N-10 (n10-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: N-10 (n10-il) Reynolds number: 50,000 Max Cl/Cd: 37.22 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n10-il-50000-n5.txt Download as CSV file: xf-n10-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3912 0.10419 0.09704 -0.0393 0.9999 0.0803
-10.750 -0.3821 0.10075 0.09361 -0.0382 0.9999 0.0788
-10.500 -0.3839 0.09730 0.09023 -0.0387 0.9999 0.0783
-10.250 -0.3893 0.09394 0.08697 -0.0392 0.9999 0.0781
-10.000 -0.3978 0.09074 0.08388 -0.0393 0.9999 0.0779
-9.750 -0.4078 0.08750 0.08076 -0.0395 0.9999 0.0776
-9.500 -0.4156 0.08385 0.07720 -0.0405 0.9999 0.0773
-9.250 -0.4233 0.08010 0.07352 -0.0413 0.9999 0.0767
-9.000 -0.4309 0.07620 0.06966 -0.0420 0.9999 0.0759
-8.750 -0.4380 0.07209 0.06555 -0.0427 0.9999 0.0751
-8.500 -0.4436 0.06780 0.06121 -0.0434 0.9999 0.0743
-8.250 -0.4466 0.06338 0.05666 -0.0441 0.9999 0.0737
-8.000 -0.4459 0.05908 0.05218 -0.0447 0.9999 0.0737
-7.750 -0.4411 0.05521 0.04806 -0.0452 0.9999 0.0749
-7.500 -0.4329 0.05132 0.04382 -0.0457 0.9999 0.0765
-7.250 -0.4211 0.04753 0.03957 -0.0462 0.9999 0.0774
-7.000 -0.4060 0.04418 0.03578 -0.0465 0.9999 0.0778
-6.750 -0.3731 0.04051 0.03145 -0.0496 0.9950 0.0787
-6.500 -0.3379 0.03753 0.02768 -0.0524 0.9892 0.0808
-6.250 -0.3040 0.03575 0.02583 -0.0548 0.9838 0.0843
-6.000 -0.2699 0.03403 0.02378 -0.0567 0.9775 0.0873
-5.750 -0.2339 0.03233 0.02166 -0.0587 0.9719 0.0897
-5.500 -0.1989 0.03091 0.01984 -0.0603 0.9655 0.0926
-5.250 -0.1633 0.02971 0.01838 -0.0619 0.9596 0.0965
-5.000 -0.1302 0.02885 0.01747 -0.0633 0.9525 0.1033
-4.750 -0.0938 0.02800 0.01638 -0.0649 0.9466 0.1108
-4.500 -0.0620 0.02723 0.01562 -0.0659 0.9390 0.1184
-4.250 -0.0231 0.02653 0.01488 -0.0681 0.9338 0.1329
-4.000 0.0066 0.02604 0.01449 -0.0688 0.9248 0.1557
-3.750 0.0464 0.02541 0.01404 -0.0713 0.9189 0.2084
-3.500 0.0777 0.02462 0.01367 -0.0724 0.9085 0.2959
-3.250 0.1128 0.02348 0.01337 -0.0738 0.8984 0.4599
-3.000 0.1561 0.02182 0.01307 -0.0738 0.8893 0.8835
-2.750 0.2078 0.02146 0.01231 -0.0778 0.8748 1.0001
-2.500 0.2438 0.02130 0.01182 -0.0788 0.8608 1.0001
-2.250 0.2757 0.02128 0.01153 -0.0793 0.8482 1.0001
-2.000 0.3076 0.02128 0.01130 -0.0799 0.8371 1.0001
-1.750 0.3437 0.02119 0.01099 -0.0810 0.8276 1.0001
-1.250 0.3993 0.02134 0.01082 -0.0806 0.8017 1.0001
-1.000 0.4279 0.02140 0.01074 -0.0804 0.7889 1.0001
-0.750 0.4569 0.02143 0.01065 -0.0803 0.7758 1.0001
-0.500 0.4856 0.02145 0.01056 -0.0800 0.7624 1.0001
-0.250 0.5135 0.02148 0.01050 -0.0797 0.7483 1.0001
0.000 0.5401 0.02154 0.01048 -0.0791 0.7331 1.0001
0.250 0.5659 0.02162 0.01048 -0.0784 0.7169 1.0001
