HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 50,000 Max Cl/Cd: 32.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tempest3-il-50000-n5.txt Download as CSV file: xf-tempest3-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5430 0.09632 0.08912 -0.0335 1.0000 0.0425
-10.000 -0.5472 0.09128 0.08415 -0.0359 1.0000 0.0420
-9.750 -0.5546 0.08550 0.07842 -0.0393 1.0000 0.0415
-9.500 -0.5665 0.07989 0.07286 -0.0426 1.0000 0.0410
-9.250 -0.5830 0.07514 0.06811 -0.0442 1.0000 0.0406
-9.000 -0.6007 0.07137 0.06434 -0.0436 1.0000 0.0402
-8.750 -0.6180 0.06768 0.06059 -0.0420 1.0000 0.0399
-8.500 -0.6315 0.06398 0.05677 -0.0401 1.0000 0.0396
-8.250 -0.6419 0.06040 0.05303 -0.0378 1.0000 0.0394
-8.000 -0.6500 0.05676 0.04916 -0.0352 1.0000 0.0393
-7.750 -0.6543 0.05333 0.04545 -0.0324 1.0000 0.0394
-7.500 -0.6558 0.04999 0.04177 -0.0295 1.0000 0.0399
-7.250 -0.6544 0.04683 0.03821 -0.0266 1.0000 0.0410
-7.000 -0.6499 0.04385 0.03475 -0.0236 1.0000 0.0424
-6.750 -0.6422 0.04102 0.03136 -0.0206 1.0000 0.0438
-6.500 -0.6311 0.03825 0.02825 -0.0182 1.0000 0.0452
-6.250 -0.6168 0.03588 0.02564 -0.0162 1.0000 0.0466
-6.000 -0.6001 0.03378 0.02327 -0.0143 1.0000 0.0485
-5.750 -0.5817 0.03187 0.02107 -0.0125 1.0000 0.0519
-5.500 -0.5616 0.03017 0.01897 -0.0108 1.0000 0.0573
-5.250 -0.5430 0.02875 0.01753 -0.0092 1.0000 0.0631
-5.000 -0.5217 0.02727 0.01581 -0.0075 1.0000 0.0699
-4.750 -0.5034 0.02614 0.01464 -0.0058 1.0000 0.0831
-4.500 -0.4853 0.02490 0.01342 -0.0041 1.0000 0.1001
-4.250 -0.4676 0.02370 0.01231 -0.0025 1.0000 0.1367
-4.000 -0.4515 0.02237 0.01131 -0.0009 1.0000 0.1958
-3.750 -0.4389 0.02098 0.01057 0.0011 1.0000 0.2960
-3.500 -0.4319 0.01955 0.01021 0.0049 1.0000 0.4730
-3.250 -0.4130 0.01888 0.01043 0.0085 1.0000 0.6866
-3.000 -0.3645 0.01929 0.01083 0.0071 1.0000 0.8269
-2.750 -0.3091 0.01984 0.01096 0.0033 1.0000 0.8955
-2.500 -0.2241 0.02050 0.01107 -0.0065 1.0000 0.9484
-2.250 -0.1269 0.02060 0.01061 -0.0199 1.0000 0.9877
-2.000 -0.0872 0.02039 0.01015 -0.0235 1.0000 1.0000
-1.750 -0.0855 0.02027 0.00994 -0.0200 1.0000 1.0000
-1.500 -0.0835 0.02020 0.00978 -0.0165 1.0000 1.0000
-1.250 -0.0808 0.02018 0.00963 -0.0130 1.0000 1.0000
-1.000 -0.0771 0.02020 0.00956 -0.0097 1.0000 1.0000
-0.750 -0.0723 0.02027 0.00953 -0.0066 1.0000 1.0000
-0.500 -0.0366 0.02045 0.00959 -0.0093 0.9914 1.0000
-0.250 0.0026 0.02070 0.00973 -0.0126 0.9819 1.0000
0.000 0.0392 0.02088 0.00981 -0.0153 0.9715 1.0000
0.250 0.0748 0.02107 0.00994 -0.0177 0.9608 1.0000
