SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7037-092-88 (sd7037-il) Reynolds number: 50,000 Max Cl/Cd: 39.14 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7037-il-50000-n5.txt Download as CSV file: xf-sd7037-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4012 0.08850 0.08174 -0.0383 1.0000 0.0519
-7.750 -0.4024 0.08532 0.07865 -0.0382 1.0000 0.0515
-7.500 -0.4034 0.08206 0.07547 -0.0385 1.0000 0.0511
-7.250 -0.4050 0.07870 0.07218 -0.0391 1.0000 0.0505
-7.000 -0.4069 0.07521 0.06874 -0.0399 1.0000 0.0498
-6.750 -0.4087 0.07152 0.06508 -0.0408 1.0000 0.0490
-6.500 -0.4097 0.06764 0.06119 -0.0417 1.0000 0.0482
-6.250 -0.4090 0.06361 0.05711 -0.0428 1.0000 0.0473
-6.000 -0.4061 0.05928 0.05267 -0.0439 1.0000 0.0463
-5.750 -0.4002 0.05484 0.04801 -0.0452 1.0000 0.0454
-5.500 -0.3908 0.05024 0.04310 -0.0464 1.0000 0.0445
-5.250 -0.3776 0.04601 0.03847 -0.0474 1.0000 0.0439
-5.000 -0.3612 0.04216 0.03415 -0.0479 1.0000 0.0437
-4.750 -0.3424 0.03885 0.03037 -0.0482 1.0000 0.0437
-4.500 -0.3219 0.03600 0.02707 -0.0481 1.0000 0.0441
-4.250 -0.3006 0.03371 0.02440 -0.0479 1.0000 0.0455
-4.000 -0.2783 0.03174 0.02201 -0.0476 1.0000 0.0482
-3.750 -0.2547 0.02991 0.01970 -0.0471 1.0000 0.0508
-3.500 -0.2313 0.02823 0.01768 -0.0464 1.0000 0.0530
-3.250 -0.2088 0.02693 0.01627 -0.0457 1.0000 0.0557
-3.000 -0.1861 0.02586 0.01503 -0.0449 1.0000 0.0600
-2.750 -0.1510 0.02482 0.01385 -0.0465 0.9945 0.0706
-2.500 -0.1130 0.02385 0.01269 -0.0485 0.9872 0.0909
-2.250 -0.0748 0.02271 0.01184 -0.0511 0.9800 0.1498
-2.000 -0.0360 0.02129 0.01129 -0.0541 0.9734 0.3095
-1.750 -0.0073 0.02016 0.01126 -0.0543 0.9647 0.5574
-1.500 0.0180 0.01945 0.01132 -0.0517 0.9562 0.8337
-1.250 0.0702 0.01937 0.01086 -0.0564 0.9464 1.0000
-1.000 0.1071 0.01957 0.01065 -0.0585 0.9349 1.0000
-0.750 0.1448 0.01977 0.01051 -0.0607 0.9239 1.0000
-0.500 0.1862 0.01995 0.01040 -0.0634 0.9141 1.0000
-0.250 0.2216 0.02010 0.01031 -0.0651 0.9018 1.0000
0.000 0.2564 0.02024 0.01025 -0.0665 0.8892 1.0000
0.250 0.2917 0.02036 0.01021 -0.0679 0.8767 1.0000
0.500 0.3264 0.02044 0.01014 -0.0690 0.8642 1.0000
0.750 0.3610 0.02048 0.01007 -0.0701 0.8517 1.0000
1.000 0.3956 0.02048 0.00997 -0.0710 0.8391 1.0000
1.250 0.4286 0.02048 0.00989 -0.0715 0.8256 1.0000
1.500 0.4596 0.02048 0.00984 -0.0717 0.8111 1.0000
1.750 0.4904 0.02047 0.00979 -0.0717 0.7963 1.0000
2.000 0.5210 0.02045 0.00973 -0.0717 0.7809 1.0000
2.250 0.5495 0.02048 0.00973 -0.0713 0.7642 1.0000
2.500 0.5782 0.02050 0.00976 -0.0709 0.7469 1.0000
2.750 0.6071 0.02052 0.00976 -0.0705 0.7293 1.0000
