ONERA HOR04 AIRFOIL (hor04-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: ONERA HOR04 AIRFOIL (hor04-il) Reynolds number: 200,000 Max Cl/Cd: 54.8 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-hor04-il-200000.txt Download as CSV file: xf-hor04-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: ONERA HOR04 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
------ -------- --------- --------- -------- -------- --------
-6.750 -0.5511 0.08319 0.07965 -0.0068 1.0000 0.0254
-6.500 -0.5537 0.07537 0.07193 -0.0063 1.0000 0.0266
-6.250 -0.5459 0.07213 0.06870 -0.0048 1.0000 0.0284
-6.000 -0.5272 0.06780 0.06433 -0.0087 1.0000 0.0304
-5.750 -0.5035 0.06289 0.05931 -0.0141 1.0000 0.0321
-5.500 -0.4758 0.05790 0.05414 -0.0197 1.0000 0.0341
-5.250 -0.4323 0.05404 0.04984 -0.0267 1.0000 0.0373
-5.000 -0.3999 0.05111 0.04650 -0.0298 1.0000 0.0378
-4.750 -0.3798 0.04314 0.03849 -0.0333 1.0000 0.0393
-4.500 -0.3566 0.03957 0.03489 -0.0348 1.0000 0.0413
-4.250 -0.3281 0.03644 0.03158 -0.0367 1.0000 0.0447
-4.000 -0.2880 0.03662 0.03098 -0.0376 1.0000 0.0512
-3.750 -0.2632 0.02993 0.02436 -0.0405 1.0000 0.0549
-2.250 -0.0701 0.01603 0.00835 -0.0433 1.0000 0.0422
-2.000 -0.0399 0.01482 0.00689 -0.0429 1.0000 0.0392
-1.750 -0.0109 0.01335 0.00536 -0.0429 1.0000 0.0404
-1.500 0.0177 0.01246 0.00452 -0.0430 1.0000 0.0475
-1.250 0.0468 0.01145 0.00353 -0.0432 1.0000 0.0547
-1.000 0.0759 0.01074 0.00287 -0.0435 1.0000 0.0697
-0.750 0.1038 0.00847 0.00241 -0.0445 1.0000 0.5779
-0.500 0.1182 0.00715 0.00199 -0.0405 1.0000 1.0000
-0.250 0.1461 0.00718 0.00189 -0.0405 1.0000 1.0000
0.000 0.1738 0.00723 0.00186 -0.0405 1.0000 1.0000
0.250 0.2014 0.00729 0.00187 -0.0406 1.0000 1.0000
0.500 0.2288 0.00736 0.00192 -0.0405 1.0000 1.0000
0.750 0.2561 0.00744 0.00202 -0.0405 1.0000 1.0000
1.000 0.2831 0.00754 0.00215 -0.0405 1.0000 1.0000
1.250 0.3100 0.00767 0.00233 -0.0405 1.0000 1.0000
1.500 0.3367 0.00784 0.00257 -0.0406 1.0000 1.0000
1.750 0.3786 0.00787 0.00272 -0.0438 0.9861 1.0000
2.000 0.4264 0.00788 0.00273 -0.0470 0.9033 1.0000
2.250 0.4472 0.00816 0.00285 -0.0443 0.8210 1.0000
2.500 0.4667 0.00867 0.00294 -0.0414 0.7064 1.0000
2.750 0.4884 0.00963 0.00311 -0.0396 0.5314 1.0000
3.000 0.5117 0.01261 0.00399 -0.0402 0.0982 1.0000
3.250 0.5397 0.01344 0.00479 -0.0402 0.0793 1.0000
3.500 0.5670 0.01440 0.00572 -0.0403 0.0687 1.0000
3.750 0.5944 0.01527 0.00663 -0.0401 0.0626 1.0000
4.000 0.6207 0.01711 0.00839 -0.0399 0.0571 1.0000
4.250 0.6487 0.01776 0.00921 -0.0396 0.0510 1.0000
4.500 0.6754 0.01973 0.01124 -0.0394 0.0452 1.0000
4.750 0.7036 0.02105 0.01289 -0.0390 0.0396 1.0000
5.000 0.7316 0.02324 0.01538 -0.0385 0.0365 1.0000
5.250 0.7587 0.02578 0.01821 -0.0382 0.0345 1.0000
5.500 0.7933 0.03546 0.02947 -0.0355 0.0635 1.0000
5.750 0.8168 0.03889 0.03312 -0.0354 0.0603 1.0000
6.000 0.8317 0.04765 0.04187 -0.0366 0.0573 1.0000
6.250 0.8582 0.04735 0.04252 -0.0353 0.0503 1.0000
6.500 0.8761 0.05115 0.04657 -0.0354 0.0477 1.0000
6.750 0.8918 0.05530 0.05077 -0.0355 0.0460 1.0000
7.000 0.8958 0.06531 0.06081 -0.0369 0.0444 1.0000
7.250 0.9064 0.06923 0.06516 -0.0372 0.0441 1.0000
7.500 0.9160 0.07381 0.07036 -0.0404 0.0413 1.0000
7.750 0.9190 0.08005 0.07679 -0.0439 0.0397 1.0000
8.000 0.9188 0.08635 0.08320 -0.0481 0.0387 1.0000
8.250 0.9158 0.09296 0.08986 -0.0538 0.0381 1.0000
8.500 0.9082 0.09913 0.09601 -0.0596 0.0380 1.0000
8.750 0.9040 0.10465 0.10150 -0.0635 0.0373 1.0000
9.000 0.9019 0.10962 0.10645 -0.0662 0.0363 1.0000
9.250 0.9038 0.11322 0.11005 -0.0665 0.0345 1.0000
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Polar data table (+)
Polar graphs
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