0.500 0.5918 0.02170 0.01051 -0.0777 0.7002 1.0001
0.750 0.6183 0.02178 0.01051 -0.0771 0.6833 1.0001
1.000 0.6452 0.02185 0.01052 -0.0765 0.6661 1.0001
1.250 0.6724 0.02195 0.01054 -0.0760 0.6485 1.0001
1.500 0.6996 0.02208 0.01059 -0.0755 0.6308 1.0001
1.750 0.7266 0.02228 0.01070 -0.0750 0.6133 1.0001
2.000 0.7530 0.02254 0.01091 -0.0745 0.5962 1.0001
2.250 0.7783 0.02290 0.01121 -0.0740 0.5792 1.0001
2.500 0.8031 0.02329 0.01158 -0.0735 0.5627 1.0001
2.750 0.8281 0.02370 0.01198 -0.0730 0.5475 1.0001
3.000 0.8532 0.02413 0.01240 -0.0726 0.5338 1.0001
3.250 0.8775 0.02464 0.01295 -0.0721 0.5210 1.0001
3.500 0.9021 0.02516 0.01352 -0.0718 0.5094 1.0001
3.750 0.9275 0.02565 0.01403 -0.0714 0.4991 1.0001
4.000 0.9530 0.02609 0.01446 -0.0711 0.4885 1.0001
4.250 0.9757 0.02662 0.01507 -0.0704 0.4761 1.0001
4.500 0.9982 0.02709 0.01556 -0.0695 0.4626 1.0001
4.750 1.0199 0.02753 0.01600 -0.0685 0.4479 1.0001
5.000 1.0411 0.02801 0.01647 -0.0675 0.4329 1.0001
5.250 1.0626 0.02858 0.01710 -0.0666 0.4198 1.0001
5.500 1.0857 0.02917 0.01774 -0.0660 0.4090 1.0001
5.750 1.1082 0.02983 0.01848 -0.0653 0.3984 1.0001
6.000 1.1285 0.03060 0.01942 -0.0645 0.3878 1.0001
6.250 1.1502 0.03131 0.02025 -0.0637 0.3772 1.0001
6.500 1.1718 0.03200 0.02103 -0.0629 0.3659 1.0001
6.750 1.1884 0.03287 0.02210 -0.0616 0.3536 1.0001
7.000 1.2056 0.03373 0.02312 -0.0603 0.3412 1.0001
7.250 1.2234 0.03457 0.02413 -0.0591 0.3291 1.0001
7.500 1.2424 0.03537 0.02503 -0.0580 0.3172 1.0001
7.750 1.2550 0.03645 0.02635 -0.0562 0.3043 1.0001
8.000 1.2667 0.03757 0.02769 -0.0543 0.2915 1.0001
8.250 1.2781 0.03871 0.02902 -0.0524 0.2791 1.0001
8.500 1.2897 0.03982 0.03027 -0.0506 0.2677 1.0001
8.750 1.3016 0.04092 0.03155 -0.0488 0.2573 1.0001
9.000 1.3053 0.04241 0.03329 -0.0462 0.2468 1.0001
9.250 1.3073 0.04369 0.03472 -0.0435 0.2364 1.0001
9.500 1.3073 0.04489 0.03600 -0.0408 0.2255 1.0001
9.750 1.3046 0.04629 0.03748 -0.0382 0.2143 1.0001
10.000 1.2978 0.04836 0.03968 -0.0360 0.2026 1.0001
10.250 1.2909 0.05066 0.04205 -0.0343 0.1911 1.0001
10.500 1.2837 0.05325 0.04467 -0.0331 0.1798 1.0001
10.750 1.2757 0.05617 0.04758 -0.0322 0.1686 1.0001
11.000 1.2665 0.05944 0.05082 -0.0317 0.1577 1.0001
11.250 1.2557 0.06334 0.05486 -0.0317 0.1473 1.0001
11.500 1.2446 0.06762 0.05927 -0.0322 0.1379 1.0001
11.750 1.2351 0.07171 0.06338 -0.0326 0.1296 1.0001
12.000 1.2228 0.07670 0.06863 -0.0337 0.1211 1.0001
12.250 1.2112 0.08155 0.07357 -0.0348 0.1131 1.0001
12.500 1.1979 0.08700 0.07920 -0.0365 0.1043 1.0001
12.750 1.1841 0.09283 0.08519 -0.0384 0.0954 1.0001
13.000 1.1715 0.09852 0.09095 -0.0404 0.0866 1.0001
|
Polar data table (+)
Polar graphs
<< Back to N-10 (n10-il)