N-10 (n10-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-10 (n10-il) Reynolds number: 500,000 Max Cl/Cd: 95.34 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n10-il-500000.txt Download as CSV file: xf-n10-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3058 0.08501 0.08288 -0.0394 0.9999 0.0338
-11.000 -0.3072 0.08227 0.08017 -0.0388 0.9999 0.0345
-10.750 -0.3128 0.07918 0.07711 -0.0383 0.9999 0.0352
-10.500 -0.5830 0.03745 0.03426 -0.0716 0.9931 0.0265
-10.250 -0.5592 0.03464 0.03134 -0.0740 0.9893 0.0273
-10.000 -0.4453 0.07693 0.07487 -0.0365 0.9999 0.0342
-9.750 -0.4721 0.04351 0.04087 -0.0732 0.9874 0.0303
-9.500 -0.4705 0.02890 0.02503 -0.0803 0.9803 0.0305
-9.250 -0.4442 0.02538 0.02096 -0.0819 0.9757 0.0315
-9.000 -0.4149 0.02215 0.01723 -0.0838 0.9731 0.0328
-8.750 -0.3805 0.02080 0.01580 -0.0859 0.9715 0.0339
-8.500 -0.3509 0.01980 0.01470 -0.0865 0.9660 0.0348
-8.250 -0.3186 0.01864 0.01338 -0.0876 0.9617 0.0357
-8.000 -0.2844 0.01765 0.01222 -0.0890 0.9581 0.0371
-7.750 -0.2563 0.01673 0.01114 -0.0890 0.9497 0.0379
-7.500 -0.2243 0.01588 0.01013 -0.0897 0.9439 0.0386
-7.250 -0.1962 0.01531 0.00942 -0.0895 0.9343 0.0391
-7.000 -0.1685 0.01359 0.00759 -0.0896 0.9261 0.0406
-6.750 -0.1407 0.01294 0.00689 -0.0894 0.9155 0.0416
-6.500 -0.1132 0.01242 0.00630 -0.0892 0.9042 0.0425
-6.250 -0.0856 0.01195 0.00576 -0.0889 0.8937 0.0435
-5.750 -0.0311 0.01120 0.00485 -0.0882 0.8718 0.0460
-5.500 -0.0039 0.01095 0.00452 -0.0878 0.8605 0.0471
-5.250 0.0226 0.01048 0.00396 -0.0873 0.8494 0.0486
-5.000 0.0493 0.01012 0.00354 -0.0869 0.8381 0.0508
-4.750 0.0765 0.00990 0.00329 -0.0866 0.8272 0.0533
-4.500 0.1040 0.00973 0.00305 -0.0863 0.8167 0.0563
-4.250 0.1311 0.00949 0.00277 -0.0860 0.8057 0.0623
-4.000 0.1584 0.00927 0.00257 -0.0857 0.7939 0.0749
-3.750 0.1855 0.00898 0.00237 -0.0855 0.7826 0.1080
-3.500 0.2122 0.00864 0.00227 -0.0853 0.7716 0.1834
-3.250 0.2396 0.00850 0.00220 -0.0852 0.7596 0.2242
-3.000 0.2670 0.00836 0.00212 -0.0850 0.7466 0.2555
-2.500 0.3207 0.00789 0.00200 -0.0847 0.7202 0.3901
-2.250 0.3464 0.00751 0.00199 -0.0844 0.7064 0.5224
-2.000 0.3673 0.00681 0.00204 -0.0829 0.6929 0.7573
-1.750 0.3894 0.00651 0.00213 -0.0807 0.6795 0.9402
-1.500 0.4370 0.00659 0.00212 -0.0847 0.6644 0.9888
-1.250 0.4785 0.00671 0.00210 -0.0877 0.6495 1.0001
-1.000 0.5034 0.00681 0.00210 -0.0871 0.6356 1.0001
-0.750 0.5282 0.00693 0.00211 -0.0864 0.6201 1.0001
-0.500 0.5529 0.00707 0.00213 -0.0857 0.6027 1.0001
-0.250 0.5777 0.00720 0.00217 -0.0851 0.5817 1.0001
0.000 0.6022 0.00736 0.00220 -0.0844 0.5563 1.0001
0.250 0.6264 0.00755 0.00224 -0.0837 0.5199 1.0001
0.500 0.6489 0.00790 0.00232 -0.0827 0.4691 1.0001
0.750 0.6718 0.00829 0.00247 -0.0819 0.4317 1.0001
1.000 0.6961 0.00859 0.00263 -0.0813 0.4092 1.0001
1.250 0.7212 0.00885 0.00279 -0.0808 0.3951 1.0001
1.500 0.7467 0.00908 0.00294 -0.0805 0.3846 1.0001
1.750 0.7723 0.00930 0.00310 -0.0802 0.3749 1.0001
2.000 0.7984 0.00950 0.00326 -0.0799 0.3671 1.0001
