3464 0.3417 0.3370 0.3323 0.3277 0.3232 0.3187 0.3142 0.3098 0.3055 0.3012 0.2969 0.2927 0.2886 0.2845 0.2804 0.2764 0.2724 0.2685 0.2646 0.2608 0.2570 0.2533 0.2496 0.2459 0.2423 0.2388 0.2353 0.2318 0.2284 0.2250 0.2217 0.2184 0.2151 0.2119 0.2088 0.2057 0.2026 0.1996 0.1966 0.1936 0.1907 0.1878 0.1850 0.1822 0.1794 0.5164 0.5115 0.5067 0.5019 0.4971 0.4923 0.4876 0.4829 0.4782 0.4736 0.4690 0.4644 0.4598 0.4553 0.4508 0.4463 0.4418 0.4374 0.4330 0.4287 0.4244 0.4201 0.4158 0.4116 0.4074 0.4032 0.3991 0.3950 0.3909 0.3869 0.3829 0.3789 0.3750 0.3710 0.3672 0.3633 0.3595 0.3557 0.3520 0.3483 0.3446 0.3409 0.3373 0.3337 0.3302 0.3266 0.3232 0.3197 0.3163 0.3129 0.3095 0.3062 0.3029 0.2996 0.2964 0.2931 0.7677 0.7648 0.7619 0.7590 0.7561 0.7532 0.7503 0.7474 0.7445 0.7416 0.7387 0.7358 0.7329 0.7300 0.7271 0.7242 0.7213 0.7184 0.7155 0.7126 0.7097 0.7069 0.7040 0.7011 0.6982 0.6954 0.6925 0.6897 0.6868 0.6840 0.6811 0.6783 0.6754 0.6726 0.6698 0.6670 0.6642 0.6614 0.6586 0.6558 0.6530 0.6502 0.6475 0.6447 0.6419 0.6392 0.6364 0.6337 0.6310 0.6283 0.6256 0.6229 0.6202 0.6175 0.6148 0.6121 0.7162 0.7332 0.7500 0.7666 0.7829 0.7990 0.8149 0.8307 0.8462 0.8616 0.8769 0.8920 0.9069 0.9217 0.9364 0.9510 0.9655 0.9798 0.9940 1.0082 1.0222 1.0361 1.0500 1.0638 1.0775 1.0911 1.1046 1.1180 1.1314 1.1447 1.1580 1.1712 1.1843 1.1973 1.2103 1.2233 1.2362 1.2490 1.2618 1.2745 1.2872 1.2998 1.3124 1.3250 1.3375 1.3500 1.3624 1.3748 1.3871 1.3994 1.4117 1.4239 1.4361 1.4483 1.4604 1.4725 0.4198 0.4211 0.4223 0.4233 0.4244 0.4253 0.4262 0.4270 0.4277 0.4283 0.4289 0.4294 0.4299 0.4303 0.4306 0.4308 0.4310 0.4311 0.4312 0.4312 0.4311 0.4310 0.4308 0.4306 0.4303 0.4299 0.4295 0.4290 0.4285 0.4279 0.4273 0.4266 0.4259 0.4252 0.4243 0.4235 0.4226 0.4216 0.4206 0.4196 0.4185 0.4174 0.4162 0.4150 0.4138 0.4125 0.4112 0.4098 0.4085 0.4071 0.4056 0.4041 0.4026 0.4011 0.3996 0.3980 1.0398 1.0432 1.0468 1.0504 1.0542 1.0581 1.0621 1.0663 1.0706 1.0750 1.0796 1.0842 1.0890 1.0940 1.0990 1.1042 1.1095 1.1149 1.1205 1.1262 1.1320 1.1379 1.1440 1.1501 1.1565 1.1629 1.1695 1.1762 1.1830 1.1899 1.1970 1.2042 1.2116 1.2190 1.2266 1.2344 1.2422 1.2502 1.2584 1.2666 1.2750 1.2836 1.2922 1.3010 1.3100 1.3190 1.3283 1.3376 1.3471 1.3567 1.3665 1.3764 1.3865 1.3967 1.4070 1.4175 1.1806 1.1879 1.1952 1.2025 1.2097 1.2169 1.2240 1.2311 1.2382 1.2452 1.2522 1.2591 1.2660 1.2729 1.2797 1.2864 1.2932 1.2999 1.3065 1.3131 1.3197 1.3262 1.3327 1.3392 1.3456 1.3520 1.3583 1.3646 1.3708 1.3770 1.3832 1.3894 1.3955 1.4015 1.4075 1.4135 1.4195 1.4254 1.4313 1.4371 1.4429 1.4487 1.4544 1.4601 1.4657 1.4713 1.4769 1.4825 1.4880 1.4935 1.4989 1.5043 1.5097 1.5150 1.5203 1.5256 Appendix 257 Table A4.2 Continued M P/Po ␳/␳o T/To ␤ q/Po A/A* V/a* 1.79 1.80 1.81 1.82 1.83 1.84 1.85 1.86 1.87 1.88 1.89 1.90 1.91 1.92 1.93 1.94 1.95 1.96 1.97 1.98 1.99 2.00 2.01 2.02 2.03 2.04 2.05 2.06 2.07 2.08 2.09 2.10 2.11 2.12 2.13 2.14 2.15 2.16 2.17 2.18 2.19 2.20 2.21 2.22 2.23 2.24 2.25 2.26 2.27 2.28 2.29 2.30 2.31 2.32 2.33 2.34 0.1767 0.1740 0.1714 0.1688 0.1662 0.1637 0.1612 0.1587 0.1563 0.1539 0.1516 0.1492 0.1470 0.1447 0.1425 0.1403 0.1381 0.1360 0.1339 0.1318 0.1298 0.1278 0.1258 0.1239 0.1220 0.1201 0.1182 0.1164 0.1146 0.1128 0.1111 0.1094 0.1077 0.1060 0.1043 0.1027 0.1011 9.956e–2 9.802e–2 9.649e–2 9.500e–2 9.352e–2 9.207e–2 9.064e–2 8.923e–2 8.785e–2 8.648e–2 8.514e–2 8.382e–2 8.251e–2 8.123e–2 7.997e–2 7.873e–2 7.751e–2 7.631e–2 7.512e–2 0.2900 0.2868 0.2837 0.2806 0.2776 0.2745 0.2715 0.2686 0.2656 0.2627 0.2598 0.2570 0.2542 0.2514 0.2486 0.2459 0.2432 0.2405 0.2378 0.2352 0.2326 0.2300 0.2275 0.2250 0.2225 0.2200 0.2176 0.2152 0.2128 0.2104 0.2081 0.2058 0.2035 0.2013 0.1990 0.1968 0.1946 0.1925 0.1903 0.1882 0.1861 0.1841 0.1820 0.1800 0.1780 0.1760 0.1740 0.1721 0.1702 0.1683 0.1664 0.1646 0.1628 0.1609 0.1592 0.1574 0.6095 0.6068 0.6041 0.6015 0.5989 0.5963 0.5936 0.5910 0.5884 0.5859 0.5833 0.5807 0.5782 0.5756 0.5731 0.5705 0.5680 0.5655 0.5630 0.5605 0.5580 0.5556 0.5531 0.5506 0.5482 0.5458 0.5433 0.5409 0.5385 0.5361 0.5337 0.5313 0.5290 0.5266 0.5243 0.5219 0.5196 0.5173 0.5150 0.5127 0.5104 0.5081 0.5059 0.5036 0.5014 0.4991 0.4969 0.4947 0.4925 0.4903 0.4881 0.4859 0.4837 0.4816 0.4794 0.4773 1.4846 1.4967 1.5087 1.5207 1.5326 1.5445 1.5564 1.5683 1.5802 1.5920 1.6038 1.6155 1.6273 1.6390 1.6507 1.6624 1.6741 1.6857 1.6973 1.7089 1.7205 1.7321 1.7436 1.7551 1.7666 1.7781 1.7896 1.8010 1.8124 1.8238 1.8352 1.8466 1.8580 1.8693 1.8807 1.8920 1.9033 1.9146 1.9259 1.9371 1.9484 