3.000 0.6362 0.02054 0.00977 -0.0701 0.7113 1.0000
3.250 0.6656 0.02056 0.00976 -0.0696 0.6931 1.0000
3.500 0.6925 0.02068 0.00990 -0.0689 0.6727 1.0000
3.750 0.7192 0.02083 0.01004 -0.0681 0.6519 1.0000
4.000 0.7470 0.02095 0.01012 -0.0674 0.6315 1.0000
4.250 0.7716 0.02123 0.01045 -0.0665 0.6085 1.0000
4.500 0.7980 0.02145 0.01064 -0.0656 0.5869 1.0000
4.750 0.8218 0.02180 0.01101 -0.0646 0.5631 1.0000
5.000 0.8467 0.02213 0.01131 -0.0636 0.5405 1.0000
5.250 0.8700 0.02255 0.01179 -0.0626 0.5164 1.0000
5.500 0.8934 0.02298 0.01221 -0.0616 0.4928 1.0000
5.750 0.9164 0.02346 0.01270 -0.0605 0.4692 1.0000
6.000 0.9386 0.02400 0.01330 -0.0594 0.4452 1.0000
6.250 0.9610 0.02455 0.01384 -0.0583 0.4223 1.0000
6.500 0.9821 0.02520 0.01454 -0.0572 0.3983 1.0000
6.750 1.0034 0.02585 0.01520 -0.0561 0.3759 1.0000
7.000 1.0236 0.02659 0.01603 -0.0549 0.3529 1.0000
7.250 1.0437 0.02736 0.01680 -0.0537 0.3316 1.0000
7.500 1.0629 0.02821 0.01774 -0.0525 0.3098 1.0000
7.750 1.0817 0.02909 0.01863 -0.0512 0.2898 1.0000
8.250 1.1170 0.03108 0.02083 -0.0485 0.2506 1.0000
8.500 1.1336 0.03216 0.02196 -0.0471 0.2329 1.0000
8.750 1.1491 0.03330 0.02313 -0.0457 0.2159 1.0000
9.000 1.1636 0.03455 0.02453 -0.0442 0.1991 1.0000
9.250 1.1765 0.03587 0.02600 -0.0425 0.1831 1.0000
9.500 1.1886 0.03728 0.02752 -0.0409 0.1683 1.0000
9.750 1.1986 0.03877 0.02913 -0.0390 0.1543 1.0000
10.000 1.2076 0.04039 0.03086 -0.0372 0.1415 1.0000
10.250 1.2134 0.04206 0.03260 -0.0350 0.1300 1.0000
10.500 1.2178 0.04384 0.03442 -0.0329 0.1195 1.0000
10.750 1.2191 0.04591 0.03670 -0.0308 0.1087 1.0000
11.000 1.2185 0.04820 0.03916 -0.0289 0.0990 1.0000
11.250 1.2150 0.05060 0.04166 -0.0273 0.0904 1.0000
11.500 1.2101 0.05320 0.04434 -0.0261 0.0828 1.0000
11.750 1.2045 0.05640 0.04776 -0.0254 0.0755 1.0000
12.000 1.1984 0.05951 0.05085 -0.0250 0.0701 1.0000
12.250 1.1920 0.06349 0.05514 -0.0250 0.0648 1.0000
12.500 1.1858 0.06733 0.05909 -0.0254 0.0608 1.0000
12.750 1.1797 0.07138 0.06320 -0.0261 0.0575 1.0000
13.000 1.1698 0.07660 0.06877 -0.0274 0.0549 1.0000
13.250 1.1592 0.08197 0.07438 -0.0291 0.0527 1.0000
13.500 1.1491 0.08742 0.07999 -0.0312 0.0510 1.0000
13.750 1.1427 0.09214 0.08475 -0.0331 0.0491 1.0000
14.000 1.1327 0.09795 0.09068 -0.0355 0.0480 1.0000
14.250 1.1143 0.10597 0.09897 -0.0398 0.0477 1.0000
14.500 1.0938 0.11497 0.10820 -0.0450 0.0476 1.0000
14.750 1.0730 0.12468 0.11808 -0.0506 0.0479 1.0000
15.000 1.0516 0.13532 0.12883 -0.0568 0.0483 1.0000
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Polar data table (+)
Polar graphs
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