0.500 0.1108 0.02127 0.01011 -0.0201 0.9504 1.0000
0.750 0.1501 0.02147 0.01030 -0.0231 0.9410 1.0000
1.000 0.1826 0.02163 0.01047 -0.0247 0.9292 1.0000
1.250 0.2157 0.02178 0.01066 -0.0263 0.9174 1.0000
1.500 0.2497 0.02193 0.01088 -0.0280 0.9058 1.0000
1.750 0.2857 0.02206 0.01107 -0.0299 0.8944 1.0000
2.000 0.3259 0.02212 0.01125 -0.0325 0.8839 1.0000
2.250 0.3620 0.02217 0.01146 -0.0342 0.8717 1.0000
2.500 0.3948 0.02219 0.01161 -0.0352 0.8580 1.0000
2.750 0.4280 0.02216 0.01174 -0.0361 0.8438 1.0000
3.000 0.4605 0.02209 0.01185 -0.0366 0.8285 1.0000
3.250 0.4872 0.02209 0.01205 -0.0361 0.8106 1.0000
3.500 0.5169 0.02200 0.01216 -0.0358 0.7926 1.0000
3.750 0.5489 0.02183 0.01220 -0.0358 0.7744 1.0000
4.000 0.5737 0.02176 0.01234 -0.0345 0.7522 1.0000
4.250 0.6012 0.02155 0.01237 -0.0333 0.7274 1.0000
4.500 0.6250 0.02135 0.01236 -0.0313 0.6967 1.0000
4.750 0.6495 0.02111 0.01226 -0.0292 0.6604 1.0000
5.000 0.6687 0.02105 0.01229 -0.0263 0.6147 1.0000
5.250 0.6852 0.02107 0.01224 -0.0227 0.5511 1.0000
5.500 0.6953 0.02144 0.01232 -0.0184 0.4550 1.0000
5.750 0.6997 0.02247 0.01263 -0.0137 0.3326 1.0000
6.000 0.7011 0.02413 0.01352 -0.0096 0.2191 1.0000
6.250 0.7045 0.02609 0.01483 -0.0062 0.1409 1.0000
6.500 0.7118 0.02790 0.01630 -0.0033 0.1037 1.0000
6.750 0.7232 0.02950 0.01786 -0.0007 0.0843 1.0000
7.000 0.7370 0.03102 0.01942 0.0015 0.0716 1.0000
7.250 0.7526 0.03260 0.02101 0.0033 0.0629 1.0000
7.500 0.7756 0.03438 0.02308 0.0046 0.0569 1.0000
7.750 0.7973 0.03641 0.02508 0.0054 0.0516 1.0000
8.000 0.8202 0.03840 0.02749 0.0065 0.0465 1.0000
8.250 0.8421 0.04087 0.03024 0.0075 0.0439 1.0000
8.500 0.8602 0.04353 0.03316 0.0087 0.0423 1.0000
8.750 0.8745 0.04678 0.03658 0.0100 0.0405 1.0000
9.000 0.8809 0.04964 0.03992 0.0127 0.0394 1.0000
9.250 0.8829 0.05256 0.04332 0.0155 0.0382 1.0000
9.500 0.8797 0.05566 0.04685 0.0186 0.0370 1.0000
9.750 0.8735 0.05880 0.05033 0.0215 0.0363 1.0000
10.000 0.8627 0.06196 0.05383 0.0245 0.0361 1.0000
10.250 0.8470 0.06515 0.05725 0.0276 0.0359 1.0000
10.500 0.8298 0.06864 0.06086 0.0295 0.0360 1.0000
10.750 0.8114 0.07256 0.06496 0.0303 0.0363 1.0000
11.000 0.7908 0.07720 0.06973 0.0297 0.0364 1.0000
11.250 0.7703 0.08254 0.07519 0.0276 0.0368 1.0000
11.500 0.7499 0.08888 0.08159 0.0242 0.0372 1.0000
11.750 0.7319 0.09596 0.08870 0.0199 0.0378 1.0000
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Polar data table (+)
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