1.9596 1.9708 1.9820 1.9932 2.0044 2.0156 2.0267 2.0379 2.0490 2.0601 2.0712 2.0823 2.0934 2.1045 2.1156 0.3964 0.3947 0.3931 0.3914 0.3897 0.3879 0.3862 0.3844 0.3826 0.3808 0.3790 0.3771 0.3753 0.3734 0.3715 0.3696 0.3677 0.3657 0.3638 0.3618 0.3598 0.3579 0.3559 0.3539 0.3518 0.3498 0.3478 0.3458 0.3437 0.3417 0.3396 0.3376 0.3355 0.3334 0.3314 0.3293 0.3272 0.3252 0.3231 0.3210 0.3189 0.3169 0.3148 0.3127 0.3106 0.3085 0.3065 0.3044 0.3023 0.3003 0.2982 0.2961 0.2941 0.2920 0.2900 0.2879 1.4282 1.4390 1.4499 1.4610 1.4723 1.4836 1.4952 1.5069 1.5187 1.5308 1.5429 1.5553 1.5677 1.5804 1.5932 1.6062 1.6193 1.6326 1.6461 1.6597 1.6735 1.6875 1.7016 1.7160 1.7305 1.7451 1.7600 1.7750 1.7902 1.8056 1.8212 1.8369 1.8529 1.8690 1.8853 1.9018 1.9185 1.9354 1.9525 1.9698 1.9873 2.0050 2.0229 2.0409 2.0592 2.0777 2.0964 2.1153 2.1345 2.1538 2.1734 2.1931 2.2131 2.2333 2.2538 2.2744 1.5308 1.5360 1.5411 1.5463 1.5514 1.5564 1.5614 1.5664 1.5714 1.5763 1.5812 1.5861 1.5909 1.5957 1.6005 1.6052 1.6099 1.6146 1.6192 1.6239 1.6284 1.6330 1.6375 1.6420 1.6465 1.6509 1.6553 1.6597 1.6640 1.6683 1.6726 1.6769 1.6811 1.6853 1.6895 1.6936 1.6977 1.7018 1.7059 1.7099 1.7139 1.7179 1.7219 1.7258 1.7297 1.7336 1.7374 1.7412 1.7450 1.7488 1.7526 1.7563 1.7600 1.7637 1.7673 1.7709 258 Aeronautical Engineer’s Data Book Table A4.2 Continued M P/Po ␳/␳o T/To ␤ q/Po A/A* V/a* 2.35 2.36 2.37 2.38 2.39 2.40 2.41 2.42 2.43 2.44 2.45 2.46 2.47 2.48 2.49 2.50 2.51 2.52 2.53 2.54 2.55 2.56 2.57 2.58 2.59 2.60 2.61 2.62 2.63 2.64 2.65 2.66 2.67 2.68 2.69 2.70 2.71 2.72 2.73 2.74 2.75 2.76 2.77 2.78 2.79 2.80 2.81 2.82 2.83 2.84 2.85 2.86 2.87 2.88 2.89 2.90 7.396e–2 7.281e–2 7.168e–2 7.057e–2 6.948e–2 6.840e–2 6.734e–2 6.630e–2 6.527e–2 6.426e–2 6.327e–2 6.229e–2 6.133e–2 6.038e–2 5.945e–2 5.853e–2 5.762e–2 5.674e–2 5.586e–2 5.500e–2 5.415e–2 5.332e–2 5.250e–2 5.169e–2 5.090e–2 5.012e–2 4.935e–2 4.859e–2 4.784e–2 4.711e–2 4.639e–2 4.568e–2 4.498e–2 4.429e–2 4.362e–2 4.295e–2 4.229e–2 4.165e–2 4.102e–2 4.039e–2 3.978e–2 3.917e–2 3.858e–2 3.799e–2 3.742e–2 3.685e–2 3.629e–2 3.574e–2 3.520e–2 3.467e–2 3.415e–2 3.363e–2 3.312e–2 3.263e–2 3.213e–2 3.165e–2 0.1556 0.1539 0.1522 0.1505 0.1488 0.1472 0.1456 0.1439 0.1424 0.1408 0.1392 0.1377 0.1362 0.1346 0.1332 0.1317 0.1302 0.1288 0.1274 0.1260 0.1246 0.1232 0.1218 0.1205 0.1192 0.1179 0.1166 0.1153 0.1140 0.1128 0.1115 0.1103 0.1091 0.1079 0.1067 0.1056 0.1044 0.1033 0.1022 0.1010 9.994e–2 9.885e–2 9.778e–2 9.671e–2 9.566e–2 9.463e–2 9.360e–2 9.259e–2 9.158e–2 9.059e–2 8.962e–2 8.865e–2 8.769e–2 8.675e–2 8.581e–2 8.489e–2 0.4752 0.4731 0.4709 0.4688 0.4668 0.4647 0.4626 0.4606 0.4585 0.4565 0.4544 0.4524 0.4504 0.4484 0.4464 0.4444 0.4425 0.4405 0.4386 0.4366 0.4347 0.4328 0.4309 0.4289 0.4271 0.4252 0.4233 0.4214 0.4196 0.4177 0.4159 0.4141 0.4122 0.4104 0.4086 0.4068 0.4051 0.4033 0.4015 0.3998 0.3980 0.3963 0.3945 0.3928 0.3911 0.3894 0.3877 0.3860 0.3844 0.3827 0.3810 0.3794 0.3777 0.3761 0.3745 0.3729 2.1266 2.1377 2.1487 2.1597 2.1707 2.1817 2.1927 2.2037 2.2147 2.2257 2.2366 2.2476 2.2585 2.2694 2.2804 2.2913 2.3022 2.3131 2.3240 2.3349 2.3457 2.3566 2.3675 2.3783 2.3892 2.4000 2.4108 2.4217 2.4325 2.4433 2.4541 2.4649 2.4757 2.4864 2.4972 2.5080 2.5187 2.5295 2.5403 2.5510 2.5617 2.5725 2.5832 2.5939 2.6046 2.6153 2.6260 2.6367 2.6474 2.6581 2.6688 2.6795 2.6901 2.7008 2.7115 2.7221 0.2859 0.2839 0.2818 0.2798 0.2778 0.2758 0.2738 0.2718 0.2698 0.2678 0.2658 0.2639 0.2619 0.2599 0.2580 0.2561 0.2541 0.2522 0.2503 0.2484 0.2465 0.2446 0.2427 0.2409 0.2390 0.2371 0.2353 0.2335 0.2317 0.2298 0.2280 0.2262 0.2245 0.2227 0.2209 0.2192 0.2174 0.2157 0.2140 0.2123 0.2106 0.2089 0.2072 0.2055 0.2039 0.2022 0.2006 0.1990 0.1973 0.1957 0.1941 0.1926 0.1910 0.1894 0.1879 0.1863 2.2953 2.3164 2.3377 2.3593 2.3811 2.4031 2.4254 2.4479 2.4706 2.4936 2.5168 2.5403 2.5640 2.5880 2.6122 2.6367 2.6615 2.6865 2.7117 2.7372 2.7630 2.7891 2.8154 2.8420 2.8688 2.8960 2.9234 2.9511 2.9791 3.0073 3.0359 3.0647 3.0938 3.1233 3.1530 3.1830 3.2133 3.2440 3.2749 3.3061 3.3377 3.3695 3.4017 3.4342 3.4670 3.5001 3.5336 3.5674 3.6015 3.6359 3.6707 3.7058 3.7413 3.7771 3.8133 3.8498 1.7745 1.7781 1.7817 1.7852 1.7887 1.7922 1.7956 1.7991 1.8025 1.8059 1.8092 1.8126 1.8159 1.8192 1.8225 1.8257 1.8290 1.8322 1.8354 1.8386 1.8417 1.8448 1.8479 1.8510 1.8541 1.8571 1.8602 1.8632 1.8662 1.8691 1.8721 1.8750 1.8779 1.8808 1.8837 1.8865 1.8894 1.8922 1.8950 1.8978 1.9005 1.9033 1.9060 1.9087 1.9114 1.9140 1.9167 1.9193 1.9219 1.9246 1.9271 1.9297 