HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Reynolds number: 200,000 Max Cl/Cd: 65.61 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-tempest2-il-200000.txt Download as CSV file: xf-tempest2-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: HAWKER TEMPEST 61% SEMISPAN AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5499 0.08684 0.08330 -0.0436 1.0000 0.0687
-10.250 -0.6294 0.04884 0.04502 -0.0597 1.0000 0.0398
-10.000 -0.6528 0.04557 0.04168 -0.0565 1.0000 0.0392
-9.750 -0.6790 0.04279 0.03881 -0.0515 1.0000 0.0386
-9.500 -0.7040 0.04036 0.03629 -0.0454 1.0000 0.0379
-9.250 -0.8193 0.04566 0.04044 -0.0299 1.0000 0.0323
-9.000 -0.8257 0.04338 0.03791 -0.0251 1.0000 0.0322
-8.750 -0.8229 0.04119 0.03554 -0.0214 1.0000 0.0315
-8.500 -0.8278 0.03782 0.03190 -0.0170 1.0000 0.0311
-8.250 -0.8287 0.03509 0.02886 -0.0126 1.0000 0.0309
-8.000 -0.8257 0.03267 0.02611 -0.0087 1.0000 0.0309
-7.750 -0.8191 0.03062 0.02373 -0.0052 1.0000 0.0311
-7.500 -0.8093 0.02894 0.02174 -0.0021 1.0000 0.0314
-7.250 -0.7977 0.02724 0.01975 0.0007 1.0000 0.0320
-7.000 -0.7830 0.02482 0.01717 0.0027 1.0000 0.0334
-6.750 -0.7686 0.02386 0.01619 0.0047 1.0000 0.0353
-6.500 -0.7530 0.02287 0.01509 0.0069 1.0000 0.0372
-6.250 -0.7370 0.02186 0.01396 0.0090 1.0000 0.0389
-6.000 -0.7212 0.02107 0.01302 0.0112 1.0000 0.0408
-5.750 -0.6934 0.01967 0.01166 0.0106 0.9970 0.0454
-5.500 -0.6591 0.01895 0.01085 0.0090 0.9930 0.0525
-5.250 -0.6287 0.01802 0.00994 0.0081 0.9879 0.0639
-5.000 -0.5965 0.01707 0.00922 0.0066 0.9837 0.0969
-4.750 -0.5681 0.01642 0.00876 0.0059 0.9779 0.1389
-4.500 -0.5355 0.01591 0.00839 0.0043 0.9728 0.1785
-4.250 -0.5018 0.01533 0.00809 0.0025 0.9689 0.2335
-4.000 -0.4814 0.01449 0.00772 0.0033 0.9612 0.3257
-3.750 -0.4567 0.01351 0.00755 0.0034 0.9563 0.4936
-3.500 -0.4392 0.01299 0.00748 0.0056 0.9481 0.6031
-3.250 -0.4079 0.01268 0.00749 0.0052 0.9434 0.6878
-3.000 -0.3719 0.01258 0.00752 0.0040 0.9400 0.7477
-2.750 -0.3451 0.01256 0.00756 0.0046 0.9325 0.7881
-2.500 -0.3049 0.01260 0.00761 0.0026 0.9291 0.8240
-2.250 -0.2592 0.01270 0.00765 -0.0006 0.9269 0.8508
-2.000 -0.2249 0.01289 0.00782 -0.0014 0.9205 0.8714
-1.750 -0.1787 0.01309 0.00794 -0.0047 0.9172 0.8876
-1.500 -0.1276 0.01330 0.00808 -0.0089 0.9152 0.9006
-1.250 -0.0687 0.01371 0.00842 -0.0145 0.9146 0.9135
-1.000 0.0000 0.01404 0.00869 -0.0223 0.9149 0.9191
-0.750 0.0534 0.01408 0.00868 -0.0273 0.9132 0.9268
-0.500 0.1148 0.01404 0.00859 -0.0340 0.9120 0.9293
-0.250 0.1582 0.01403 0.00857 -0.0371 0.9045 0.9352
0.000 0.2036 0.01385 0.00837 -0.0406 0.8997 0.9415
0.250 0.2548 0.01366 0.00817 -0.0454 0.8941 0.9446
0.500 0.2995 0.01346 0.00798 -0.0488 0.8860 0.9496
0.750 0.3367 0.01330 0.00782 -0.0506 0.8759 0.9563
