SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7037-092-88 (sd7037-il) Reynolds number: 200,000 Max Cl/Cd: 74.75 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7037-il-200000.txt Download as CSV file: xf-sd7037-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SD7037-092-88
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3853 0.09760 0.09408 -0.0371 1.0000 0.0447
-8.750 -0.3896 0.09447 0.09101 -0.0393 1.0000 0.0448
-8.500 -0.3954 0.09148 0.08809 -0.0405 1.0000 0.0449
-8.250 -0.3858 0.08652 0.08314 -0.0364 1.0000 0.0463
-8.000 -0.3825 0.08426 0.08092 -0.0348 1.0000 0.0471
-7.750 -0.3859 0.08213 0.07885 -0.0334 1.0000 0.0479
-7.500 -0.3972 0.08026 0.07706 -0.0313 1.0000 0.0485
-7.250 -0.4103 0.07825 0.07513 -0.0296 1.0000 0.0489
-7.000 -0.4192 0.07580 0.07273 -0.0292 1.0000 0.0497
-6.750 -0.4270 0.07291 0.06988 -0.0296 1.0000 0.0506
-6.500 -0.4323 0.06958 0.06656 -0.0309 1.0000 0.0518
-6.250 -0.4341 0.06573 0.06268 -0.0331 1.0000 0.0533
-6.000 -0.4315 0.06017 0.05654 -0.0416 1.0000 0.0564
-5.750 -0.4294 0.05408 0.05061 -0.0412 0.9998 0.0578
-5.500 -0.4009 0.05116 0.04774 -0.0438 0.9961 0.0598
-5.250 -0.3676 0.04727 0.04366 -0.0486 0.9915 0.0643
-5.000 -0.3313 0.04158 0.03755 -0.0552 0.9864 0.0723
-4.750 -0.2953 0.03826 0.03377 -0.0597 0.9812 0.0844
-4.500 -0.2539 0.02861 0.02274 -0.0617 0.9772 0.0454
-4.250 -0.2166 0.02318 0.01652 -0.0635 0.9745 0.0359
-4.000 -0.1778 0.02171 0.01473 -0.0654 0.9705 0.0350
-3.750 -0.1435 0.01979 0.01251 -0.0666 0.9649 0.0349
-3.500 -0.1045 0.01793 0.01047 -0.0686 0.9614 0.0357
-3.250 -0.0629 0.01669 0.00926 -0.0714 0.9585 0.0396
-3.000 -0.0317 0.01598 0.00849 -0.0719 0.9505 0.0435
-2.750 0.0092 0.01486 0.00740 -0.0744 0.9466 0.0506
-2.500 0.0466 0.01362 0.00646 -0.0763 0.9413 0.1137
-2.250 0.0816 0.01262 0.00613 -0.0782 0.9348 0.2771
-2.000 0.1196 0.01150 0.00602 -0.0805 0.9309 0.5299
-1.750 0.1446 0.01092 0.00599 -0.0793 0.9219 0.6910
-1.500 0.1748 0.01045 0.00584 -0.0784 0.9164 0.8170
-1.250 0.2094 0.01016 0.00566 -0.0784 0.9093 0.9276
-1.000 0.2755 0.00984 0.00520 -0.0857 0.9062 1.0000
-0.750 0.3068 0.00966 0.00489 -0.0861 0.8976 1.0000
-0.500 0.3339 0.00951 0.00462 -0.0855 0.8866 1.0000
-0.250 0.3591 0.00940 0.00440 -0.0846 0.8741 1.0000
0.000 0.3850 0.00929 0.00419 -0.0837 0.8617 1.0000
0.250 0.4111 0.00919 0.00399 -0.0829 0.8488 1.0000
0.500 0.4373 0.00910 0.00381 -0.0821 0.8349 1.0000
0.750 0.4634 0.00904 0.00366 -0.0813 0.8199 1.0000
1.000 0.4896 0.00901 0.00353 -0.0805 0.8037 1.0000
1.250 0.5158 0.00899 0.00342 -0.0798 0.7865 1.0000
1.500 0.5423 0.00901 0.00333 -0.0791 0.7687 1.0000
1.750 0.5683 0.00908 0.00329 -0.0784 0.7492 1.0000
2.000 0.5942 0.00917 0.00328 -0.0777 0.7286 1.0000
2.250 0.6203 0.00930 0.00330 -0.0770 0.7085 1.0000
2.500 0.6459 0.00945 0.00336 -0.0764 0.6865 1.0000
2.750 0.6715 0.00963 0.00342 -0.0757 0.6651 1.0000
3.000 0.6970 0.00982 0.00352 -0.0751 0.6426 1.0000
3.250 0.7223 0.01004 0.00364 -0.0744 0.6205 1.0000
