S7075 (9%) (s7075-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: S7075 (9%) (s7075-il) Reynolds number: 100,000 Max Cl/Cd: 57.66 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s7075-il-100000-n5.txt Download as CSV file: xf-s7075-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S7075 (9%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3880 0.09199 0.08702 -0.0366 1.0000 0.0340
-8.250 -0.3924 0.08919 0.08430 -0.0359 1.0000 0.0327
-8.000 -0.4015 0.08638 0.08157 -0.0350 1.0000 0.0314
-7.500 -0.4472 0.07720 0.07259 -0.0377 1.0000 0.0271
-7.250 -0.4530 0.07411 0.06954 -0.0375 1.0000 0.0268
-7.000 -0.4574 0.07065 0.06610 -0.0380 1.0000 0.0265
-6.750 -0.4600 0.06674 0.06217 -0.0390 1.0000 0.0262
-6.500 -0.4601 0.06235 0.05772 -0.0405 1.0000 0.0259
-6.250 -0.4538 0.05681 0.05202 -0.0436 0.9991 0.0258
-6.000 -0.4285 0.04905 0.04380 -0.0510 0.9944 0.0263
-5.750 -0.4028 0.04305 0.03724 -0.0558 0.9898 0.0267
-5.500 -0.3746 0.03823 0.03187 -0.0593 0.9859 0.0267
-5.250 -0.3440 0.03427 0.02734 -0.0621 0.9828 0.0266
-5.000 -0.3156 0.03106 0.02359 -0.0635 0.9787 0.0266
-4.750 -0.2844 0.02843 0.02039 -0.0650 0.9752 0.0268
-4.500 -0.2507 0.02631 0.01776 -0.0665 0.9722 0.0273
-4.250 -0.2185 0.02433 0.01554 -0.0678 0.9693 0.0280
-4.000 -0.1899 0.02300 0.01408 -0.0683 0.9646 0.0294
-3.750 -0.1573 0.02208 0.01300 -0.0695 0.9606 0.0322
-3.500 -0.1221 0.02116 0.01188 -0.0709 0.9574 0.0357
-3.250 -0.0928 0.02011 0.01080 -0.0714 0.9526 0.0385
-3.000 -0.0615 0.01935 0.00998 -0.0722 0.9476 0.0437
-2.750 -0.0262 0.01863 0.00920 -0.0737 0.9438 0.0569
-2.500 0.0045 0.01787 0.00865 -0.0746 0.9386 0.0936
-2.250 0.0348 0.01706 0.00830 -0.0755 0.9330 0.1888
-2.000 0.0698 0.01631 0.00808 -0.0773 0.9291 0.3341
-1.750 0.0961 0.01566 0.00803 -0.0771 0.9225 0.4968
-1.500 0.1226 0.01509 0.00809 -0.0761 0.9168 0.6753
-1.250 0.1503 0.01483 0.00808 -0.0748 0.9120 0.8164
-1.000 0.1763 0.01465 0.00790 -0.0735 0.9039 0.8961
-0.750 0.2327 0.01442 0.00755 -0.0790 0.9009 1.0000
-0.500 0.2629 0.01441 0.00739 -0.0795 0.8928 1.0000
-0.250 0.2979 0.01435 0.00718 -0.0807 0.8862 1.0000
0.000 0.3266 0.01434 0.00705 -0.0808 0.8770 1.0000
0.250 0.3624 0.01423 0.00683 -0.0821 0.8705 1.0000
0.500 0.3892 0.01422 0.00674 -0.0818 0.8597 1.0000
0.750 0.4193 0.01415 0.00660 -0.0820 0.8500 1.0000
1.000 0.4526 0.01401 0.00641 -0.0826 0.8414 1.0000
1.250 0.4798 0.01396 0.00632 -0.0822 0.8289 1.0000
1.500 0.5077 0.01390 0.00622 -0.0819 0.8162 1.0000
1.750 0.5361 0.01383 0.00613 -0.0816 0.8027 1.0000
2.000 0.5647 0.01376 0.00604 -0.0814 0.7881 1.0000
2.250 0.5939 0.01368 0.00594 -0.0812 0.7724 1.0000
2.500 0.6242 0.01359 0.00582 -0.0812 0.7556 1.0000
2.750 0.6526 0.01356 0.00579 -0.0809 0.7356 1.0000
