HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HAWKER TEMPEST 61% SEMISPAN AIRFOIL (tempest2-il) Reynolds number: 50,000 Max Cl/Cd: 31.99 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-tempest2-il-50000-n5.txt Download as CSV file: xf-tempest2-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5519 0.10046 0.09304 -0.0409 1.0000 0.0493
-11.250 -0.5647 0.09314 0.08579 -0.0447 1.0000 0.0488
-11.000 -0.5817 0.08567 0.07835 -0.0491 1.0000 0.0481
-10.750 -0.6054 0.07868 0.07137 -0.0530 1.0000 0.0473
-10.500 -0.6325 0.07286 0.06550 -0.0551 1.0000 0.0464
-10.250 -0.6604 0.06824 0.06082 -0.0547 1.0000 0.0456
-10.000 -0.6875 0.06459 0.05706 -0.0520 1.0000 0.0449
-9.750 -0.7094 0.06183 0.05418 -0.0480 1.0000 0.0452
-9.500 -0.7254 0.05893 0.05111 -0.0444 1.0000 0.0455
-9.250 -0.7378 0.05610 0.04806 -0.0406 1.0000 0.0461
-9.000 -0.7470 0.05327 0.04498 -0.0368 1.0000 0.0469
-8.750 -0.7528 0.05044 0.04180 -0.0330 1.0000 0.0476
-8.500 -0.7551 0.04762 0.03862 -0.0294 1.0000 0.0484
-8.250 -0.7536 0.04482 0.03542 -0.0259 1.0000 0.0494
-8.000 -0.7478 0.04213 0.03229 -0.0227 1.0000 0.0506
-7.750 -0.7386 0.03978 0.02961 -0.0200 1.0000 0.0527
-7.500 -0.7279 0.03830 0.02809 -0.0177 1.0000 0.0560
-7.250 -0.7148 0.03658 0.02612 -0.0154 1.0000 0.0599
-7.000 -0.6966 0.03460 0.02373 -0.0135 1.0000 0.0638
-6.750 -0.6824 0.03322 0.02242 -0.0115 1.0000 0.0687
-6.500 -0.6650 0.03185 0.02077 -0.0096 1.0000 0.0769
-6.250 -0.6496 0.03060 0.01953 -0.0076 1.0000 0.0854
-6.000 -0.6345 0.02948 0.01838 -0.0055 1.0000 0.0977
-5.750 -0.6192 0.02837 0.01722 -0.0034 1.0000 0.1146
-5.500 -0.6053 0.02732 0.01624 -0.0012 1.0000 0.1363
-5.250 -0.5915 0.02634 0.01533 0.0009 1.0000 0.1645
-5.000 -0.5782 0.02542 0.01450 0.0031 1.0000 0.1978
-4.750 -0.5653 0.02448 0.01377 0.0052 1.0000 0.2385
-4.500 -0.5533 0.02351 0.01310 0.0076 1.0000 0.2922
-4.250 -0.5430 0.02250 0.01257 0.0103 1.0000 0.3683
-4.000 -0.5347 0.02167 0.01232 0.0139 1.0000 0.4741
-3.750 -0.5221 0.02121 0.01229 0.0174 1.0000 0.5848
-3.500 -0.5013 0.02116 0.01249 0.0199 1.0000 0.6774
-3.250 -0.4737 0.02144 0.01280 0.0212 1.0000 0.7505
-3.000 -0.4413 0.02189 0.01314 0.0214 1.0000 0.8065
-2.750 -0.4043 0.02246 0.01348 0.0205 1.0000 0.8514
-2.500 -0.3535 0.02327 0.01403 0.0170 1.0000 0.8905
-2.250 -0.2910 0.02414 0.01457 0.0112 1.0000 0.9255
-2.000 -0.2260 0.02465 0.01478 0.0039 0.9998 0.9490
-1.750 -0.1664 0.02485 0.01472 -0.0031 0.9959 0.9661
-1.500 -0.1097 0.02490 0.01457 -0.0099 0.9914 0.9794
-1.250 -0.0538 0.02487 0.01436 -0.0167 0.9864 0.9910
-1.000 -0.0024 0.02485 0.01420 -0.0227 0.9812 1.0000
-0.750 0.0330 0.02479 0.01404 -0.0257 0.9710 1.0000
-0.500 0.0654 0.02472 0.01390 -0.0279 0.9600 1.0000
-0.250 0.0980 0.02469 0.01381 -0.0301 0.9494 1.0000
