USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 40 B AIRFOIL (usa40b-il) Reynolds number: 200,000 Max Cl/Cd: 56.44 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa40b-il-200000.txt Download as CSV file: xf-usa40b-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 40 B AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2792 0.09735 0.09372 -0.0311 1.0000 0.0759
-8.750 -0.2809 0.09471 0.09112 -0.0314 1.0000 0.0780
-8.500 -0.3464 0.08987 0.08646 -0.0386 1.0000 0.0808
-8.250 -0.3328 0.08679 0.08340 -0.0356 1.0000 0.0815
-8.000 -0.3172 0.08541 0.08206 -0.0323 1.0000 0.0824
-7.750 -0.3163 0.08391 0.08063 -0.0298 1.0000 0.0832
-7.500 -0.3236 0.08254 0.07933 -0.0271 1.0000 0.0840
-7.250 -0.3415 0.08144 0.07832 -0.0237 1.0000 0.0846
-7.000 -0.3371 0.06554 0.06228 -0.0563 0.9839 0.0923
-6.750 -0.3016 0.06406 0.06086 -0.0560 0.9786 0.0933
-6.500 -0.2689 0.06172 0.05853 -0.0584 0.9721 0.0952
-6.000 -0.2306 0.02884 0.02273 -0.0906 0.9448 0.0635
-5.750 -0.1894 0.02600 0.01963 -0.0939 0.9409 0.0631
-5.500 -0.1556 0.02398 0.01733 -0.0952 0.9311 0.0631
-5.250 -0.1131 0.02215 0.01520 -0.0980 0.9259 0.0635
-5.000 -0.0790 0.02038 0.01333 -0.0992 0.9155 0.0643
-4.750 -0.0380 0.01919 0.01213 -0.1015 0.9078 0.0662
-4.500 -0.0049 0.01833 0.01119 -0.1021 0.8939 0.0682
-4.250 0.0293 0.01746 0.01016 -0.1027 0.8796 0.0702
-4.000 0.0622 0.01664 0.00918 -0.1031 0.8640 0.0719
-3.750 0.0922 0.01570 0.00830 -0.1031 0.8466 0.0744
-3.500 0.1213 0.01512 0.00768 -0.1028 0.8278 0.0777
-3.250 0.1494 0.01455 0.00702 -0.1023 0.8080 0.0821
-3.000 0.1766 0.01404 0.00651 -0.1017 0.7879 0.0883
-2.750 0.2032 0.01350 0.00594 -0.1011 0.7678 0.0963
-2.500 0.2294 0.01304 0.00545 -0.1003 0.7475 0.1099
-2.250 0.2551 0.01264 0.00509 -0.0996 0.7269 0.1357
-2.000 0.2806 0.01232 0.00492 -0.0988 0.7060 0.1950
-1.750 0.3054 0.01204 0.00477 -0.0980 0.6845 0.2581
-1.500 0.3297 0.01181 0.00470 -0.0971 0.6603 0.3170
-1.250 0.3534 0.01160 0.00464 -0.0960 0.6330 0.3909
-1.000 0.3759 0.01138 0.00462 -0.0946 0.6016 0.4786
-0.750 0.3970 0.01129 0.00470 -0.0928 0.5659 0.5738
-0.500 0.4180 0.01142 0.00480 -0.0908 0.5290 0.6432
-0.250 0.4395 0.01168 0.00492 -0.0890 0.4965 0.6937
0.000 0.4611 0.01196 0.00506 -0.0872 0.4692 0.7335
0.250 0.4827 0.01224 0.00519 -0.0854 0.4476 0.7662
0.500 0.5043 0.01245 0.00531 -0.0836 0.4297 0.7949
0.750 0.5262 0.01261 0.00539 -0.0819 0.4145 0.8230
1.000 0.5481 0.01272 0.00544 -0.0803 0.4020 0.8497
1.250 0.5705 0.01283 0.00546 -0.0788 0.3910 0.8788
1.500 0.6016 0.01286 0.00551 -0.0790 0.3796 0.9150
1.750 0.6451 0.01315 0.00565 -0.0822 0.3684 1.0000
2.000 0.6730 0.01343 0.00581 -0.0823 0.3592 1.0000
2.250 0.7008 0.01381 0.00602 -0.0824 0.3514 1.0000