2.250 0.8243 0.00971 0.00342 -0.0797 0.3600 1.0001
2.500 0.8502 0.00991 0.00360 -0.0795 0.3542 1.0001
2.750 0.8766 0.01008 0.00377 -0.0793 0.3485 1.0001
3.000 0.9024 0.01030 0.00395 -0.0791 0.3433 1.0001
3.250 0.9284 0.01051 0.00416 -0.0789 0.3389 1.0001
3.500 0.9550 0.01066 0.00434 -0.0788 0.3342 1.0001
3.750 0.9807 0.01087 0.00454 -0.0786 0.3288 1.0001
4.000 1.0063 0.01111 0.00477 -0.0784 0.3239 1.0001
4.250 1.0328 0.01124 0.00495 -0.0783 0.3189 1.0001
4.500 1.0584 0.01145 0.00516 -0.0781 0.3132 1.0001
4.750 1.0839 0.01166 0.00538 -0.0779 0.3067 1.0001
5.000 1.1096 0.01183 0.00557 -0.0777 0.2980 1.0001
5.250 1.1351 0.01202 0.00578 -0.0776 0.2894 1.0001
5.500 1.1598 0.01225 0.00599 -0.0772 0.2795 1.0001
5.750 1.1851 0.01243 0.00620 -0.0771 0.2661 1.0001
6.000 1.2092 0.01270 0.00642 -0.0767 0.2438 1.0001
6.250 1.2288 0.01332 0.00678 -0.0757 0.1957 1.0001
6.500 1.2458 0.01417 0.00740 -0.0743 0.1626 1.0001
6.750 1.2654 0.01479 0.00795 -0.0733 0.1486 1.0001
7.000 1.2848 0.01540 0.00851 -0.0722 0.1376 1.0001
7.250 1.3057 0.01587 0.00898 -0.0714 0.1285 1.0001
7.500 1.3260 0.01636 0.00948 -0.0705 0.1207 1.0001
7.750 1.3447 0.01695 0.01004 -0.0694 0.1101 1.0001
8.000 1.3639 0.01749 0.01054 -0.0684 0.0952 1.0001
8.250 1.3685 0.01891 0.01158 -0.0652 0.0467 1.0001
8.500 1.3705 0.02034 0.01286 -0.0614 0.0261 1.0001
8.750 1.3811 0.02128 0.01382 -0.0591 0.0223 1.0001
9.000 1.3909 0.02228 0.01489 -0.0568 0.0204 1.0001
9.250 1.4008 0.02331 0.01600 -0.0547 0.0193 1.0001
9.500 1.4110 0.02433 0.01711 -0.0528 0.0184 1.0001
9.750 1.4193 0.02552 0.01839 -0.0508 0.0177 1.0001
10.000 1.4257 0.02689 0.01984 -0.0488 0.0170 1.0001
10.250 1.4280 0.02864 0.02169 -0.0466 0.0164 1.0001
10.500 1.4246 0.03096 0.02412 -0.0443 0.0158 1.0001
10.750 1.4300 0.03268 0.02595 -0.0430 0.0155 1.0001
11.000 1.4340 0.03461 0.02798 -0.0419 0.0151 1.0001
11.250 1.4358 0.03681 0.03029 -0.0408 0.0148 1.0001
11.500 1.4360 0.03929 0.03288 -0.0399 0.0144 1.0001
11.750 1.4347 0.04201 0.03571 -0.0392 0.0142 1.0001
12.000 1.4322 0.04501 0.03881 -0.0387 0.0139 1.0001
12.250 1.4285 0.04827 0.04217 -0.0385 0.0137 1.0001
12.500 1.4234 0.05179 0.04580 -0.0384 0.0135 1.0001
12.750 1.4172 0.05559 0.04969 -0.0386 0.0133 1.0001
13.000 1.4096 0.05963 0.05384 -0.0389 0.0131 1.0001
13.250 1.4011 0.06388 0.05819 -0.0394 0.0130 1.0001
13.500 1.3920 0.06828 0.06268 -0.0399 0.0128 1.0001
13.750 1.3826 0.07266 0.06715 -0.0403 0.0126 1.0001
14.000 1.3747 0.07675 0.07130 -0.0405 0.0125 1.0001
14.250 1.3724 0.08059 0.07526 -0.0414 0.0124 1.0001
14.500 1.3698 0.08450 0.07928 -0.0424 0.0123 1.0001
14.750 1.3668 0.08846 0.08335 -0.0435 0.0122 1.0001
15.000 1.3637 0.09251 0.08751 -0.0446 0.0120 1.0001
15.250 1.3605 0.09664 0.09175 -0.0459 0.0119 1.0001
15.500 1.3573 0.10074 0.09595 -0.0471 0.0117 1.0001
15.750 1.3540 0.10492 0.10023 -0.0485 0.0115 1.0001
16.000 1.3507 0.10907 0.10447 -0.0499 0.0113 1.0001
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