1.9323 1.9348 1.9373 1.9398 Appendix 259 Table A4.2 Continued M P/Po ␳/␳o T/To ␤ q/Po A/A* V/a* 2.91 2.92 2.93 2.94 2.95 2.96 2.97 2.98 2.99 3.00 3.02 3.04 3.06 3.08 3.10 3.12 3.14 3.16 3.18 3.20 3.22 3.24 3.26 3.28 3.30 3.32 3.34 3.36 3.38 3.40 3.42 3.44 3.46 3.48 3.50 3.52 3.54 3.56 3.58 3.60 3.62 3.64 3.66 3.68 3.70 3.72 3.74 3.76 3.78 3.80 3.82 3.84 3.86 3.88 3.90 3.92 3.118e–2 3.071e–2 3.025e–2 2.980e–2 2.935e–2 2.891e–2 2.848e–2 2.805e–2 2.764e–2 2.722e–2 2.642e–2 2.564e–2 2.489e–2 2.416e–2 2.345e–2 2.276e–2 2.210e–2 2.146e–2 2.083e–2 2.023e–2 1.964e–2 1.908e–2 1.853e–2 1.799e–2 1.748e–2 1.698e–2 1.649e–2 1.602e–2 1.557e–2 1.512e–2 1.470e–2 1.428e–2 1.388e–2 1.349e–2 1.311e–2 1.274e–2 1.239e–2 1.204e–2 1.171e–2 1.138e–2 1.107e–2 1.076e–2 1.047e–2 1.018e–2 9.903e–3 9.633e–3 9.370e–3 9.116e–3 8.869e–3 8.629e–3 8.396e–3 8.171e–3 7.951e–3 7.739e–3 7.532e–3 7.332e–3 8.398e–2 8.307e–2 8.218e–2 8.130e–2 8.043e–2 7.957e–2 7.872e–2 7.788e–2 7.705e–2 7.623e–2 7.461e–2 7.303e–2 7.149e–2 6.999e–2 6.852e–2 6.708e–2 6.568e–2 6.430e–2 6.296e–2 6.165e–2 6.037e–2 5.912e–2 5.790e–2 5.671e–2 5.554e–2 5.440e–2 5.329e–2 5.220e–2 5.113e–2 5.009e–2 4.908e–2 4.808e–2 4.711e–2 4.616e–2 4.523e–2 4.433e–2 4.344e–2 4.257e–2 4.172e–2 4.089e–2 4.008e–2 3.929e–2 3.852e–2 3.776e–2 3.702e–2 3.629e–2 3.558e–2 3.489e–2 3.421e–2 3.355e–2 3.290e–2 3.227e–2 3.165e–2 3.104e–2 3.044e–2 2.986e–2 0.3712 0.3696 0.3681 0.3665 0.3649 0.3633 0.3618 0.3602 0.3587 0.3571 0.3541 0.3511 0.3481 0.3452 0.3422 0.3393 0.3365 0.3337 0.3309 0.3281 0.3253 0.3226 0.3199 0.3173 0.3147 0.3121 0.3095 0.3069 0.3044 0.3019 0.2995 0.2970 0.2946 0.2922 0.2899 0.2875 0.2852 0.2829 0.2806 0.2784 0.2762 0.2740 0.2718 0.2697 0.2675 0.2654 0.2633 0.2613 0.2592 0.2572 0.2552 0.2532 0.2513 0.2493 0.2474 0.2455 2.7328 2.7434 2.7541 2.7647 2.7753 2.7860 2.7966 2.8072 2.8178 2.8284 2.8496 2.8708 2.8920 2.9131 2.9343 2.9554 2.9765 2.9976 3.0187 3.0397 3.0608 3.0818 3.1028 3.1238 3.1448 3.1658 3.1868 3.2077 3.2287 3.2496 3.2705 3.2914 3.3123 3.3332 3.3541 3.3750 3.3958 3.4167 3.4375 3.4583 3.4791 3.4999 3.5207 3.5415 3.5623 3.5831 3.6038 3.6246 3.6453 3.6661 3.6868 3.7075 3.7282 3.7489 3.7696 3.7903 0.1848 0.1833 0.1818 0.1803 0.1788 0.1773 0.1758 0.1744 0.1729 0.1715 0.1687 0.1659 0.1631 0.1604 0.1577 0.1551 0.1525 0.1500 0.1475 0.1450 0.1426 0.1402 0.1378 0.1355 0.1332 0.1310 0.1288 0.1266 0.1245 0.1224 0.1203 0.1183 0.1163 0.1144 0.1124 0.1105 0.1087 0.1068 0.1050 0.1033 0.1015 9.984e–2 9.816e–2 9.652e–2 9.490e–2 9.331e–2 9.175e–2 9.021e–2 8.870e–2 8.722e–2 8.577e–2 8.434e–2 8.293e–2 8.155e–2 8.019e–2 7.886e–2 3.8866 3.9238 3.9614 3.9993 4.0376 4.0763 4.1153 4.1547 4.1944 4.2346 4.3160 4.3989 4.4835 4.5696 4.6573 4.7467 4.8377 4.9304 5.0248 5.1210 5.2189 5.3186 5.4201 5.5234 5.6286 5.7358 5.8448 5.9558 6.0687 6.1837 6.3007 6.4198 6.5409 6.6642 6.7896 6.9172 7.0471 7.1791 7.3135 7.4501 7.5891 7.7305 7.8742 8.0204 8.1691 8.3202 8.4739 8.6302 8.7891 8.9506 9.1148 9.2817 9.4513 9.6237 9.7990 9.9771 1.9423 1.9448 1.9472 1.9497 1.9521 1.9545 1.9569 1.9593 1.9616 1.9640 1.9686 1.9732 1.9777 1.9822 1.9866 1.9910 1.9953 1.9995 2.0037 2.0079 2.0119 2.0160 2.0200 2.0239 2.0278 2.0317 2.0355 2.0392 2.0429 2.0466 2.0502 2.0537 2.0573 2.0607 2.0642 2.0676 2.0709 2.0743 2.0775 2.0808 2.0840 2.0871 2.0903 2.0933 2.0964 2.0994 2.1024 2.1053 2.1082 2.1111 2.1140 2.1168 2.1195 2.1223 2.1250 2.1277 260 Aeronautical Engineer’s Data Book Table A4.2 Continued M P/Po ␳/␳o T/To ␤ q/Po A/A* V/a* 3.94 3.96 3.98 4.00 4.04 4.08 4.12 4.16 4.20 4.24 4.28 4.32 4.36 4.40 4.44 4.48 4.52 4.56 4.60 4.64 4.68 4.72 4.76 4.80 4.84 4.88 4.92 4.96 5.00 5.10 5.20 5.30 5.40 5.50 5.60 5.70 5.80 5.90 6.00 7.137e–3 6.948e–3 6.764e–3 6.586e–3 6.245e–3 5.923e–3 5.619e–3 5.333e–3 5.062e–3 4.806e–3 4.565e–3 4.337e–3 4.121e–3 3.918e–3 3.725e–3 3.543e–3 3.370e–3 3.207e–3 3.053e–3 2.906e–3 2.768e–3 2.637e–3 2.512e–3 2.394e–3 2.283e–3 2.177e–3 2.076e–3 1.981e–3 1.890e–3 1.683e–3 1.501e–3 1.341e–3 1.200e–3 1.075e–3 9.643e–4 8.663e–4 7.794e–4 7.021e–4 6.334e–4 2.929e–2 2.874e–2 2.819e–2 2.766e–2 2.663e–2 2.564e–2 2.470e–2 2.379e–2 2.292e–2 2.209e–2 2.129e–2 2.052e–2 1.979e–2 1.909e–2 1.841e–2 1.776e–2 1.714e–2 1.654e–2 1.597e–2 1.542e–2 1.489e–2 1.438e–2 1.390e–2 1.343e–2 1.298e–2 1.254e–2 1.213e–2 1.173e–2 1.134e–2 1.044e–2 9.620e–3 8.875e–3 8.197e–3 7.578e–3 7.012e–3 6.496e–3 6.023e–3 5.590e–3 5.194e–3 0.2436 0.2418 0.2399 0.2381 0.2345 0.2310 0.2275 0.2242 0.2208 0.2176 0.2144 0.2113 0.2083 0.2053 0.2023 0.1994 0.1966 0.1938 0.1911 0.1885 0.1859 0.1833 