3.000 0.6826 0.01352 0.00570 -0.0808 0.7144 1.0000
3.250 0.7113 0.01355 0.00568 -0.0805 0.6905 1.0000
3.500 0.7396 0.01364 0.00572 -0.0802 0.6649 1.0000
3.750 0.7669 0.01380 0.00579 -0.0797 0.6375 1.0000
4.000 0.7929 0.01402 0.00592 -0.0790 0.6085 1.0000
4.250 0.8180 0.01430 0.00611 -0.0782 0.5778 1.0000
4.500 0.8421 0.01463 0.00636 -0.0773 0.5456 1.0000
4.750 0.8655 0.01501 0.00663 -0.0763 0.5124 1.0000
5.000 0.8883 0.01543 0.00693 -0.0753 0.4790 1.0000
5.250 0.9104 0.01589 0.00729 -0.0742 0.4442 1.0000
5.500 0.9316 0.01640 0.00771 -0.0730 0.4085 1.0000
5.750 0.9524 0.01696 0.00814 -0.0717 0.3720 1.0000
6.000 0.9724 0.01759 0.00862 -0.0705 0.3351 1.0000
6.250 0.9922 0.01824 0.00915 -0.0692 0.2989 1.0000
6.500 1.0114 0.01896 0.00974 -0.0679 0.2637 1.0000
6.750 1.0302 0.01973 0.01040 -0.0667 0.2297 1.0000
7.000 1.0488 0.02054 0.01110 -0.0654 0.1972 1.0000
7.250 1.0667 0.02142 0.01185 -0.0641 0.1668 1.0000
7.500 1.0844 0.02235 0.01268 -0.0628 0.1404 1.0000
7.750 1.1012 0.02334 0.01360 -0.0613 0.1192 1.0000
8.000 1.1181 0.02434 0.01459 -0.0599 0.1028 1.0000
8.250 1.1338 0.02541 0.01565 -0.0583 0.0904 1.0000
8.500 1.1482 0.02656 0.01677 -0.0566 0.0806 1.0000
8.750 1.1635 0.02762 0.01792 -0.0549 0.0723 1.0000
9.000 1.1763 0.02886 0.01923 -0.0530 0.0669 1.0000
9.250 1.1894 0.03003 0.02053 -0.0510 0.0626 1.0000
9.500 1.2008 0.03131 0.02187 -0.0490 0.0592 1.0000
9.750 1.2112 0.03281 0.02339 -0.0469 0.0565 1.0000
10.000 1.2251 0.03413 0.02491 -0.0452 0.0534 1.0000
10.250 1.2376 0.03549 0.02641 -0.0436 0.0506 1.0000
10.500 1.2489 0.03695 0.02796 -0.0419 0.0484 1.0000
10.750 1.2604 0.03868 0.02979 -0.0403 0.0468 1.0000
11.000 1.2744 0.04070 0.03192 -0.0391 0.0454 1.0000
11.250 1.2874 0.04261 0.03411 -0.0377 0.0443 1.0000
11.500 1.2981 0.04470 0.03648 -0.0362 0.0430 1.0000
11.750 1.3055 0.04684 0.03888 -0.0345 0.0416 1.0000
12.000 1.3101 0.04903 0.04130 -0.0328 0.0403 1.0000
12.250 1.3127 0.05124 0.04372 -0.0312 0.0391 1.0000
12.500 1.3144 0.05363 0.04629 -0.0297 0.0381 1.0000
12.750 1.3149 0.05635 0.04919 -0.0284 0.0374 1.0000
13.000 1.3137 0.05937 0.05240 -0.0274 0.0368 1.0000
13.250 1.3103 0.06287 0.05613 -0.0265 0.0362 1.0000
13.500 1.3018 0.06705 0.06051 -0.0260 0.0358 1.0000
13.750 1.2870 0.07150 0.06527 -0.0260 0.0356 1.0000
14.000 1.2695 0.07656 0.07064 -0.0268 0.0355 1.0000
14.250 1.2499 0.08232 0.07667 -0.0286 0.0353 1.0000
14.500 1.2280 0.08891 0.08352 -0.0315 0.0353 1.0000
14.750 1.2044 0.09639 0.09124 -0.0355 0.0353 1.0000
15.000 1.1790 0.10499 0.10001 -0.0407 0.0355 1.0000
15.250 1.1515 0.11492 0.11012 -0.0472 0.0356 1.0000
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Polar data table (+)
Polar graphs
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