3.500 0.7475 0.01026 0.00379 -0.0737 0.5977 1.0000
3.750 0.7725 0.01051 0.00393 -0.0731 0.5749 1.0000
4.000 0.7974 0.01076 0.00412 -0.0724 0.5515 1.0000
4.250 0.8220 0.01106 0.00432 -0.0717 0.5285 1.0000
4.500 0.8465 0.01134 0.00454 -0.0710 0.5044 1.0000
4.750 0.8708 0.01165 0.00478 -0.0703 0.4807 1.0000
5.000 0.8948 0.01199 0.00503 -0.0696 0.4566 1.0000
5.250 0.9187 0.01233 0.00534 -0.0689 0.4321 1.0000
5.500 0.9422 0.01272 0.00564 -0.0681 0.4082 1.0000
5.750 0.9655 0.01311 0.00598 -0.0674 0.3836 1.0000
6.000 0.9886 0.01353 0.00636 -0.0666 0.3595 1.0000
6.250 1.0111 0.01401 0.00675 -0.0657 0.3365 1.0000
6.500 1.0339 0.01446 0.00718 -0.0650 0.3125 1.0000
6.750 1.0558 0.01499 0.00763 -0.0641 0.2899 1.0000
7.000 1.0777 0.01550 0.00812 -0.0632 0.2672 1.0000
7.250 1.0990 0.01608 0.00864 -0.0623 0.2463 1.0000
7.500 1.1204 0.01664 0.00920 -0.0613 0.2259 1.0000
7.750 1.1409 0.01729 0.00979 -0.0603 0.2075 1.0000
8.000 1.1612 0.01795 0.01045 -0.0593 0.1896 1.0000
8.250 1.1813 0.01857 0.01108 -0.0583 0.1705 1.0000
8.500 1.1999 0.01927 0.01171 -0.0571 0.1512 1.0000
8.750 1.2190 0.01994 0.01238 -0.0560 0.1326 1.0000
9.000 1.2374 0.02065 0.01312 -0.0548 0.1156 1.0000
9.250 1.2544 0.02147 0.01393 -0.0535 0.1007 1.0000
9.500 1.2699 0.02240 0.01483 -0.0519 0.0857 1.0000
9.750 1.2842 0.02341 0.01584 -0.0502 0.0688 1.0000
10.000 1.2909 0.02492 0.01723 -0.0476 0.0508 1.0000
10.250 1.2919 0.02672 0.01901 -0.0440 0.0396 1.0000
10.500 1.2969 0.02820 0.02061 -0.0412 0.0346 1.0000
10.750 1.2942 0.03032 0.02274 -0.0379 0.0318 1.0000
11.000 1.3000 0.03194 0.02452 -0.0356 0.0297 1.0000
11.250 1.3045 0.03369 0.02638 -0.0334 0.0280 1.0000
11.500 1.3081 0.03559 0.02835 -0.0315 0.0267 1.0000
11.750 1.3092 0.03798 0.03078 -0.0296 0.0254 1.0000
12.000 1.3132 0.04031 0.03325 -0.0281 0.0243 1.0000
12.250 1.3187 0.04240 0.03551 -0.0267 0.0235 1.0000
12.500 1.3236 0.04476 0.03804 -0.0255 0.0229 1.0000
12.750 1.3270 0.04734 0.04079 -0.0244 0.0222 1.0000
13.000 1.3298 0.05007 0.04373 -0.0235 0.0219 1.0000
13.250 1.3307 0.05305 0.04689 -0.0229 0.0215 1.0000
13.500 1.3300 0.05628 0.05031 -0.0224 0.0212 1.0000
13.750 1.3267 0.05983 0.05406 -0.0223 0.0209 1.0000
14.000 1.3212 0.06379 0.05824 -0.0225 0.0208 1.0000
14.250 1.3132 0.06818 0.06285 -0.0232 0.0207 1.0000
14.500 1.3027 0.07306 0.06795 -0.0244 0.0206 1.0000
14.750 1.2891 0.07861 0.07375 -0.0264 0.0207 1.0000
15.000 1.2727 0.08487 0.08026 -0.0291 0.0207 1.0000
15.250 1.2544 0.09183 0.08746 -0.0325 0.0208 1.0000
15.500 1.2328 0.09991 0.09579 -0.0371 0.0211 1.0000
15.750 1.2051 0.10981 0.10596 -0.0434 0.0214 1.0000
16.000 1.1745 0.12129 0.11770 -0.0511 0.0218 1.0000
16.250 1.1394 0.13503 0.13166 -0.0605 0.0223 1.0000
16.500 1.0939 0.15334 0.15014 -0.0728 0.0234 1.0000
16.750 1.0514 0.17296 0.16978 -0.0844 0.0246 1.0000
17.000 1.0084 0.20023 0.19690 -0.0972 0.0314 1.0000
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Polar data table (+)
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