SA7038 (sa7038-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 200,000 Max Cl/Cd: 76.54 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sa7038-il-200000.txt Download as CSV file: xf-sa7038-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: SA7038
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3525 0.08751 0.08417 -0.0341 1.0000 0.0438
-7.750 -0.3635 0.08528 0.08203 -0.0339 1.0000 0.0448
-7.500 -0.3807 0.08370 0.08055 -0.0320 1.0000 0.0452
-7.250 -0.4004 0.08184 0.07878 -0.0317 1.0000 0.0457
-7.000 -0.4122 0.07877 0.07576 -0.0346 1.0000 0.0461
-6.750 -0.4190 0.07510 0.07205 -0.0377 1.0000 0.0464
-6.500 -0.4221 0.07162 0.06848 -0.0393 1.0000 0.0466
-6.250 -0.4296 0.06565 0.06250 -0.0400 1.0000 0.0473
-6.000 -0.4187 0.06289 0.05985 -0.0384 0.9984 0.0485
-5.750 -0.3915 0.05964 0.05658 -0.0418 0.9945 0.0505
-5.500 -0.3598 0.05452 0.05130 -0.0487 0.9890 0.0550
-5.250 -0.3210 0.04662 0.04292 -0.0593 0.9838 0.0616
-5.000 -0.2939 0.04456 0.04090 -0.0610 0.9782 0.0668
-4.750 -0.2568 0.03935 0.03523 -0.0670 0.9731 0.0758
-4.500 -0.2215 0.03661 0.03233 -0.0702 0.9690 0.0816
-4.250 -0.1798 0.02857 0.02277 -0.0720 0.9629 0.0471
-4.000 -0.1408 0.02392 0.01743 -0.0737 0.9598 0.0354
-3.750 -0.1010 0.02091 0.01405 -0.0761 0.9574 0.0341
-3.500 -0.0701 0.01925 0.01212 -0.0764 0.9507 0.0341
-3.250 -0.0306 0.01804 0.01070 -0.0784 0.9465 0.0350
-3.000 0.0104 0.01636 0.00901 -0.0810 0.9438 0.0393
-2.750 0.0427 0.01549 0.00812 -0.0817 0.9366 0.0424
-2.500 0.0835 0.01452 0.00710 -0.0840 0.9322 0.0492
-2.250 0.1241 0.01283 0.00614 -0.0867 0.9291 0.2132
-2.000 0.1505 0.01196 0.00601 -0.0868 0.9199 0.4074
-1.750 0.1824 0.01102 0.00590 -0.0872 0.9153 0.6358
-1.500 0.2014 0.01049 0.00587 -0.0842 0.9056 0.7917
-1.250 0.2448 0.01004 0.00557 -0.0857 0.9019 0.9430
-1.000 0.2973 0.00979 0.00516 -0.0905 0.8958 1.0000
-0.750 0.3267 0.00963 0.00483 -0.0903 0.8869 1.0000
-0.500 0.3516 0.00953 0.00461 -0.0894 0.8752 1.0000
-0.250 0.3775 0.00944 0.00440 -0.0886 0.8637 1.0000
0.000 0.4039 0.00934 0.00419 -0.0878 0.8524 1.0000
0.250 0.4305 0.00925 0.00398 -0.0871 0.8407 1.0000
0.500 0.4570 0.00918 0.00380 -0.0864 0.8283 1.0000
0.750 0.4831 0.00914 0.00366 -0.0856 0.8144 1.0000
1.000 0.5090 0.00913 0.00356 -0.0848 0.7991 1.0000
1.250 0.5349 0.00914 0.00348 -0.0841 0.7826 1.0000
1.500 0.5610 0.00917 0.00342 -0.0834 0.7654 1.0000
1.750 0.5872 0.00922 0.00337 -0.0827 0.7478 1.0000
2.000 0.6135 0.00930 0.00334 -0.0821 0.7301 1.0000
2.250 0.6393 0.00942 0.00337 -0.0815 0.7105 1.0000
2.500 0.6652 0.00955 0.00340 -0.0808 0.6908 1.0000
2.750 0.6911 0.00971 0.00346 -0.0802 0.6713 1.0000
3.000 0.7165 0.00989 0.00357 -0.0796 0.6499 1.0000
3.250 0.7420 0.01009 0.00366 -0.0789 0.6294 1.0000
3.500 0.7672 0.01030 0.00380 -0.0783 0.6071 1.0000
3.750 0.7923 0.01054 0.00393 -0.0776 0.5857 1.0000
