HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAWKER TEMPEST 96.77% SEMISPAN AIRFOIL (tempest3-il) Reynolds number: 500,000 Max Cl/Cd: 63.12 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tempest3-il-500000-n5.txt Download as CSV file: xf-tempest3-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.7348 0.05067 0.04821 -0.0544 1.0000 0.0051
-10.750 -0.7835 0.04366 0.04089 -0.0530 1.0000 0.0049
-10.500 -0.8075 0.04067 0.03771 -0.0484 1.0000 0.0050
-10.250 -0.8222 0.03849 0.03536 -0.0435 1.0000 0.0051
-10.000 -0.8286 0.03641 0.03310 -0.0395 1.0000 0.0052
-9.750 -0.8418 0.03333 0.02969 -0.0344 1.0000 0.0052
-9.500 -0.8426 0.03150 0.02765 -0.0305 1.0000 0.0054
-9.250 -0.8455 0.02923 0.02509 -0.0261 1.0000 0.0055
-9.000 -0.8373 0.02685 0.02236 -0.0237 0.9990 0.0056
-8.750 -0.8156 0.02456 0.01973 -0.0239 0.9962 0.0058
-8.500 -0.7906 0.02304 0.01794 -0.0243 0.9937 0.0062
-8.250 -0.7668 0.02160 0.01626 -0.0243 0.9907 0.0065
-8.000 -0.7400 0.02058 0.01504 -0.0246 0.9879 0.0068
-7.750 -0.7131 0.01928 0.01352 -0.0250 0.9853 0.0070
-7.500 -0.6878 0.01742 0.01145 -0.0253 0.9831 0.0075
-7.250 -0.6623 0.01648 0.01039 -0.0253 0.9797 0.0078
-7.000 -0.6357 0.01575 0.00957 -0.0255 0.9760 0.0082
-6.750 -0.6069 0.01503 0.00876 -0.0260 0.9731 0.0087
-6.500 -0.5765 0.01434 0.00798 -0.0269 0.9709 0.0092
-6.250 -0.5450 0.01367 0.00722 -0.0280 0.9690 0.0098
-6.000 -0.5197 0.01320 0.00667 -0.0277 0.9635 0.0103
-5.750 -0.4908 0.01250 0.00589 -0.0282 0.9596 0.0118
-5.500 -0.4594 0.01200 0.00535 -0.0292 0.9565 0.0131
-5.250 -0.4310 0.01159 0.00488 -0.0295 0.9516 0.0143
-5.000 -0.4027 0.01124 0.00446 -0.0297 0.9460 0.0158
-4.750 -0.3720 0.01077 0.00397 -0.0305 0.9420 0.0201
-4.500 -0.3454 0.01045 0.00362 -0.0303 0.9354 0.0263
-4.250 -0.3171 0.01005 0.00329 -0.0306 0.9296 0.0434
-4.000 -0.2905 0.00967 0.00301 -0.0306 0.9229 0.0716
-3.750 -0.2636 0.00932 0.00278 -0.0305 0.9158 0.1025
-3.500 -0.2373 0.00903 0.00256 -0.0304 0.9084 0.1318
-3.250 -0.2110 0.00871 0.00235 -0.0302 0.9007 0.1691
-3.000 -0.1876 0.00827 0.00216 -0.0295 0.8920 0.2369
-2.750 -0.1647 0.00775 0.00195 -0.0288 0.8836 0.3274
-2.500 -0.1423 0.00735 0.00178 -0.0278 0.8741 0.4064
-2.250 -0.1202 0.00697 0.00166 -0.0267 0.8648 0.4858
-2.000 -0.0968 0.00671 0.00155 -0.0258 0.8557 0.5450
-1.750 -0.0739 0.00648 0.00146 -0.0248 0.8458 0.5983
-1.500 -0.0508 0.00629 0.00139 -0.0237 0.8361 0.6460
-1.250 -0.0275 0.00612 0.00134 -0.0227 0.8265 0.6919
-1.000 -0.0038 0.00599 0.00131 -0.0217 0.8161 0.7340
-0.750 0.0207 0.00590 0.00130 -0.0208 0.8054 0.7701
-0.500 0.0456 0.00582 0.00132 -0.0200 0.7946 0.8115
-0.250 0.0720 0.00579 0.00139 -0.0194 0.7832 0.8552
0.000 0.1008 0.00582 0.00145 -0.0194 0.7713 0.8804
0.250 0.1293 0.00589 0.00148 -0.0194 0.7581 0.8961
0.500 0.1588 0.00596 0.00152 -0.0196 0.7431 0.9068
0.750 0.1873 0.00605 0.00156 -0.0197 0.7259 0.9157
