N-10 (n10-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 200,000 Max Cl/Cd: 68.62 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n10-il-200000.txt Download as CSV file: xf-n10-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: N-10
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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3656 0.09609 0.09250 -0.0354 0.9999 0.0634
-10.500 -0.3695 0.09294 0.08940 -0.0366 0.9999 0.0657
-10.250 -0.3944 0.08957 0.08616 -0.0402 0.9999 0.0681
-10.000 -0.3338 0.07792 0.07486 -0.0369 0.9999 0.0707
-9.750 -0.3338 0.07673 0.07372 -0.0332 0.9999 0.0720
-9.500 -0.4716 0.07943 0.07613 -0.0448 0.9999 0.0689
-9.250 -0.4723 0.07549 0.07235 -0.0404 0.9999 0.0699
-9.000 -0.4722 0.07427 0.07118 -0.0361 0.9999 0.0706
-8.750 -0.4630 0.07260 0.06953 -0.0344 0.9988 0.0720
-8.500 -0.4363 0.06899 0.06586 -0.0390 0.9948 0.0760
-8.250 -0.4120 0.05726 0.05370 -0.0560 0.9863 0.0837
-8.000 -0.3822 0.05498 0.05146 -0.0578 0.9835 0.0859
-7.750 -0.3553 0.04836 0.04407 -0.0664 0.9747 0.0970
-7.500 -0.3250 0.04514 0.04105 -0.0682 0.9721 0.0992
-7.250 -0.3012 0.03156 0.02603 -0.0722 0.9650 0.0660
-7.000 -0.2681 0.02759 0.02152 -0.0743 0.9609 0.0636
-6.750 -0.2290 0.02512 0.01861 -0.0768 0.9581 0.0644
-6.500 -0.1970 0.02310 0.01622 -0.0777 0.9511 0.0644
-6.250 -0.1565 0.02134 0.01412 -0.0800 0.9466 0.0651
-6.000 -0.1113 0.02007 0.01258 -0.0832 0.9438 0.0674
-5.750 -0.0772 0.01919 0.01151 -0.0840 0.9360 0.0687
-5.500 -0.0383 0.01751 0.00975 -0.0861 0.9318 0.0708
-5.250 0.0023 0.01647 0.00874 -0.0884 0.9284 0.0739
-5.000 0.0319 0.01586 0.00810 -0.0884 0.9185 0.0779
-4.750 0.0698 0.01503 0.00723 -0.0899 0.9135 0.0830
-4.500 0.0975 0.01431 0.00658 -0.0896 0.9028 0.0896
-4.250 0.1285 0.01359 0.00589 -0.0899 0.8943 0.1012
-4.000 0.1581 0.01274 0.00521 -0.0900 0.8850 0.1371
-3.750 0.1848 0.01205 0.00498 -0.0897 0.8734 0.2508
-3.500 0.2122 0.01156 0.00473 -0.0894 0.8622 0.3257
-3.250 0.2391 0.01097 0.00456 -0.0891 0.8523 0.4458
-3.000 0.2598 0.01027 0.00454 -0.0873 0.8402 0.6329
-2.750 0.2919 0.00964 0.00467 -0.0861 0.8306 0.9352
-2.500 0.3570 0.00957 0.00442 -0.0935 0.8219 1.0001
-2.250 0.3813 0.00961 0.00432 -0.0927 0.8094 1.0001
-2.000 0.4061 0.00966 0.00423 -0.0919 0.7973 1.0001
-1.750 0.4311 0.00970 0.00414 -0.0911 0.7856 1.0001
-1.500 0.4564 0.00975 0.00405 -0.0904 0.7737 1.0001
-1.250 0.4808 0.00980 0.00400 -0.0895 0.7601 1.0001
-1.000 0.5056 0.00985 0.00396 -0.0888 0.7464 1.0001
-0.750 0.5306 0.00990 0.00392 -0.0880 0.7326 1.0001
-0.500 0.5558 0.00995 0.00388 -0.0873 0.7180 1.0001
-0.250 0.5811 0.01001 0.00384 -0.0866 0.7023 1.0001
0.000 0.6063 0.01009 0.00382 -0.0859 0.6853 1.0001
0.250 0.6314 0.01020 0.00380 -0.0852 0.6670 1.0001
0.500 0.6562 0.01035 0.00382 -0.0844 0.6460 1.0001
0.750 0.6805 0.01054 0.00387 -0.0836 0.6221 1.0001
1.000 0.7042 0.01077 0.00395 -0.0826 0.5937 1.0001
1.250 0.7274 0.01101 0.00404 -0.0816 0.5615 1.0001
1.500 0.7504 0.01128 0.00414 -0.0806 0.5282 1.0001
1.750 0.7735 0.01158 0.00427 -0.0798 0.4985 1.0001
2.000 0.7970 0.01192 0.00444 -0.0790 0.4763 1.0001
2.250 0.8212 0.01228 0.00466 -0.0784 0.4596 1.0001
2.500 0.8457 0.01264 0.00491 -0.0779 0.4465 1.0001
2.750 0.8705 0.01302 0.00518 -0.0775 0.4353 1.0001