0.1808 0.1783 0.1759 0.1735 0.1712 0.1689 0.1667 0.1612 0.1561 0.1511 0.1464 0.1418 0.1375 0.1334 0.1294 0.1256 0.1220 3.8110 3.8317 3.8523 3.8730 3.9143 3.9556 3.9968 4.0380 4.0792 4.1204 4.1615 4.2027 4.2438 4.2849 4.3259 4.3670 4.4080 4.4490 4.4900 4.5310 4.5719 4.6129 4.6538 4.6947 4.7356 4.7764 4.8173 4.8581 4.8990 5.0010 5.1029 5.2048 5.3066 5.4083 5.5100 5.6116 5.7131 5.8146 5.9161 7.755e–2 7.627e–2 7.500e–2 7.376e–2 7.135e–2 6.902e–2 6.677e–2 6.460e–2 6.251e–2 6.049e–2 5.854e–2 5.666e–2 5.484e–2 5.309e–2 5.140e–2 4.977e–2 4.820e–2 4.668e–2 4.521e–2 4.380e–2 4.243e–2 4.112e–2 3.984e–2 3.861e–2 3.743e–2 3.628e–2 3.518e–2 3.411e–2 3.308e–2 3.065e–2 2.842e–2 2.637e–2 2.449e–2 2.276e–2 2.117e–2 1.970e–2 1.835e–2 1.711e–2 1.596e–2 10.158 10.342 10.528 10.718 11.107 11.509 11.923 12.350 12.791 13.246 13.715 14.198 14.696 15.209 15.738 16.283 16.844 17.422 18.017 18.630 19.260 19.909 20.577 21.263 21.970 22.696 23.443 24.210 25.000 27.069 29.283 31.649 34.174 36.869 39.740 42.797 46.050 49.507 53.179 2.1303 2.1329 2.1355 2.1381 2.1431 2.1480 2.1529 2.1576 2.1622 2.1667 2.1711 2.1754 2.1796 2.1837 2.1877 2.1917 2.1955 2.1993 2.2030 2.2066 2.2102 2.2136 2.2170 2.2204 2.2236 2.2268 2.2300 2.2331 2.2361 2.2433 2.2503 2.2569 2.2631 2.2691 2.2748 2.2803 2.2855 2.2905 2.2953 Appendix 5: Shock wave data Table A5.1 Normal shock wave data Pressure, Mach number and temperature changes through shock waves (␥ = 7/5) Notation: M1 = Mach number of flow upstream of shock wave M2 = Mach number of flow behind the shock wave ␯ = Prandtl–Meyer angle, (deg), for expanding flow at M1 µ = Mach angle, (deg), (sin(–1)(1/M1)) P2/P1 = Static pressure ratio across normal shock wave d2/d1 = Density ratio across normal shock wave T2/T1 = Temperature ratio across normal shock wave Po2/Po1 = Stagnation pressure ratio across normal shock wave M1 ␯ ␮ M2 P2/P1 d2/d1 T2/T1 Po2/Po1 1.00 1.01 1.02 1.03 1.04 1.05 1.06 1.07 1.08 1.09 1.10 1.11 1.12 1.13 1.14 1.15 1.16 1.17 1.18 1.19 1.20 1.21 1.22 1.23 1.24 1.25 0.000 0.045 0.126 0.229 0.351 0.487 0.637 0.797 0.968 1.148 1.336 1.532 1.735 1.944 2.160 2.381 2.607 2.839 3.074 3.314 3.558 3.806 4.057 4.312 4.569 4.830 90.000 81.931 78.635 76.138 74.058 72.247 70.630 69.160 67.808 66.553 65.380 64.277 63.234 62.246 61.306 60.408 59.550 58.727 57.936 57.176 56.443 55.735 55.052 54.391 53.751 53.130 1.0000 0.9901 0.9805 0.9712 0.9620 0.9531 0.9444 0.9360 0.9277 0.9196 0.9118 0.9041 0.8966 0.8892 0.8820 0.8750 0.8682 0.8615 0.8549 0.8485 0.8422 0.8360 0.8300 0.8241 0.8183 0.8126 1.000 1.023 1.047 1.071 1.095 1.120 1.144 1.169 1.194 1.219 1.245 1.271 1.297 1.323 1.350 1.376 1.403 1.430 1.458 1.485 1.513 1.541 1.570 1.598 1.627 1.656 1.0000 1.0167 1.0334 1.0502 1.0671 1.0840 1.1009 1.1179 1.1349 1.1520 1.1691 1.1862 1.2034 1.2206 1.2378 1.2550 1.2723 1.2896 1.3069 1.3243 1.3416 1.3590 1.3764 1.3938 1.4112 1.4286 1.0000 1.0066 1.0132 1.0198 1.0263 1.0328 1.0393 1.0458 1.0522 1.0586 1.0649 1.0713 1.0776 1.0840 1.0903 1.0966 1.1029 1.1092 1.1154 1.1217 1.1280 1.1343 1.1405 1.1468 1.1531 1.1594 1.0000 1.0000 1.0000 1.0000 0.9999 0.9999 0.9998 0.9996 0.9994 0.9992 0.9989 0.9986 0.9982 0.9978 0.9973 0.9967 0.9961 0.9953 0.9946 0.9937 0.9928 0.9918 0.9907 0.9896 0.9884 0.9871 262 Aeronautical Engineer’s Data Book Table A5.1 Continued M1 ␯ ␮ M2 P2/P1 d2/d1 T2/T1 Po2/Po1 1.26 1.27 1.28 1.29 1.30 1.31 1.32 1.33 1.34 1.35 1.36 1.37 1.38 1.39 1.40 1.41 1.42 1.43 1.44 1.45 1.46 1.47 1.48 1.49 1.50 1.51 1.52 1.53 1.54 1.55 1.56 1.57 1.58 1.59 1.60 1.61 1.62 1.63 1.64 1.65 1.66 1.67 1.68 1.69 1.70 1.71 1.72 1.73 1.74 1.75 1.76 1.77 1.78 1.79 1.80 1.81 5.093 5.359 5.627 5.898 6.170 6.445 6.721 7.000 7.279 7.561 7.844 8.128 8.413 8.699 8.987 9.276 9.565 9.855 10.146 10.438 10.731 11.023 11.317 11.611 11.905 12.200 12.495 12.790 13.086 13.381 13.677 13.973 14.269 14.565 14.860 15.156 15.452 15.747 16.043 16.338 16.633 16.928 17.222 17.516 17.810 18.103 18.396 18.689 18.981 19.273 19.565 19.855 20.146 20.436 20.725 21.014 52.528 51.943 51.375 50.823 50.285 49.761 49.251 48.753 48.268 47.795 47.332 46.880 46.439 46.007 45.585 45.171 44.767 44.371 43.983 43.603 43.230 42.865 42.507 42.155 41.810 41.472 41.140 40.813 40.493 40.178 39.868 39.564 39.265 38.971 38.682 38.398 38.118 37.843 37.572 37.305 37.043 36.784 36.530 36.279 36.032 35.789 35.549 35.312 35.080 34.850 34.624 34.400 34.180 33.963 33.749 33.538 0.8071 0.8016 0.7963 0.7911 0.7860 0.7809 0.7760 0.7712 0.7664 0.7618 0.7572 0.7527 0.7483 0.7440 0.7397 0.7355 0.7314 0.7274 0.7235 0.7196 0.7157 