USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: USA 40 AIRFOIL (usa40-il) Reynolds number: 50,000 Max Cl/Cd: 35.33 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-usa40-il-50000-n5.txt Download as CSV file: xf-usa40-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: USA 40 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2990 0.09980 0.09244 -0.0395 1.0000 0.0862
-8.500 -0.3045 0.09678 0.08953 -0.0396 1.0000 0.0850
-8.250 -0.3132 0.09387 0.08673 -0.0394 1.0000 0.0841
-7.750 -0.3769 0.08523 0.07840 -0.0414 1.0000 0.0797
-7.500 -0.3873 0.08212 0.07539 -0.0415 1.0000 0.0795
-7.250 -0.3975 0.07860 0.07193 -0.0424 1.0000 0.0793
-7.000 -0.4068 0.07472 0.06808 -0.0438 1.0000 0.0790
-6.750 -0.4143 0.07065 0.06400 -0.0454 1.0000 0.0787
-6.500 -0.3938 0.06356 0.05666 -0.0548 0.9918 0.0782
-6.250 -0.3658 0.05636 0.04904 -0.0648 0.9826 0.0779
-6.000 -0.3351 0.05013 0.04225 -0.0729 0.9732 0.0779
-5.750 -0.3004 0.04509 0.03655 -0.0795 0.9645 0.0789
-5.500 -0.2619 0.04181 0.03285 -0.0846 0.9571 0.0810
-5.250 -0.2286 0.03991 0.03082 -0.0872 0.9471 0.0834
-5.000 -0.1885 0.03747 0.02799 -0.0911 0.9392 0.0856
-4.750 -0.1509 0.03525 0.02535 -0.0940 0.9291 0.0878
-4.500 -0.1114 0.03332 0.02292 -0.0967 0.9194 0.0909
-4.250 -0.0715 0.03195 0.02154 -0.0994 0.9100 0.0955
-4.000 -0.0358 0.03078 0.02020 -0.1009 0.8987 0.1008
-3.750 0.0072 0.02941 0.01865 -0.1035 0.8907 0.1065
-3.500 0.0387 0.02858 0.01782 -0.1041 0.8781 0.1144
-3.250 0.0760 0.02762 0.01685 -0.1055 0.8684 0.1251
-3.000 0.1088 0.02686 0.01611 -0.1062 0.8564 0.1392
-2.750 0.1406 0.02621 0.01551 -0.1068 0.8437 0.1594
-2.500 0.1793 0.02536 0.01472 -0.1084 0.8343 0.1938
-2.250 0.2085 0.02466 0.01419 -0.1086 0.8200 0.2396
-2.000 0.2392 0.02394 0.01378 -0.1091 0.8066 0.3013
-1.750 0.2720 0.02330 0.01340 -0.1095 0.7949 0.3774
-1.500 0.3004 0.02282 0.01322 -0.1090 0.7813 0.4568
-1.250 0.3230 0.02254 0.01336 -0.1069 0.7667 0.5555
-1.000 0.3438 0.02243 0.01348 -0.1040 0.7528 0.6488
-0.750 0.3671 0.02230 0.01333 -0.1016 0.7398 0.7160
-0.500 0.3899 0.02214 0.01309 -0.0994 0.7259 0.7650
-0.250 0.4106 0.02198 0.01287 -0.0971 0.7108 0.8076
0.000 0.4318 0.02173 0.01257 -0.0947 0.6963 0.8510
0.250 0.4592 0.02140 0.01217 -0.0936 0.6821 0.9035
0.500 0.4980 0.02120 0.01177 -0.0952 0.6668 1.0000
0.750 0.5298 0.02132 0.01164 -0.0959 0.6521 1.0000
1.000 0.5592 0.02156 0.01166 -0.0963 0.6365 1.0000
1.250 0.5884 0.02182 0.01171 -0.0966 0.6212 1.0000
1.500 0.6178 0.02208 0.01178 -0.0969 0.6069 1.0000