3.000 0.8959 0.01334 0.00548 -0.0772 0.4254 1.0001
3.250 0.9212 0.01374 0.00580 -0.0769 0.4170 1.0001
3.500 0.9468 0.01405 0.00612 -0.0767 0.4087 1.0001
3.750 0.9722 0.01444 0.00646 -0.0764 0.4009 1.0001
4.000 0.9972 0.01475 0.00679 -0.0761 0.3922 1.0001
4.250 1.0227 0.01514 0.00716 -0.0759 0.3852 1.0001
4.500 1.0479 0.01544 0.00753 -0.0757 0.3782 1.0001
4.750 1.0736 0.01589 0.00791 -0.0755 0.3719 1.0001
5.000 1.0981 0.01615 0.00832 -0.0751 0.3648 1.0001
5.250 1.1230 0.01654 0.00870 -0.0749 0.3578 1.0001
5.500 1.1471 0.01686 0.00913 -0.0745 0.3502 1.0001
5.750 1.1711 0.01723 0.00951 -0.0740 0.3419 1.0001
6.000 1.1931 0.01748 0.00989 -0.0732 0.3312 1.0001
6.250 1.2141 0.01776 0.01023 -0.0723 0.3185 1.0001
6.500 1.2341 0.01802 0.01054 -0.0711 0.3041 1.0001
6.750 1.2536 0.01828 0.01089 -0.0699 0.2884 1.0001
7.000 1.2722 0.01854 0.01121 -0.0686 0.2689 1.0001
7.250 1.2900 0.01889 0.01158 -0.0672 0.2453 1.0001
7.500 1.3060 0.01941 0.01203 -0.0656 0.2171 1.0001
7.750 1.3191 0.02018 0.01265 -0.0637 0.1931 1.0001
8.000 1.3317 0.02104 0.01344 -0.0617 0.1769 1.0001
8.250 1.3414 0.02195 0.01430 -0.0592 0.1644 1.0001
8.500 1.3513 0.02290 0.01523 -0.0569 0.1530 1.0001
8.750 1.3631 0.02377 0.01615 -0.0550 0.1419 1.0001
9.000 1.3737 0.02473 0.01715 -0.0530 0.1291 1.0001
9.250 1.3814 0.02589 0.01830 -0.0509 0.1112 1.0001
9.500 1.3850 0.02750 0.01966 -0.0484 0.0653 1.0001
9.750 1.3771 0.02999 0.02194 -0.0451 0.0469 1.0001
10.000 1.3756 0.03213 0.02413 -0.0426 0.0409 1.0001
10.250 1.3729 0.03450 0.02656 -0.0405 0.0375 1.0001
10.500 1.3724 0.03680 0.02898 -0.0389 0.0353 1.0001
10.750 1.3724 0.03916 0.03147 -0.0376 0.0334 1.0001
11.000 1.3699 0.04187 0.03429 -0.0365 0.0319 1.0001
11.250 1.3632 0.04515 0.03767 -0.0357 0.0308 1.0001
11.500 1.3536 0.04889 0.04150 -0.0350 0.0300 1.0001
11.750 1.3510 0.05202 0.04478 -0.0347 0.0294 1.0001
12.000 1.3474 0.05535 0.04825 -0.0345 0.0288 1.0001
12.250 1.3434 0.05881 0.05182 -0.0345 0.0282 1.0001
12.500 1.3395 0.06230 0.05542 -0.0345 0.0277 1.0001
12.750 1.3361 0.06579 0.05901 -0.0346 0.0272 1.0001
13.000 1.3333 0.06922 0.06253 -0.0347 0.0267 1.0001
13.250 1.3313 0.07257 0.06595 -0.0348 0.0262 1.0001
13.500 1.3303 0.07579 0.06921 -0.0349 0.0256 1.0001
13.750 1.3304 0.07872 0.07217 -0.0346 0.0250 1.0001
14.000 1.3348 0.08075 0.07420 -0.0331 0.0243 1.0001
14.250 1.3338 0.08430 0.07793 -0.0338 0.0240 1.0001
14.500 1.3331 0.08781 0.08159 -0.0344 0.0236 1.0001
14.750 1.3325 0.09130 0.08523 -0.0349 0.0233 1.0001
15.000 1.3313 0.09495 0.08904 -0.0355 0.0231 1.0001
15.250 1.3282 0.09895 0.09320 -0.0364 0.0229 1.0001
15.500 1.3239 0.10327 0.09770 -0.0376 0.0227 1.0001
15.750 1.3179 0.10798 0.10259 -0.0392 0.0226 1.0001
16.000 1.3102 0.11312 0.10792 -0.0412 0.0226 1.0001
16.250 1.3004 0.11877 0.11377 -0.0437 0.0225 1.0001
16.500 1.2887 0.12497 0.12018 -0.0468 0.0226 1.0001
16.750 1.2752 0.13178 0.12719 -0.0505 0.0226 1.0001
17.000 1.2599 0.13920 0.13482 -0.0547 0.0228 1.0001
17.250 1.2423 0.14744 0.14327 -0.0598 0.0229 1.0001
17.500 1.2229 0.15646 0.15249 -0.0654 0.0231 1.0001
17.750 1.2009 0.16665 0.16287 -0.0720 0.0234 1.0001
18.000 1.1757 0.17843 0.17483 -0.0797 0.0238 1.0001
18.250 1.1502 0.19117 0.18769 -0.0876 0.0243 1.0001
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