0.7120 0.7083 0.7047 0.7011 0.6976 0.6941 0.6907 0.6874 0.6841 0.6809 0.6777 0.6746 0.6715 0.6684 0.6655 0.6625 0.6596 0.6568 0.6540 0.6512 0.6485 0.6458 0.6431 0.6405 0.6380 0.6355 0.6330 0.6305 0.6281 0.6257 0.6234 0.6210 0.6188 0.6165 0.6143 1.686 1.715 1.745 1.775 1.805 1.835 1.866 1.897 1.928 1.960 1.991 2.023 2.055 2.087 2.120 2.153 2.186 2.219 2.253 2.286 2.320 2.354 2.389 2.423 2.458 2.493 2.529 2.564 2.600 2.636 2.673 2.709 2.746 2.783 2.820 2.857 2.895 2.933 2.971 3.010 3.048 3.087 3.126 3.165 3.205 3.245 3.285 3.325 3.366 3.406 3.447 3.488 3.530 3.571 3.613 3.655 1.4460 1.4634 1.4808 1.4983 1.5157 1.5331 1.5505 1.5680 1.5854 1.6028 1.6202 1.6376 1.6549 1.6723 1.6897 1.7070 1.7243 1.7416 1.7589 1.7761 1.7934 1.8106 1.8278 1.8449 1.8621 1.8792 1.8963 1.9133 1.9303 1.9473 1.9643 1.9812 1.9981 2.0149 2.0317 2.0485 2.0653 2.0820 2.0986 2.1152 2.1318 2.1484 2.1649 2.1813 2.1977 2.2141 2.2304 2.2467 2.2629 2.2791 2.2952 2.3113 2.3273 2.3433 2.3592 2.3751 1.1657 1.1720 1.1783 1.1846 1.1909 1.1972 1.2035 1.2099 1.2162 1.2226 1.2290 1.2354 1.2418 1.2482 1.2547 1.2612 1.2676 1.2741 1.2807 1.2872 1.2938 1.3003 1.3069 1.3136 1.3202 1.3269 1.3336 1.3403 1.3470 1.3538 1.3606 1.3674 1.3742 1.3811 1.3880 1.3949 1.4018 1.4088 1.4158 1.4228 1.4299 1.4369 1.4440 1.4512 1.4583 1.4655 1.4727 1.4800 1.4873 1.4946 1.5019 1.5093 1.5167 1.5241 1.5316 1.5391 0.9857 0.9842 0.9827 0.9811 0.9794 0.9776 0.9758 0.9738 0.9718 0.9697 0.9676 0.9653 0.9630 0.9607 0.9582 0.9557 0.9531 0.9504 0.9473 0.9448 0.9420 0.9390 0.9360 0.9329 0.9298 0.9266 0.9233 0.9200 0.9166 0.9132 0.9097 0.9062 0.9026 0.8989 0.8952 0.8915 0.8877 0.8838 0.8799 0.8760 0.8720 0.8680 0.8639 0.8599 0.8557 0.8516 0.8474 0.8431 0.8389 0.8346 0.8302 0.8259 0.8215 0.8171 0.8127 0.8082 Appendix 263 Table A5.1 Continued M1 ␯ ␮ M2 P2/P1 d2/d1 T2/T1 Po2/Po1 1.82 1.83 1.84 1.85 1.86 1.87 1.88 1.89 1.90 1.91 1.92 1.93 1.94 1.95 1.96 1.97 1.98 1.99 2.00 2.01 2.02 2.03 2.04 2.05 2.06 2.07 2.08 2.09 2.10 2.11 2.12 2.13 2.14 2.15 2.16 2.17 2.18 2.19 2.20 2.21 2.22 2.23 2.24 2.25 2.26 2.27 2.28 2.29 2.30 2.31 2.32 2.33 2.34 2.35 2.36 2.37 21.302 21.590 21.877 22.163 22.449 22.734 23.019 23.303 23.586 23.869 24.151 24.432 24.712 24.992 25.271 25.549 25.827 26.104 26.380 26.655 26.930 27.203 27.476 27.748 28.020 28.290 28.560 28.829 29.097 29.364 29.631 29.896 30.161 30.425 30.688 30.951 31.212 31.473 21.732 31.991 32.249 32.507 32.763 33.018 33.273 33.527 33.780 34.032 34.283 34.533 34.782 35.031 35.279 35.526 35.771 36.017 33.329 33.124 32.921 32.720 32.523 32.328 32.135 31.945 31.757 31.571 31.388 31.207 31.028 30.852 30.677 30.505 30.335 30.166 30.000 29.836 29.673 29.512 29.353 29.196 29.041 28.888 28.736 28.585 28.437 28.290 28.145 28.001 27.859 27.718 27.578 27.441 27.304 27.169 27.036 26.903 26.773 26.643 26.515 26.388 26.262 26.138 26.014 25.892 25.771 25.652 25.533 25.416 25.300 25.184 25.070 24.957 0.6121 0.6099 0.6078 0.6057 0.6036 0.6016 0.5996 0.5976 0.5956 0.5937 0.5918 0.5899 0.5880 0.5862 0.5844 0.5826 0.5808 0.5791 0.5774 0.5757 0.5740 0.5723 0.5707 0.5691 0.5675 0.5659 0.5643 0.5628 0.5613 0.5598 0.5583 0.5568 0.5554 0.5540 0.5525 0.5511 0.5498 0.5484 0.5471 0.5457 0.5444 0.5431 0.5418 0.5406 0.5393 0.5381 0.5368 0.5356 0.5344 0.5332 0.5321 0.5309 0.5297 0.5286 0.5275 0.5264 3.698 3.740 3.783 3.826 3.870 3.913 3.957 4.001 4.045 4.089 4.134 4.179 4.224 4.270 4.315 4.361 4.407 4.453 4.500 4.547 4.594 4.641 4.689 4.736 4.784 4.832 4.881 4.929 4.978 5.027 5.077 5.126 5.176 5.226 5.277 5.327 5.378 5.429 5.480 5.531 5.583 5.635 5.687 5.740 5.792 5.845 5.898 5.951 6.005 6.059 6.113 6.167 6.222 6.276 6.331 6.386 2.3909 2.4067 2.4224 2.4381 2.4537 2.4693 2.4848 2.5003 2.5157 2.5310 2.5463 2.5616 2.5767 2.5919 2.6069 2.6220 2.6369 2.6518 2.6667 2.6815 2.6962 2.7109 2.7255 2.7400 2.7545 2.7689 2.7833 2.7976 2.8119 2.8261 2.8402 2.8543 2.8683 2.8823 2.8962 2.9101 2.9238 2.9376 2.9512 2.9648 2.9784 2.9918 3.0053 3.0186 3.0319 3.0452 3.0584 3.0715 3.0845 3.0976 3.1105 3.1234 3.1362 3.1490 3.1617 3.1743 1.5466 1.5541 1.5617 1.5693 1.5770 1.5847 1.5924 1.6001 1.6079 1.6157 1.6236 1.6314 1.6394 1.6473 1.6553 1.6633 1.6713 1.6794 1.6875 1.6956 1.7038 1.7120 1.7203 1.7285 1.7369 1.7452 1.7536 1.7620 1.7705 1.7789 1.7875 1.7960 1.8046 1.8132 1.8219 1.8306 1.8393 1.8481 1.8569 1.8657 1.8746 1.8835 1.8924 1.9014 1.9104 1.9194 1.9285 1.9376 1.9468 1.9560 1.9652 1.9745 1.9838 1.9931 2.0025 2.0119 0.8038 0.7993 0.7948 0.7902 0.7857 0.7811 0.7765 0.7720 0.7674 0.7627 0.7581 0.7535 0.7488 0.7442 0.7395 0.7349 