N-10 (n10-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: N-10 (n10-il) Reynolds number: 50,000 Max Cl/Cd: 28.82 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n10-il-50000.txt Download as CSV file: xf-n10-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3694 0.11382 0.10680 -0.0244 0.9999 0.2337
-10.500 -0.3478 0.10905 0.10198 -0.0229 0.9999 0.2436
-10.250 -0.3755 0.10922 0.10235 -0.0241 0.9999 0.2490
-10.000 -0.3519 0.10430 0.09739 -0.0224 0.9999 0.2623
-9.750 -0.3426 0.10066 0.09380 -0.0213 0.9999 0.2720
-9.500 -0.3718 0.10088 0.09423 -0.0206 0.9999 0.2802
-9.250 -0.3499 0.09626 0.08960 -0.0190 0.9999 0.2934
-9.000 -0.3492 0.09338 0.08681 -0.0175 0.9999 0.3022
-8.750 -0.3794 0.09345 0.08709 -0.0146 0.9999 0.3119
-8.500 -0.3607 0.08931 0.08296 -0.0129 0.9999 0.3239
-8.000 -0.4089 0.08768 0.08169 -0.0076 0.9999 0.3446
-7.750 -0.3963 0.08425 0.07827 -0.0042 0.9999 0.3587
-7.500 -0.3988 0.08197 0.07608 -0.0010 0.9999 0.3738
-7.250 -0.4088 0.08025 0.07446 0.0023 0.9999 0.3908
-7.000 -0.4279 0.07909 0.07343 0.0050 0.9999 0.4091
-6.750 -0.4115 0.07572 0.07008 0.0097 0.9999 0.4303
-6.500 -0.4320 0.07498 0.06945 0.0132 0.9999 0.4571
-6.250 -0.4168 0.07172 0.06623 0.0179 0.9999 0.4794
-6.000 -0.3688 0.05033 0.04291 -0.0378 0.9999 0.1861
-5.750 -0.3441 0.04551 0.03756 -0.0401 0.9999 0.1716
-5.500 -0.3208 0.04256 0.03425 -0.0410 0.9999 0.1678
-5.250 -0.2957 0.03996 0.03120 -0.0420 0.9999 0.1678
-5.000 -0.2696 0.03765 0.02843 -0.0428 0.9999 0.1679
-4.750 -0.2431 0.03564 0.02597 -0.0435 0.9999 0.1680
-4.500 -0.2165 0.03400 0.02385 -0.0439 0.9999 0.1697
-4.250 -0.1936 0.03290 0.02272 -0.0438 0.9999 0.1759
-4.000 -0.1687 0.03202 0.02150 -0.0438 0.9999 0.1842
-3.750 -0.1447 0.03113 0.02054 -0.0437 0.9999 0.1923
-3.500 -0.1203 0.03042 0.01967 -0.0436 0.9999 0.2047
-3.250 -0.0968 0.02988 0.01916 -0.0434 0.9999 0.2260
-3.000 -0.0706 0.02926 0.01856 -0.0435 0.9999 0.2611
-2.750 -0.0400 0.02811 0.01803 -0.0442 0.9999 0.3623
-2.500 -0.0287 0.02516 0.01756 -0.0395 0.9999 1.0001
-2.250 0.0105 0.02607 0.01771 -0.0427 0.9944 1.0001
-2.000 0.0662 0.02711 0.01822 -0.0490 0.9783 1.0001
-1.750 0.1182 0.02803 0.01877 -0.0545 0.9622 1.0001
-1.500 0.1690 0.02884 0.01928 -0.0595 0.9458 1.0001
-1.250 0.2204 0.02955 0.01974 -0.0645 0.9292 1.0001
-1.000 0.2649 0.03009 0.02011 -0.0680 0.9109 1.0001
-0.750 0.3064 0.03055 0.02043 -0.0708 0.8914 1.0001
-0.500 0.3529 0.03089 0.02065 -0.0742 0.8723 1.0001
-0.250 0.4034 0.03103 0.02071 -0.0779 0.8538 1.0001
0.000 0.4449 0.03119 0.02081 -0.0800 0.8332 1.0001
0.250 0.4863 0.03124 0.02082 -0.0818 0.8121 1.0001
0.500 0.5331 0.03102 0.02056 -0.0840 0.7934 1.0001
