SA7038 (sa7038-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SA7038 (sa7038-il) Reynolds number: 100,000 Max Cl/Cd: 56.72 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sa7038-il-100000-n5.txt Download as CSV file: xf-sa7038-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3647 0.11146 0.10634 -0.0302 1.0000 0.0496
-9.500 -0.3706 0.10904 0.10401 -0.0339 1.0000 0.0508
-9.250 -0.3738 0.10625 0.10130 -0.0365 1.0000 0.0511
-8.750 -0.3616 0.09810 0.09323 -0.0348 1.0000 0.0531
-8.500 -0.3584 0.09519 0.09037 -0.0348 1.0000 0.0536
-8.250 -0.3573 0.09228 0.08752 -0.0346 1.0000 0.0543
-8.000 -0.3597 0.08952 0.08483 -0.0346 1.0000 0.0545
-7.750 -0.3018 0.07440 0.07009 -0.0346 1.0000 0.0362
-7.500 -0.3105 0.07153 0.06730 -0.0333 1.0000 0.0348
-7.250 -0.3889 0.07996 0.07551 -0.0334 1.0000 0.0367
-7.000 -0.3960 0.07708 0.07271 -0.0328 1.0000 0.0350
-6.750 -0.4043 0.07354 0.06923 -0.0336 1.0000 0.0332
-6.500 -0.4119 0.06491 0.06048 -0.0411 1.0000 0.0281
-6.250 -0.4126 0.06158 0.05714 -0.0409 1.0000 0.0276
-6.000 -0.3881 0.05564 0.05102 -0.0474 0.9943 0.0267
-5.750 -0.3619 0.04934 0.04443 -0.0537 0.9878 0.0258
-5.500 -0.3317 0.04300 0.03765 -0.0596 0.9823 0.0250
-5.250 -0.3033 0.03782 0.03194 -0.0633 0.9759 0.0244
-5.000 -0.2699 0.03322 0.02670 -0.0667 0.9713 0.0239
-4.750 -0.2395 0.02982 0.02271 -0.0684 0.9655 0.0239
-4.500 -0.2062 0.02710 0.01945 -0.0701 0.9604 0.0242
-4.250 -0.1693 0.02515 0.01702 -0.0721 0.9568 0.0259
-4.000 -0.1391 0.02376 0.01522 -0.0725 0.9499 0.0280
-3.750 -0.1034 0.02228 0.01345 -0.0740 0.9453 0.0286
-3.500 -0.0696 0.02063 0.01170 -0.0752 0.9405 0.0299
-3.250 -0.0384 0.01961 0.01061 -0.0759 0.9335 0.0315
-3.000 -0.0009 0.01870 0.00957 -0.0777 0.9292 0.0344
-2.750 0.0283 0.01803 0.00874 -0.0778 0.9209 0.0385
-2.500 0.0637 0.01718 0.00793 -0.0792 0.9156 0.0546
-2.250 0.0920 0.01624 0.00739 -0.0795 0.9072 0.1346
-2.000 0.1237 0.01502 0.00716 -0.0809 0.9012 0.3632
-1.750 0.1487 0.01435 0.00704 -0.0801 0.8918 0.5251
-1.500 0.1772 0.01377 0.00688 -0.0793 0.8853 0.6749
-1.250 0.1989 0.01335 0.00675 -0.0768 0.8752 0.8113
-1.000 0.2564 0.01292 0.00630 -0.0817 0.8703 1.0000
-0.750 0.2848 0.01287 0.00605 -0.0817 0.8594 1.0000
-0.500 0.3123 0.01285 0.00584 -0.0814 0.8478 1.0000
-0.250 0.3405 0.01282 0.00564 -0.0812 0.8363 1.0000
0.000 0.3690 0.01278 0.00545 -0.0810 0.8245 1.0000
0.250 0.3975 0.01274 0.00527 -0.0808 0.8121 1.0000
0.500 0.4255 0.01272 0.00512 -0.0805 0.7988 1.0000
0.750 0.4532 0.01271 0.00500 -0.0802 0.7846 1.0000
1.000 0.4806 0.01272 0.00491 -0.0797 0.7696 1.0000
1.250 0.5079 0.01275 0.00484 -0.0793 0.7539 1.0000
1.500 0.5352 0.01279 0.00478 -0.0789 0.7377 1.0000
1.750 0.5624 0.01285 0.00474 -0.0784 0.7209 1.0000
2.000 0.5896 0.01292 0.00473 -0.0780 0.7035 1.0000
2.250 0.6161 0.01304 0.00475 -0.0774 0.6849 1.0000
2.500 0.6423 0.01317 0.00480 -0.0768 0.6655 1.0000
2.750 0.6686 0.01333 0.00485 -0.0763 0.6463 1.0000
3.000 0.6943 0.01351 0.00499 -0.0757 0.6260 1.0000