1.000 0.3847 0.01299 0.00751 -0.0546 0.8669 0.9595
1.250 0.4238 0.01279 0.00731 -0.0568 0.8542 0.9651
1.500 0.4598 0.01262 0.00714 -0.0584 0.8404 0.9711
1.750 0.5002 0.01239 0.00694 -0.0611 0.8262 0.9758
2.000 0.5342 0.01228 0.00683 -0.0623 0.8111 0.9823
2.250 0.5745 0.01200 0.00653 -0.0649 0.7941 0.9866
2.500 0.6099 0.01180 0.00635 -0.0665 0.7726 0.9924
2.750 0.6473 0.01155 0.00609 -0.0685 0.7519 0.9972
3.000 0.6763 0.01143 0.00597 -0.0689 0.7306 1.0000
3.250 0.6947 0.01143 0.00594 -0.0671 0.7097 1.0000
3.500 0.7127 0.01145 0.00596 -0.0651 0.6878 1.0000
3.750 0.7305 0.01150 0.00597 -0.0631 0.6642 1.0000
4.000 0.7474 0.01157 0.00601 -0.0610 0.6377 1.0000
4.250 0.7634 0.01169 0.00605 -0.0586 0.6066 1.0000
4.500 0.7781 0.01186 0.00614 -0.0559 0.5695 1.0000
4.750 0.7915 0.01209 0.00624 -0.0531 0.5262 1.0000
5.000 0.8031 0.01243 0.00638 -0.0499 0.4733 1.0000
5.250 0.8125 0.01288 0.00658 -0.0465 0.4111 1.0000
5.500 0.8197 0.01351 0.00689 -0.0427 0.3446 1.0000
5.750 0.8261 0.01423 0.00730 -0.0389 0.2815 1.0000
6.000 0.8325 0.01500 0.00777 -0.0353 0.2216 1.0000
6.250 0.8383 0.01583 0.00829 -0.0315 0.1665 1.0000
6.500 0.8429 0.01676 0.00893 -0.0275 0.1172 1.0000
6.750 0.8456 0.01781 0.00972 -0.0231 0.0833 1.0000
7.000 0.8506 0.01870 0.01051 -0.0190 0.0649 1.0000
7.250 0.8551 0.01959 0.01139 -0.0147 0.0565 1.0000
7.500 0.8596 0.02048 0.01227 -0.0106 0.0506 1.0000
7.750 0.8651 0.02144 0.01328 -0.0066 0.0465 1.0000
8.000 0.8740 0.02217 0.01404 -0.0033 0.0426 1.0000
8.250 0.8801 0.02336 0.01520 0.0003 0.0396 1.0000
8.500 0.8935 0.02483 0.01672 0.0027 0.0376 1.0000
8.750 0.9097 0.02597 0.01798 0.0047 0.0359 1.0000
9.000 0.9246 0.02706 0.01916 0.0068 0.0337 1.0000
9.250 0.9376 0.02813 0.02026 0.0090 0.0316 1.0000
9.500 0.9679 0.03177 0.02402 0.0076 0.0296 1.0000
9.750 0.9809 0.03333 0.02583 0.0100 0.0292 1.0000
10.000 0.9925 0.03525 0.02801 0.0124 0.0288 1.0000
10.250 1.0001 0.03749 0.03054 0.0153 0.0286 1.0000
10.500 1.0031 0.03991 0.03327 0.0188 0.0284 1.0000
10.750 1.0013 0.04211 0.03574 0.0228 0.0282 1.0000
11.000 0.9924 0.04404 0.03793 0.0278 0.0277 1.0000
11.250 0.9832 0.04605 0.04018 0.0323 0.0273 1.0000
11.500 0.9713 0.04862 0.04301 0.0364 0.0272 1.0000
11.750 0.9580 0.05106 0.04567 0.0399 0.0267 1.0000
12.000 0.9415 0.05429 0.04914 0.0428 0.0270 1.0000
12.250 0.9217 0.05795 0.05303 0.0450 0.0273 1.0000
12.500 0.9018 0.06192 0.05720 0.0462 0.0276 1.0000
12.750 0.8800 0.06634 0.06180 0.0463 0.0278 1.0000
13.000 0.8592 0.07139 0.06699 0.0455 0.0284 1.0000
13.250 0.8350 0.07707 0.07284 0.0435 0.0285 1.0000
13.500 0.8113 0.08359 0.07948 0.0405 0.0288 1.0000
13.750 0.5505 0.11906 0.11556 0.0212 0.0513 1.0000
14.000 0.5447 0.12251 0.11899 0.0199 0.0478 1.0000
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