1.750 0.6479 0.02233 0.01180 -0.0971 0.5938 1.0000
2.000 0.6757 0.02267 0.01200 -0.0972 0.5795 1.0000
2.250 0.7028 0.02306 0.01227 -0.0971 0.5655 1.0000
2.500 0.7308 0.02342 0.01248 -0.0971 0.5532 1.0000
2.750 0.7592 0.02376 0.01268 -0.0971 0.5415 1.0000
3.000 0.7850 0.02423 0.01308 -0.0969 0.5288 1.0000
3.250 0.8125 0.02464 0.01337 -0.0968 0.5181 1.0000
3.500 0.8393 0.02508 0.01373 -0.0967 0.5074 1.0000
3.750 0.8652 0.02560 0.01420 -0.0965 0.4969 1.0000
4.000 0.8930 0.02600 0.01448 -0.0964 0.4879 1.0000
4.250 0.9175 0.02664 0.01513 -0.0960 0.4778 1.0000
4.500 0.9455 0.02706 0.01544 -0.0959 0.4698 1.0000
4.750 0.9690 0.02777 0.01621 -0.0955 0.4603 1.0000
5.000 0.9963 0.02826 0.01661 -0.0954 0.4527 1.0000
5.250 1.0196 0.02903 0.01743 -0.0949 0.4443 1.0000
5.500 1.0453 0.02963 0.01803 -0.0946 0.4367 1.0000
5.750 1.0701 0.03034 0.01874 -0.0943 0.4296 1.0000
6.000 1.0926 0.03116 0.01964 -0.0938 0.4219 1.0000
6.250 1.1203 0.03171 0.02013 -0.0937 0.4160 1.0000
6.500 1.1395 0.03277 0.02137 -0.0929 0.4084 1.0000
6.750 1.1628 0.03357 0.02221 -0.0924 0.4017 1.0000
7.000 1.1882 0.03422 0.02284 -0.0920 0.3955 1.0000
7.250 1.2043 0.03533 0.02415 -0.0908 0.3869 1.0000
7.500 1.2318 0.03559 0.02430 -0.0904 0.3794 1.0000
7.750 1.2433 0.03683 0.02576 -0.0887 0.3699 1.0000
8.000 1.2696 0.03697 0.02580 -0.0881 0.3614 1.0000
8.250 1.2785 0.03827 0.02734 -0.0862 0.3520 1.0000
8.500 1.3030 0.03846 0.02745 -0.0854 0.3439 1.0000
8.750 1.3098 0.03987 0.02911 -0.0833 0.3352 1.0000
9.000 1.3300 0.04029 0.02953 -0.0822 0.3275 1.0000
9.250 1.3370 0.04166 0.03109 -0.0801 0.3197 1.0000
9.500 1.3502 0.04245 0.03195 -0.0785 0.3119 1.0000
9.750 1.3585 0.04358 0.03319 -0.0765 0.3045 1.0000
10.000 1.3599 0.04500 0.03476 -0.0739 0.2971 1.0000
10.250 1.3725 0.04569 0.03547 -0.0722 0.2901 1.0000
10.500 1.3623 0.04823 0.03826 -0.0696 0.2831 1.0000
10.750 1.3719 0.04922 0.03930 -0.0680 0.2766 1.0000
11.000 1.3617 0.05216 0.04244 -0.0662 0.2702 1.0000
11.250 1.3528 0.05518 0.04562 -0.0649 0.2636 1.0000
11.500 1.3604 0.05656 0.04703 -0.0638 0.2576 1.0000
11.750 1.3277 0.06301 0.05379 -0.0638 0.2514 1.0000
12.000 1.3240 0.06611 0.05699 -0.0636 0.2453 1.0000
12.250 1.3022 0.07204 0.06309 -0.0645 0.2394 1.0000
12.500 1.2529 0.08286 0.07413 -0.0678 0.2321 1.0000
12.750 1.2870 0.08023 0.07152 -0.0656 0.2271 1.0000
13.000 1.1968 0.09923 0.09071 -0.0730 0.2165 1.0000
13.250 1.2278 0.09669 0.08823 -0.0708 0.2124 1.0000
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