2.500 0.7284 0.01408 0.00621 -0.0824 0.3438 1.0000
2.750 0.7559 0.01446 0.00643 -0.0823 0.3374 1.0000
3.000 0.7834 0.01480 0.00670 -0.0822 0.3313 1.0000
3.250 0.8105 0.01510 0.00694 -0.0820 0.3253 1.0000
3.500 0.8377 0.01549 0.00720 -0.0819 0.3201 1.0000
3.750 0.8648 0.01591 0.00755 -0.0817 0.3150 1.0000
4.000 0.8914 0.01620 0.00783 -0.0814 0.3098 1.0000
4.250 0.9181 0.01654 0.00810 -0.0811 0.3052 1.0000
4.500 0.9454 0.01705 0.00847 -0.0810 0.3011 1.0000
4.750 0.9719 0.01746 0.00889 -0.0807 0.2974 1.0000
5.000 0.9981 0.01781 0.00927 -0.0804 0.2935 1.0000
5.250 1.0244 0.01819 0.00963 -0.0801 0.2899 1.0000
5.500 1.0510 0.01862 0.00999 -0.0798 0.2866 1.0000
5.750 1.0786 0.01923 0.01050 -0.0798 0.2835 1.0000
6.000 1.1044 0.01973 0.01104 -0.0794 0.2807 1.0000
6.250 1.1294 0.02012 0.01151 -0.0789 0.2776 1.0000
6.500 1.1546 0.02054 0.01197 -0.0785 0.2744 1.0000
6.750 1.1804 0.02099 0.01240 -0.0781 0.2716 1.0000
7.000 1.2067 0.02149 0.01287 -0.0779 0.2692 1.0000
7.250 1.2338 0.02218 0.01350 -0.0779 0.2669 1.0000
7.500 1.2592 0.02292 0.01429 -0.0776 0.2647 1.0000
7.750 1.2828 0.02345 0.01494 -0.0769 0.2627 1.0000
8.000 1.3063 0.02403 0.01564 -0.0763 0.2604 1.0000
8.250 1.3301 0.02464 0.01632 -0.0757 0.2582 1.0000
8.500 1.3541 0.02516 0.01689 -0.0751 0.2558 1.0000
8.750 1.3788 0.02562 0.01733 -0.0747 0.2533 1.0000
9.000 1.4051 0.02622 0.01786 -0.0746 0.2506 1.0000
9.250 1.4279 0.02707 0.01878 -0.0740 0.2481 1.0000
9.500 1.4481 0.02771 0.01959 -0.0730 0.2462 1.0000
9.750 1.4688 0.02844 0.02047 -0.0720 0.2442 1.0000
10.000 1.4893 0.02914 0.02128 -0.0711 0.2420 1.0000
10.250 1.5103 0.02974 0.02196 -0.0702 0.2397 1.0000
10.500 1.5330 0.03026 0.02251 -0.0696 0.2374 1.0000
10.750 1.5581 0.03082 0.02303 -0.0693 0.2352 1.0000
11.000 1.5818 0.03190 0.02411 -0.0691 0.2328 1.0000
11.250 1.5950 0.03262 0.02507 -0.0671 0.2307 1.0000
11.500 1.6096 0.03345 0.02609 -0.0655 0.2285 1.0000
11.750 1.6249 0.03428 0.02707 -0.0640 0.2262 1.0000
12.000 1.6414 0.03501 0.02791 -0.0626 0.2240 1.0000
12.250 1.6603 0.03562 0.02858 -0.0616 0.2220 1.0000
12.500 1.6839 0.03617 0.02911 -0.0612 0.2199 1.0000
12.750 1.7098 0.03730 0.03021 -0.0614 0.2175 1.0000
13.000 1.7100 0.03833 0.03153 -0.0580 0.2155 1.0000
13.250 1.7116 0.03936 0.03278 -0.0549 0.2130 1.0000
13.500 1.7140 0.04010 0.03365 -0.0517 0.2102 1.0000
13.750 1.7232 0.04039 0.03399 -0.0493 0.2075 1.0000
14.000 1.7609 0.03974 0.03313 -0.0504 0.2036 1.0000
14.250 1.2459 0.09740 0.09263 -0.0521 0.1986 1.0000
14.500 1.2810 0.09441 0.08967 -0.0498 0.1976 1.0000
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Polar data table (+)
Polar graphs
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