3.250 0.7199 0.01372 0.00512 -0.0751 0.6058 1.0000
3.500 0.7454 0.01395 0.00527 -0.0744 0.5855 1.0000
3.750 0.7705 0.01420 0.00546 -0.0738 0.5645 1.0000
4.000 0.7954 0.01447 0.00569 -0.0731 0.5437 1.0000
4.250 0.8200 0.01476 0.00593 -0.0724 0.5220 1.0000
4.500 0.8444 0.01508 0.00619 -0.0717 0.5006 1.0000
4.750 0.8685 0.01542 0.00648 -0.0710 0.4788 1.0000
5.000 0.8923 0.01578 0.00683 -0.0702 0.4574 1.0000
5.250 0.9160 0.01616 0.00718 -0.0695 0.4358 1.0000
5.500 0.9393 0.01656 0.00755 -0.0687 0.4146 1.0000
5.750 0.9622 0.01699 0.00796 -0.0679 0.3929 1.0000
6.000 0.9849 0.01745 0.00839 -0.0670 0.3715 1.0000
6.250 1.0071 0.01794 0.00890 -0.0661 0.3499 1.0000
6.500 1.0291 0.01845 0.00940 -0.0652 0.3292 1.0000
6.750 1.0507 0.01899 0.00994 -0.0643 0.3085 1.0000
7.000 1.0717 0.01958 0.01052 -0.0633 0.2895 1.0000
7.250 1.0928 0.02017 0.01118 -0.0623 0.2699 1.0000
7.500 1.1130 0.02081 0.01184 -0.0613 0.2514 1.0000
7.750 1.1325 0.02151 0.01254 -0.0602 0.2333 1.0000
8.000 1.1519 0.02221 0.01329 -0.0591 0.2147 1.0000
8.250 1.1701 0.02297 0.01407 -0.0578 0.1963 1.0000
8.500 1.1873 0.02381 0.01491 -0.0565 0.1793 1.0000
8.750 1.2044 0.02465 0.01584 -0.0551 0.1627 1.0000
9.000 1.2206 0.02554 0.01680 -0.0537 0.1473 1.0000
9.250 1.2357 0.02650 0.01782 -0.0522 0.1326 1.0000
9.500 1.2494 0.02754 0.01892 -0.0505 0.1193 1.0000
9.750 1.2616 0.02865 0.02009 -0.0487 0.1070 1.0000
10.000 1.2709 0.02983 0.02131 -0.0465 0.0961 1.0000
10.250 1.2783 0.03114 0.02268 -0.0442 0.0868 1.0000
10.500 1.2864 0.03248 0.02415 -0.0421 0.0778 1.0000
10.750 1.2916 0.03403 0.02582 -0.0399 0.0702 1.0000
11.000 1.2955 0.03571 0.02760 -0.0378 0.0636 1.0000
11.250 1.2989 0.03756 0.02958 -0.0358 0.0579 1.0000
11.500 1.3000 0.03955 0.03163 -0.0341 0.0514 1.0000
11.750 1.3033 0.04152 0.03376 -0.0328 0.0444 1.0000
12.000 1.3005 0.04405 0.03631 -0.0316 0.0393 1.0000
12.250 1.3019 0.04642 0.03890 -0.0308 0.0339 1.0000
12.500 1.2960 0.04963 0.04218 -0.0303 0.0308 1.0000
12.750 1.2909 0.05301 0.04576 -0.0300 0.0279 1.0000
13.000 1.2847 0.05672 0.04967 -0.0301 0.0256 1.0000
13.250 1.2768 0.06084 0.05396 -0.0307 0.0241 1.0000
13.500 1.2659 0.06560 0.05885 -0.0320 0.0229 1.0000
13.750 1.2525 0.07098 0.06435 -0.0337 0.0220 1.0000
14.000 1.2437 0.07599 0.06956 -0.0353 0.0211 1.0000
14.250 1.2343 0.08130 0.07509 -0.0372 0.0204 1.0000
14.500 1.2234 0.08713 0.08114 -0.0396 0.0195 1.0000
14.750 1.2126 0.09315 0.08734 -0.0423 0.0190 1.0000
15.000 1.2013 0.09949 0.09386 -0.0454 0.0185 1.0000
15.250 1.1894 0.10620 0.10074 -0.0488 0.0181 1.0000
15.500 1.1774 0.11316 0.10787 -0.0525 0.0177 1.0000
15.750 1.1655 0.12034 0.11522 -0.0564 0.0176 1.0000
16.000 1.1528 0.12801 0.12303 -0.0608 0.0173 1.0000
16.250 1.1396 0.13609 0.13128 -0.0654 0.0173 1.0000
16.500 1.1251 0.14485 0.14019 -0.0705 0.0173 1.0000
16.750 1.1061 0.15556 0.15109 -0.0769 0.0177 1.0000
17.000 1.0781 0.17011 0.16579 -0.0854 0.0186 1.0000
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