0.000 0.1345 0.02469 0.01376 -0.0328 0.9402 1.0000
0.250 0.1641 0.02467 0.01372 -0.0342 0.9288 1.0000
0.500 0.1932 0.02468 0.01372 -0.0353 0.9173 1.0000
0.750 0.2250 0.02469 0.01373 -0.0369 0.9068 1.0000
1.000 0.2624 0.02466 0.01374 -0.0393 0.8977 1.0000
1.250 0.2897 0.02469 0.01380 -0.0398 0.8855 1.0000
1.500 0.3189 0.02470 0.01386 -0.0406 0.8737 1.0000
1.750 0.3509 0.02469 0.01393 -0.0418 0.8626 1.0000
2.000 0.3888 0.02456 0.01389 -0.0438 0.8532 1.0000
2.250 0.4152 0.02455 0.01396 -0.0437 0.8399 1.0000
2.500 0.4417 0.02452 0.01405 -0.0435 0.8264 1.0000
2.750 0.4690 0.02446 0.01408 -0.0433 0.8124 1.0000
3.000 0.4964 0.02436 0.01410 -0.0430 0.7980 1.0000
3.250 0.5239 0.02423 0.01412 -0.0425 0.7831 1.0000
3.500 0.5512 0.02407 0.01410 -0.0420 0.7676 1.0000
3.750 0.5791 0.02388 0.01404 -0.0414 0.7514 1.0000
4.000 0.6001 0.02383 0.01413 -0.0396 0.7327 1.0000
4.250 0.6224 0.02372 0.01418 -0.0379 0.7126 1.0000
4.500 0.6492 0.02342 0.01401 -0.0367 0.6911 1.0000
4.750 0.6687 0.02331 0.01402 -0.0344 0.6656 1.0000
5.000 0.6884 0.02320 0.01401 -0.0320 0.6378 1.0000
5.250 0.7079 0.02313 0.01405 -0.0295 0.6072 1.0000
5.500 0.7260 0.02314 0.01410 -0.0269 0.5733 1.0000
5.750 0.7403 0.02328 0.01428 -0.0237 0.5344 1.0000
6.000 0.7524 0.02352 0.01447 -0.0202 0.4894 1.0000
6.250 0.7614 0.02391 0.01473 -0.0163 0.4362 1.0000
6.500 0.7672 0.02454 0.01510 -0.0120 0.3760 1.0000
6.750 0.7699 0.02545 0.01565 -0.0076 0.3167 1.0000
7.000 0.7710 0.02657 0.01643 -0.0033 0.2625 1.0000
7.250 0.7721 0.02781 0.01738 0.0007 0.2157 1.0000
7.500 0.7735 0.02916 0.01846 0.0045 0.1767 1.0000
7.750 0.7752 0.03055 0.01964 0.0083 0.1460 1.0000
8.000 0.7769 0.03199 0.02089 0.0119 0.1239 1.0000
8.250 0.7821 0.03343 0.02228 0.0151 0.1057 1.0000
8.500 0.7898 0.03491 0.02378 0.0178 0.0923 1.0000
8.750 0.8000 0.03641 0.02528 0.0201 0.0818 1.0000
9.000 0.8134 0.03798 0.02686 0.0219 0.0738 1.0000
9.250 0.8312 0.03964 0.02872 0.0233 0.0658 1.0000
9.500 0.8478 0.04141 0.03044 0.0245 0.0607 1.0000
9.750 0.8726 0.04369 0.03310 0.0250 0.0561 1.0000
10.000 0.8859 0.04567 0.03533 0.0266 0.0525 1.0000
10.250 0.8973 0.04773 0.03738 0.0280 0.0494 1.0000
10.500 0.9060 0.05049 0.04050 0.0299 0.0477 1.0000
10.750 0.9086 0.05332 0.04371 0.0324 0.0467 1.0000
11.000 0.9047 0.05632 0.04706 0.0351 0.0458 1.0000
11.250 0.8967 0.05939 0.05044 0.0376 0.0451 1.0000
11.500 0.8849 0.06261 0.05393 0.0397 0.0444 1.0000
11.750 0.8702 0.06612 0.05769 0.0413 0.0439 1.0000
12.000 0.8526 0.07017 0.06197 0.0420 0.0439 1.0000
12.250 0.8318 0.07482 0.06683 0.0417 0.0439 1.0000
12.500 0.8082 0.08027 0.07247 0.0402 0.0441 1.0000
12.750 0.7818 0.08701 0.07935 0.0373 0.0449 1.0000
13.000 0.7550 0.09483 0.08727 0.0330 0.0457 1.0000
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