0.7302 0.7255 0.7209 0.7162 0.7115 0.7069 0.7022 0.6975 0.6928 0.6882 0.6835 0.6789 0.6742 0.6696 0.6649 0.6603 0.6557 0.6511 0.6464 0.6419 0.6373 0.6327 0.6281 0.6236 0.6191 0.6145 0.6100 0.6055 0.6011 0.5966 0.5921 0.5877 0.5833 0.5789 0.5745 0.5702 0.5658 0.5615 0.5572 0.5529 264 Aeronautical Engineer’s Data Book Table A5.1 Continued M1 ␯ ␮ M2 P2/P1 d2/d1 T2/T1 Po2/Po1 2.38 2.39 2.40 2.41 2.42 2.43 2.44 2.45 2.46 2.47 2.48 2.49 2.50 2.51 2.52 2.53 2.54 2.55 2.56 2.57 2.58 2.59 2.60 2.61 2.62 2.63 2.64 2.65 2.66 2.67 2.68 2.69 2.70 2.71 2.72 2.73 2.74 2.75 2.76 2.77 2.78 2.79 2.80 2.81 2.82 2.83 2.84 2.85 2.86 2.87 2.88 2.89 2.90 2.91 2.92 2.93 36.261 36.504 36.747 36.988 37.229 37.469 37.708 37.946 38.183 38.420 38.655 38.890 39.124 39.357 39.589 39.820 40.050 40.280 40.508 40.736 40.963 41.189 41.415 41.639 41.863 42.086 42.307 42.529 42.749 42.968 43.187 43.405 43.621 43.838 44.053 44.267 44.481 44.694 44.906 45.117 45.327 45.537 45.746 45.954 46.161 46.368 46.573 46.778 46.982 47.185 47.388 47.589 47.790 47.990 48.190 48.388 24.845 24.734 24.624 24.515 24.407 24.301 24.195 24.090 23.985 23.882 23.780 23.679 23.578 23.479 23.380 23.282 23.185 23.089 22.993 22.899 22.805 22.712 22.620 22.528 22.438 22.348 22.259 22.170 22.082 21.995 21.909 21.823 21.738 21.654 21.571 21.488 21.405 21.324 21.243 21.162 21.083 21.003 20.925 20.847 20.770 20.693 20.617 20.541 20.466 20.391 20.318 20.244 20.171 20.099 20.027 19.956 0.5253 0.5242 0.5231 0.5221 0.5210 0.5200 0.5189 0.5179 0.5169 0.5159 0.5149 0.5140 0.5130 0.5120 0.5111 0.5102 0.5092 0.5083 0.5074 0.5065 0.5056 0.5047 0.5039 0.5030 0.5022 0.5013 0.5005 0.4996 0.4988 0.4980 0.4972 0.4964 0.4956 0.4949 0.4941 0.4933 0.4926 0.4918 0.4911 0.4903 0.4896 0.4889 0.4882 0.4875 0.4868 0.4861 0.4854 0.4847 0.4840 0.4833 0.4827 0.4820 0.4814 0.4807 0.4801 0.4795 6.442 6.497 6.553 6.609 6.666 6.722 6.779 6.836 6.894 6.951 7.009 7.067 7.125 7.183 7.242 7.301 7.360 7.420 7.479 7.539 7.599 7.659 7.720 7.781 7.842 7.903 7.965 8.026 8.088 8.150 8.213 8.275 8.338 8.401 8.465 8.528 8.592 8.656 8.721 8.785 8.850 8.915 8.980 9.045 9.111 9.177 9.243 9.310 9.376 9.443 9.510 9.577 9.645 9.713 9.781 9.849 3.1869 3.1994 3.2119 3.2243 3.2367 3.2489 3.2612 3.2733 3.2855 3.2975 3.3095 3.3215 3.3333 3.3452 3.3569 3.3686 3.3803 3.3919 3.4034 3.4149 3.4263 3.4377 3.4490 3.4602 3.4714 3.4826 3.4937 3.5047 3.5157 3.5266 3.5374 3.5482 3.5590 3.5697 3.5803 3.5909 3.6015 3.6119 3.6224 3.6327 3.6431 3.6533 3.6636 3.6737 3.6838 3.6939 3.7039 3.7139 3.7238 3.7336 3.7434 3.7532 3.7629 3.7725 3.7821 3.7917 2.0213 2.0308 2.0403 2.0499 2.0595 2.0691 2.0788 2.0885 2.0982 2.1080 2.1178 2.1276 2.1375 2.1474 2.1574 2.1674 2.1774 2.1875 2.1976 2.2077 2.2179 2.2281 2.2383 2.2486 2.2590 2.2693 2.2797 2.2902 2.3006 2.3111 2.3217 2.3323 2.3429 2.3536 2.3642 2.3750 2.3858 2.3966 2.4074 2.4183 2.4292 2.4402 2.4512 2.4622 2.4733 2.4844 2.4955 2.5067 2.5179 2.5292 2.5405 2.5518 2.5632 2.5746 2.5861 2.5976 0.5486 0.5444 0.5401 0.5359 0.5317 0.5276 0.5234 0.5193 0.5152 0.5111 0.5071 0.5030 0.4990 0.4950 0.4911 0.4871 0.4832 0.4793 0.4754 0.4715 0.4677 0.4639 0.4601 0.4564 0.4526 0.4489 0.4452 0.4416 0.4379 0.4343 0.4307 0.4271 0.4236 0.4201 0.4166 0.4131 0.4097 0.4062 0.4028 0.3994 0.3961 0.3928 0.3895 0.3862 0.3829 0.3797 0.3765 0.3733 0.3701 0.3670 0.3639 0.3608 0.3577 0.3547 0.3517 0.3487 Appendix 265 Table A5.1 Continued M1 ␯ ␮ M2 P2/P1 d2/d1 T2/T1 Po2/Po1 2.94 2.95 2.96 2.97 2.98 2.99 3.00 3.02 3.04 3.06 3.08 3.10 3.12 3.14 3.16 3.18 3.20 3.22 3.24 3.26 3.28 3.30 3.32 3.34 3.36 3.38 3.40 3.42 3.44 3.46 3.48 3.50 3.52 3.54 3.56 3.58 3.60 3.62 3.64 3.66 3.68 3.70 3.72 3.74 3.76 3.78 3.80 3.82 3.84 3.86 3.88 3.90 3.92 3.94 3.96 3.98 48.586 48.783 48.980 49.175 49.370 49.564 49.757 50.142 50.523 50.902 51.277 51.650 52.020 52.386 52.751 53.112 53.470 53.826 54.179 54.529 54.877 55.222 55.564 55.904 56.241 56.576 56.908 57.237 57.564 57.888 58.210 58.530 58.847 59.162 59.474 59.784 60.091 60.397 60.700 61.001 61.299 61.595 61.889 62.181 62.471 62.758 63.044 63.327 63.608 63.887 64.164 64.440 64.713 64.984 65.253 65.520 19.885 19.815 19.745 19.676 19.607 19.539 19.471 19.337 19.205 19.075 18.946 18.819 18.694 18.571 18.449 18.329 18.210 18.093 17.977 17.863 17.751 17.640 17.530 17.422 17.315 17.209 17.105 17.002 16.900 16.799 16.700 16.602 16.505 16.409 16.314 16.220 16.128 16.036 15.946 15.856 15.768 15.680 15.594 15.508 15.424 15.340 15.258 15.176 15.095 15.015 14.936 14.857 14.780 14.703 14.627 14.552 0.4788 0.4782 0.4776 0.4770 0.4764 0.4758 