4.000 0.8173 0.01078 0.00413 -0.0770 0.5631 1.0000
4.250 0.8420 0.01106 0.00432 -0.0763 0.5413 1.0000
4.500 0.8666 0.01133 0.00453 -0.0756 0.5187 1.0000
4.750 0.8909 0.01164 0.00476 -0.0750 0.4961 1.0000
5.000 0.9149 0.01197 0.00503 -0.0742 0.4731 1.0000
5.250 0.9388 0.01230 0.00532 -0.0735 0.4494 1.0000
5.500 0.9623 0.01267 0.00561 -0.0728 0.4266 1.0000
5.750 0.9857 0.01304 0.00594 -0.0720 0.4035 1.0000
6.000 1.0089 0.01345 0.00632 -0.0712 0.3809 1.0000
6.250 1.0316 0.01389 0.00669 -0.0704 0.3586 1.0000
6.500 1.0543 0.01433 0.00711 -0.0696 0.3362 1.0000
6.750 1.0762 0.01484 0.00755 -0.0687 0.3150 1.0000
7.000 1.0982 0.01531 0.00804 -0.0678 0.2923 1.0000
7.250 1.1192 0.01588 0.00853 -0.0668 0.2710 1.0000
7.500 1.1404 0.01641 0.00906 -0.0659 0.2490 1.0000
7.750 1.1605 0.01704 0.00962 -0.0648 0.2292 1.0000
8.000 1.1810 0.01762 0.01023 -0.0638 0.2092 1.0000
8.250 1.2001 0.01831 0.01089 -0.0626 0.1904 1.0000
8.500 1.2188 0.01903 0.01159 -0.0614 0.1726 1.0000
8.750 1.2373 0.01973 0.01232 -0.0601 0.1546 1.0000
9.000 1.2543 0.02055 0.01312 -0.0587 0.1380 1.0000
9.250 1.2696 0.02148 0.01402 -0.0571 0.1225 1.0000
9.500 1.2830 0.02253 0.01502 -0.0552 0.1074 1.0000
9.750 1.2960 0.02357 0.01612 -0.0533 0.0933 1.0000
10.000 1.3057 0.02468 0.01723 -0.0509 0.0812 1.0000
10.250 1.3137 0.02583 0.01836 -0.0484 0.0703 1.0000
10.500 1.3256 0.02672 0.01933 -0.0466 0.0604 1.0000
10.750 1.3344 0.02790 0.02061 -0.0444 0.0526 1.0000
11.000 1.3362 0.02962 0.02233 -0.0417 0.0467 1.0000
11.250 1.3436 0.03101 0.02385 -0.0398 0.0401 1.0000
11.500 1.3419 0.03322 0.02614 -0.0372 0.0345 1.0000
11.750 1.3410 0.03538 0.02835 -0.0352 0.0291 1.0000
12.000 1.3384 0.03797 0.03109 -0.0332 0.0255 1.0000
12.250 1.3391 0.04026 0.03352 -0.0318 0.0229 1.0000
12.500 1.3351 0.04317 0.03651 -0.0306 0.0213 1.0000
12.750 1.3281 0.04689 0.04031 -0.0292 0.0201 1.0000
13.000 1.3292 0.04965 0.04329 -0.0285 0.0192 1.0000
13.250 1.3285 0.05279 0.04662 -0.0280 0.0184 1.0000
13.500 1.3266 0.05616 0.05018 -0.0278 0.0177 1.0000
13.750 1.3243 0.05971 0.05390 -0.0278 0.0173 1.0000
14.000 1.3201 0.06357 0.05795 -0.0281 0.0168 1.0000
14.250 1.3146 0.06775 0.06232 -0.0288 0.0164 1.0000
14.500 1.3078 0.07227 0.06702 -0.0299 0.0162 1.0000
14.750 1.2996 0.07716 0.07210 -0.0314 0.0160 1.0000
15.000 1.2894 0.08257 0.07772 -0.0334 0.0158 1.0000
15.250 1.2771 0.08857 0.08393 -0.0359 0.0158 1.0000
15.500 1.2634 0.09513 0.09071 -0.0391 0.0158 1.0000
15.750 1.2474 0.10243 0.09824 -0.0430 0.0158 1.0000
16.000 1.2295 0.11049 0.10653 -0.0477 0.0159 1.0000
16.250 1.2087 0.11970 0.11597 -0.0533 0.0162 1.0000
16.500 1.1856 0.13003 0.12652 -0.0600 0.0164 1.0000
16.750 1.1566 0.14265 0.13938 -0.0684 0.0169 1.0000
17.000 1.1185 0.15924 0.15617 -0.0794 0.0179 1.0000
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