0.750 0.5768 0.03075 0.02027 -0.0856 0.7755 1.0001
1.000 0.6179 0.03048 0.01998 -0.0866 0.7583 1.0001
1.250 0.6404 0.03100 0.02048 -0.0855 0.7362 1.0001
1.500 0.6719 0.03112 0.02059 -0.0854 0.7187 1.0001
1.750 0.7021 0.03135 0.02081 -0.0852 0.7027 1.0001
2.000 0.7298 0.03179 0.02126 -0.0849 0.6880 1.0001
2.250 0.7567 0.03231 0.02180 -0.0845 0.6744 1.0001
2.500 0.7870 0.03264 0.02212 -0.0845 0.6626 1.0001
2.750 0.8166 0.03303 0.02254 -0.0844 0.6515 1.0001
3.000 0.8310 0.03460 0.02419 -0.0833 0.6389 1.0001
3.250 0.8482 0.03603 0.02568 -0.0825 0.6277 1.0001
3.500 0.8847 0.03602 0.02570 -0.0830 0.6197 1.0001
3.750 0.8882 0.03854 0.02833 -0.0813 0.6077 1.0001
4.000 0.9045 0.03993 0.02982 -0.0802 0.5962 1.0001
4.250 0.9365 0.03958 0.02952 -0.0794 0.5825 1.0001
4.500 0.9680 0.03906 0.02904 -0.0783 0.5673 1.0001
4.750 0.9984 0.03871 0.02876 -0.0773 0.5526 1.0001
5.000 1.0340 0.03821 0.02830 -0.0770 0.5401 1.0001
5.250 1.0528 0.03907 0.02929 -0.0757 0.5268 1.0001
5.500 1.0695 0.04010 0.03048 -0.0742 0.5133 1.0001
5.750 1.0903 0.04075 0.03126 -0.0728 0.4991 1.0001
6.000 1.1133 0.04124 0.03187 -0.0716 0.4845 1.0001
6.250 1.1390 0.04155 0.03229 -0.0705 0.4690 1.0001
6.500 1.1713 0.04134 0.03214 -0.0698 0.4515 1.0001
6.750 1.1990 0.04160 0.03244 -0.0688 0.4326 1.0001
7.000 1.2107 0.04317 0.03417 -0.0666 0.4136 1.0001
7.250 1.2262 0.04478 0.03589 -0.0648 0.3958 1.0001
7.500 1.2401 0.04668 0.03795 -0.0631 0.3798 1.0001
7.750 1.2517 0.04876 0.04017 -0.0613 0.3655 1.0001
8.000 1.2664 0.05067 0.04220 -0.0598 0.3524 1.0001
8.250 1.2933 0.05193 0.04352 -0.0594 0.3400 1.0001
8.500 1.2486 0.05799 0.04997 -0.0542 0.3341 1.0001
8.750 1.2741 0.05911 0.05119 -0.0534 0.3228 1.0001
9.000 1.1952 0.06828 0.06050 -0.0481 0.3223 1.0001
9.750 1.3742 0.05475 0.04700 -0.0469 0.2500 1.0001
10.000 1.3744 0.05421 0.04650 -0.0432 0.2328 1.0001
10.250 1.2885 0.06768 0.06055 -0.0384 0.2517 1.0001
10.500 1.2534 0.07426 0.06724 -0.0369 0.2501 1.0001
11.250 1.3492 0.06078 0.05226 -0.0265 0.1374 1.0001
11.500 1.3238 0.06554 0.05746 -0.0246 0.1327 1.0001
11.750 1.1828 0.09186 0.08518 -0.0346 0.1947 1.0001
12.000 1.2978 0.07448 0.06668 -0.0227 0.1191 1.0001
12.250 1.2755 0.08011 0.07258 -0.0229 0.1165 1.0001
12.500 1.1256 0.11129 0.10466 -0.0397 0.1659 1.0001
12.750 1.1195 0.11504 0.10838 -0.0399 0.1512 1.0001
13.500 0.9718 0.17219 0.16499 -0.0702 0.1796 1.0001
13.750 0.9579 0.18055 0.17329 -0.0749 0.1805 1.0001
14.000 0.9519 0.18744 0.18017 -0.0784 0.1807 1.0001
14.250 0.9574 0.19375 0.18649 -0.0801 0.1791 1.0001
14.500 0.6702 0.18065 0.17376 -0.0578 0.2781 1.0001
14.750 0.6749 0.18381 0.17699 -0.0580 0.2634 1.0001
|
Polar data table (+)
Polar graphs
<< Back to N-10 (n10-il)