1.000 0.2158 0.00615 0.00160 -0.0198 0.7079 0.9236
1.250 0.2454 0.00625 0.00165 -0.0202 0.6907 0.9299
1.500 0.2749 0.00637 0.00171 -0.0205 0.6738 0.9358
1.750 0.3026 0.00647 0.00177 -0.0205 0.6564 0.9420
2.000 0.3342 0.00661 0.00186 -0.0213 0.6362 0.9456
2.250 0.3623 0.00679 0.00195 -0.0214 0.6088 0.9507
2.500 0.3887 0.00698 0.00204 -0.0211 0.5789 0.9558
2.750 0.4214 0.00718 0.00216 -0.0223 0.5520 0.9582
3.000 0.4524 0.00739 0.00229 -0.0231 0.5221 0.9611
3.250 0.4801 0.00764 0.00244 -0.0233 0.4859 0.9654
3.500 0.5056 0.00801 0.00261 -0.0230 0.4298 0.9697
3.750 0.5334 0.00871 0.00287 -0.0236 0.3304 0.9724
4.000 0.5610 0.00935 0.00317 -0.0241 0.2507 0.9759
4.250 0.5858 0.00998 0.00350 -0.0239 0.1797 0.9805
4.500 0.6135 0.01057 0.00383 -0.0244 0.1216 0.9836
4.750 0.6430 0.01114 0.00418 -0.0254 0.0745 0.9859
5.000 0.6719 0.01164 0.00454 -0.0261 0.0443 0.9886
5.250 0.7003 0.01208 0.00493 -0.0265 0.0290 0.9913
5.500 0.7278 0.01251 0.00535 -0.0268 0.0209 0.9939
5.750 0.7581 0.01285 0.00572 -0.0277 0.0174 0.9958
6.000 0.7869 0.01337 0.00626 -0.0283 0.0143 0.9979
6.250 0.8162 0.01383 0.00679 -0.0290 0.0129 0.9997
6.500 0.8357 0.01421 0.00724 -0.0275 0.0117 1.0000
6.750 0.8523 0.01460 0.00767 -0.0255 0.0107 1.0000
7.000 0.8672 0.01513 0.00822 -0.0232 0.0096 1.0000
7.250 0.8803 0.01580 0.00897 -0.0205 0.0091 1.0000
7.500 0.8955 0.01630 0.00955 -0.0182 0.0087 1.0000
7.750 0.9101 0.01686 0.01018 -0.0158 0.0083 1.0000
8.000 0.9242 0.01747 0.01087 -0.0134 0.0078 1.0000
8.250 0.9381 0.01812 0.01162 -0.0109 0.0074 1.0000
8.500 0.9516 0.01883 0.01241 -0.0085 0.0071 1.0000
8.750 0.9653 0.01951 0.01315 -0.0061 0.0068 1.0000
9.000 0.9789 0.02020 0.01391 -0.0038 0.0064 1.0000
9.250 0.9894 0.02118 0.01497 -0.0011 0.0061 1.0000
9.500 0.9991 0.02235 0.01627 0.0018 0.0058 1.0000
9.750 1.0121 0.02312 0.01716 0.0040 0.0056 1.0000
10.000 1.0224 0.02400 0.01816 0.0068 0.0054 1.0000
10.250 1.0289 0.02518 0.01950 0.0101 0.0052 1.0000
10.500 1.0360 0.02627 0.02076 0.0131 0.0050 1.0000
10.750 1.0422 0.02749 0.02215 0.0161 0.0049 1.0000
11.000 1.0459 0.02904 0.02389 0.0192 0.0048 1.0000
11.250 1.0517 0.03022 0.02521 0.0218 0.0046 1.0000
11.500 1.0537 0.03188 0.02704 0.0245 0.0045 1.0000
11.750 1.0554 0.03350 0.02883 0.0270 0.0043 1.0000
12.000 1.0544 0.03544 0.03095 0.0293 0.0043 1.0000
12.250 1.0506 0.03772 0.03342 0.0315 0.0042 1.0000
12.500 1.0515 0.03946 0.03528 0.0328 0.0041 1.0000
12.750 1.0393 0.04296 0.03904 0.0343 0.0041 1.0000
13.000 1.0318 0.04601 0.04226 0.0349 0.0041 1.0000
13.250 1.0178 0.05021 0.04667 0.0347 0.0041 1.0000
13.500 1.0086 0.05407 0.05068 0.0337 0.0040 1.0000
13.750 0.9871 0.06028 0.05712 0.0314 0.0040 1.0000
14.000 0.9753 0.06554 0.06251 0.0286 0.0040 1.0000
14.250 0.9588 0.07220 0.06932 0.0246 0.0039 1.0000
14.500 0.8976 0.09000 0.08750 0.0137 0.0041 1.0000
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