0.4752 0.4740 0.4729 0.4717 0.4706 0.4695 0.4685 0.4674 0.4664 0.4654 0.4643 0.4634 0.4624 0.4614 0.4605 0.4596 0.4587 0.4578 0.4569 0.4560 0.4552 0.4544 0.4535 0.4527 0.4519 0.4512 0.4504 0.4496 0.4489 0.4481 0.4474 0.4467 0.4460 0.4453 0.4446 0.4439 0.4433 0.4426 0.4420 0.4414 0.4407 0.4401 0.4395 0.4389 0.4383 0.4377 0.4372 0.4366 0.4360 0.4355 9.918 9.986 10.05 10.12 10.19 10.26 10.33 10.47 10.61 10.75 10.90 11.04 11.19 11.33 11.48 11.63 11.78 11.93 12.08 12.23 12.38 12.53 12.69 12.84 13.00 13.16 13.32 13.47 13.63 13.80 13.96 14.12 14.28 14.45 14.61 14.78 14.95 15.12 15.29 15.46 15.63 15.80 15.97 16.15 16.32 16.50 16.68 16.85 17.03 17.21 17.39 17.57 17.76 17.94 18.12 18.31 3.8012 3.8106 3.8200 3.8294 3.8387 3.8479 3.8571 3.8754 3.8935 3.9114 3.9291 3.9466 3.9639 3.9811 3.9981 4.0149 4.0315 4.0479 4.0642 4.0803 4.0963 4.1120 4.1276 4.1431 4.1583 4.1734 4.1884 4.2032 4.2179 4.2323 4.2467 4.2609 4.2749 4.2888 4.3026 4.3162 4.3296 4.3429 4.3561 4.3692 4.3821 4.3949 4.4075 4.4200 4.4324 4.4447 4.4568 4.4688 4.4807 4.4924 4.5041 4.5156 4.5270 4.5383 4.5494 4.5605 2.6091 2.6206 2.6322 2.6439 2.6555 2.6673 2.6790 2.7026 2.7264 2.7503 2.7744 2.7986 2.8230 2.8475 2.8722 2.8970 2.9220 2.9471 2.9724 2.9979 3.0234 3.0492 3.0751 3.1011 3.1273 3.1537 3.1802 3.2069 3.2337 3.2607 3.2878 3.3151 3.3425 3.3701 3.3978 3.4257 3.4537 3.4819 3.5103 3.5388 3.5674 3.5962 3.6252 3.6543 3.6836 3.7130 3.7426 3.7723 3.8022 3.8323 3.8625 3.8928 3.9233 3.9540 3.9848 4.0158 0.3457 0.3428 0.3398 0.3369 0.3340 0.3312 0.3283 0.3227 0.3172 0.3118 0.3065 0.3012 0.2960 0.2910 0.2860 0.2811 0.2762 0.2715 0.2668 0.2622 0.2577 0.2533 0.2489 0.2446 0.2404 0.2363 0.2322 0.2282 0.2243 0.2205 0.2167 0.2129 0.2093 0.2057 0.2022 0.1987 0.1953 0.1920 0.1887 0.1855 0.1823 0.1792 0.1761 0.1731 0.1702 0.1673 0.1645 0.1617 0.1589 0.1563 0.1536 0.1510 0.1485 0.1460 0.1435 0.1411 266 Aeronautical Engineer’s Data Book Table A5.1 Continued M1 ␯ ␮ M2 P2/P1 d2/d1 T2/T1 Po2/Po1 4.00 4.05 4.10 4.15 4.20 4.25 4.30 4.35 4.40 4.45 4.50 4.55 4.60 4.65 4.70 4.75 4.80 4.85 4.90 4.95 5.00 5.10 5.20 5.30 5.40 5.50 5.60 5.70 5.80 5.90 6.00 65.785 66.439 67.082 67.713 68.333 68.942 69.541 70.129 70.706 71.274 71.832 72.380 72.919 73.449 73.970 74.482 74.986 75.482 75.969 76.449 76.920 77.841 78.732 79.596 80.433 81.245 82.032 82.796 83.537 84.256 84.955 14.478 14.295 14.117 13.943 13.774 13.609 13.448 13.290 13.137 12.986 12.840 12.696 12.556 12.419 12.284 12.153 12.025 11.899 11.776 11.655 11.537 11.308 11.087 10.876 10.672 10.476 10.287 10.104 9.928 9.758 9.594 0.4350 0.4336 0.4324 0.4311 0.4299 0.4288 0.4277 0.4266 0.4255 0.4245 0.4236 0.4226 0.4217 0.4208 0.4199 0.4191 0.4183 0.4175 0.4167 0.4160 0.4152 0.4138 0.4125 0.4113 0.4101 0.4090 0.4079 0.4069 0.4059 0.4050 0.4042 18.50 18.97 19.44 19.92 20.41 20.90 21.40 21.91 22.42 22.93 23.45 23.98 24.52 25.06 25.60 26.15 26.71 27.27 27.84 28.42 29.00 30.17 31.38 32.60 33.85 35.12 36.42 37.73 39.08 40.44 41.83 4.5714 4.5983 4.6245 4.6500 4.6749 4.6992 4.7229 4.7460 4.7685 4.7904 4.8119 4.8328 4.8532 4.8731 4.8926 4.9116 4.9301 4.9482 4.9659 4.9831 5.0000 5.0326 5.0637 5.0934 5.1218 5.1489 5.1749 5.1998 5.2236 5.2464 5.2683 4.0469 4.1254 4.2048 4.2852 4.3666 4.4489 4.5322 4.6165 4.7017 4.7879 4.8751 4.9632 5.0523 5.1424 5.2334 5.3254 5.4184 5.5124 5.6073 5.7032 5.8000 5.9966 6.1971 6.4014 6.6097 6.8218 7.0378 7.2577 7.4814 7.7091 7.9406 0.1388 0.1330 0.1276 0.1223 0.1173 0.1126 0.1080 0.1036 9.948e–2 9.550e–2 9.170e–2 8.806e–2 8.459e–2 8.126e–2 7.809e–2 7.505e–2 7.214e–2 6.936e–2 6.670e–2 6.415e–2 6.172e–2 5.715e–2 5.297e–2 4.913e–2 4.560e–2 4.236e–2 3.938e–2 3.664e–2 3.412e–2 3.179e–2 2.965e–2 Table A5.2 Oblique shock waves (isentropic flow, ␥=7/5) Notation: M1 = Upstream flow Mach number M2 = Downstream flow Mach number ␦ = (Delta) flow deflection angle ␪ = (Theta) wave angle P2/P1 = Ratio of static pressures across wave M1 ␦ Weak solution ␪ M2 P2/P1 1.05 0.0 72.25 1.050 1.000 1.10 1.10 0.0 1.0 65.38 69.81 1.100 1.039 1.000 1.077 1.15 1.15 1.15 0.0 1.0 2.0 60.41 63.16 67.01 1.150 1.102 1.043 1.000 1.062 1.141 Appendix 267 Table A5.2 Continued M1 ␦ Weak solution ␪ M2 P2/P1 1.20 1.20 1.20 1.20 0.0 1.0 2.0 3.0 56.44 58.55 61.05 64.34 1.200 1.158 1.111 1.056 1.000 1.056 1.120 1.198 1.25 1.25 1.25 1.25 1.25 1.25 0.0 1.0 2.0 3.0 4.0 5.0 53.13 54.88 56.85 59.13 61.99 66.59 1.25 1.211 1.170 1.124 1.072 0.999 1.000 1.053 1.111 1.176 1.254 1.366 1.30 1.30 1.30 1.30 1.30 1.30 1.30 0.0 1.0 2.0 3.0 4.0 5.0 6.0 50.29 51.81 53.48 55.32 57.42 59.96 63.46 1.300 1.263 1.224 1.184 1.140 1.090 1.027 1.000 1.051 1.107 1.167 1.233 1.311 1.411 1.35 1.35 1.35 1.35 1.35 1.35 1.35 1.35 1.35 0.0 1.0 2.0 3.0 4.0 5.0 6.0 7.0 8.0 47.80 49.17 50.64 52.22 53.97 55.93 58.23 61.18 66.92 1.350 1.314 1.277 1.239 1.199 1.157 1.109 1.052 0.954 1.000 1.051 1.104 1.162 1.224 1.292 1.370 1.466 1.633 1.40 1.40 1.40 1.40 1.40 1.40 1.40 1.40 1.40 1.40 0.0 1.0 2.0 3.0 4.0 5.0 6.0 7.0 8.0 9.0 45.59 46.84 48.17 49.59 51.12 52.78 54.63 56.76 59.37 63.19 1.400 1.365 1.330 1.293 1.255 1.216 1.174 1.128 1.074 1.003 1.000 1.050 1.103 1.159 1.219 1.283 1.354 1.433 1.526 1.655 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 2.20 0.0 2.0 4.0 6.0 8.0 10.0 12.0 14.0 16.0 18.0 20.0 22.0 24.0 26.0 27.04 28.59 30.24 31.98 33.83 35.79 37.87 40.10 42.49 45.09 47.98 51.28 55.36 62.70 2.200 2.124 2.049 1.974 1.899 1.823 1.745 1.666 1.583 1.496 1.404 1.301 1.181 0.980 1.000 1.127 1.265 1.417 1.583 1.764 1.961 2.176 2.410 2.666 2.949 3.270 3.655 4.292 Index Acceleration 17 Acronyms, aviation 72 Activity factor, propeller 119 Aerodynamic centre 101 Airport capacity 190 Airport data, worldwide 206–214 Airport design 173 Airport design types 189 Airspace abbreviations 75 Angular velocity 17 Approach definitions 135 Aspect ratio, wing 145 Atmosphere, International Standard 57 Axes notation 107 Axes transformation 109 Axis system, general 69 Axisymmetric flows 93 Configuration, wing 146–7 Constants 50 Construction, wing 159 Continuity equation 81 Data, civil aircraft 148–154 Data, helicopters 170 Datums, principles 217 Definitions, aeronautical 67 Density 11, 51 Derivatives, stability and control 243–4, 247–252 Design studies, aircraft 139 Design studies, helicopter 169 Design, airport 173 Dimensional analysis 23 Door clearances 181 Drag 67 Drag coefficients 95 Boundary layers 89 Cabin design 157 CAD 229 Capacity, airport 190 Cargo facilities, airport 195 Centre of pressure 101 Clearance radii, aircraft 185 Coefficients, airfoil 97 Coefficients, drag 95 Coefficients, propeller 117 Compatibility, airport/aircraft 178–187 Compressibility 77 Computer-aided- engineering (CAE) 229 Emissions, aircraft 144 Endurance, aircraft 136 Engine terminology 127 Engines, aero, types 121 Equations, generalized force 110 Equations, generalized moment 111 Equations, motion, non­ linear 111 FAA-AAS document index 200–204 Federal Aviation Regulations Finite element analysis 233 270 Index Flow, 1-D 79 Flow equations 79 Flow, 2-D 81 Flow, isentropic 89 Flows, axisymmetric 93 Force Forces, aerodynamic 67 Functions, transfer 245 Gas, perfect 76 Gas, polytropic 77 Gases, weights of 50 Ground service 159 Helicopter terminology 71 Helicopter, design 165 Holding bay sizing, aircraft 187 Holes, tolerancing 220 ISA 57–65 Landing definitions 135 Landing length 182 Laplace’s equation 82 Lift 67 Limits and fits 223–227 Loading, wing 103 Moments, aerodynamic 67 Motion notation 109 Navier–Stokes equation 85 Noise, aircraft 140 Notations, aerodynamic 51–55 Numbers, preferred 215 Operational profile 133 Operational profile, helicopter 169,172 Operational requirements, airport 175 Parametric estimates 138 Passenger throughput, airport 199 Pavement design, airport 196 Piers, airport 193 Power 15 Power, engine 131 Preferred sizes 215 Pressure conversions 11 Pressure distributions, airfoil 99–100 Pressure, centre of 101 Profile, operational 133 Propeller blades 116 Properties, material 160–163 Propfan engine 123 Pulsejet engine 126 Ramjet engine 126 Range, aircraft 136 Reynolds number 87 Runway pavements, airport 197 Screw threads, tolerancing 222 Shock waves 91 SI units Sink, fluid 85–87 Site selection, airport 174 Sonic boom 143 Source, fluid 85 Stability terms 113–114 Stream function 82 Stress 17 Supersonic conditions 103 Surface finish 227 Takeoff length 182 Temperature 11 Temperature conversions 13 Terminal design,airport 191–195 Terminology, helicopter 71 Thrust ... 0.1761 0.1731 0.1702 0.1673 0.1645 0.1617 0.1589 0.1563 0.1536 0.1510 0 .148 5 0 .146 0 0 .143 5 0 .141 1 266 Aeronautical Engineer? ??s Data Book Table A5.1 Continued M1 ␯ ␮ M2 P2/P1 d2/d1 T2/T1 Po2/Po1 4.00... 16.602 16.505 16.409 16. 314 16.220 16.128 16.036 15.946 15.856 15.768 15.680 15.594 15.508 15.424 15.340 15.258 15.176 15.095 15.015 14. 936 14. 857 14. 780 14. 703 14. 627 14. 552 0.4788 0.4782 0.4776... 0.1522 0.1505 0 .148 8 0 .147 2 0 .145 6 0 .143 9 0 .142 4 0 .140 8 0.1392 0.1377 0.1362 0.1346 0.1332 0.1317 0.1302 0.1288 0.1274 0.1260 0.1246 0.1232 0.1218 0.1205 0.1192 0.1179 0.1166 0.1153 0. 1140 0.1128