USA 41 AIRFOIL (usa41-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: USA 41 AIRFOIL (usa41-il) Reynolds number: 200,000 Max Cl/Cd: 79.31 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-usa41-il-200000.txt Download as CSV file: xf-usa41-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: USA 41 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3394 0.09752 0.09398 -0.0258 1.0000 0.0345
-8.000 -0.3444 0.09609 0.09263 -0.0274 1.0000 0.0350
-7.750 -0.3506 0.09461 0.09123 -0.0280 1.0000 0.0353
-7.500 -0.3498 0.09217 0.08885 -0.0299 1.0000 0.0355
-7.250 -0.3466 0.08946 0.08619 -0.0317 1.0000 0.0356
-7.000 -0.3497 0.08478 0.08159 -0.0318 1.0000 0.0360
-6.750 -0.3498 0.08147 0.07832 -0.0275 1.0000 0.0369
-6.500 -0.3490 0.07923 0.07611 -0.0256 1.0000 0.0376
-6.250 -0.3491 0.07715 0.07406 -0.0240 1.0000 0.0386
-6.000 -0.3491 0.07497 0.07192 -0.0234 1.0000 0.0395
-5.750 -0.3472 0.07260 0.06957 -0.0236 1.0000 0.0406
-5.500 -0.3425 0.06990 0.06688 -0.0249 1.0000 0.0425
-5.250 -0.3301 0.06652 0.06348 -0.0292 1.0000 0.0451
-5.000 -0.2863 0.05931 0.05614 -0.0423 0.9959 0.0488
-4.750 -0.2587 0.05683 0.05365 -0.0443 0.9916 0.0531
-4.500 -0.2003 0.04935 0.04585 -0.0593 0.9863 0.0611
-4.250 -0.1446 0.04671 0.04275 -0.0683 0.9816 0.0726
-4.000 -0.1246 0.04208 0.03830 -0.0696 0.9761 0.0755
-3.750 -0.0799 0.03855 0.03453 -0.0758 0.9719 0.0885
-2.750 0.0834 0.02036 0.01434 -0.0900 0.9508 0.0662
-2.500 0.1255 0.01790 0.01106 -0.0919 0.9462 0.0601
-2.250 0.1690 0.01600 0.00890 -0.0949 0.9431 0.0615
-2.000 0.2045 0.01494 0.00766 -0.0959 0.9350 0.0610
-1.750 0.2459 0.01381 0.00645 -0.0982 0.9300 0.0618
-1.500 0.2799 0.01305 0.00567 -0.0990 0.9208 0.0632
-1.250 0.3191 0.01238 0.00501 -0.1008 0.9140 0.0667
-1.000 0.3498 0.01195 0.00455 -0.1008 0.9019 0.0708
-0.750 0.3802 0.01154 0.00411 -0.1008 0.8893 0.0744
-0.500 0.4093 0.01118 0.00377 -0.1005 0.8755 0.0856
-0.250 0.4370 0.01084 0.00374 -0.0999 0.8603 0.1781
0.000 0.4645 0.01075 0.00363 -0.0993 0.8438 0.2183
0.250 0.4913 0.01058 0.00344 -0.0987 0.8265 0.2438
0.500 0.5161 0.01034 0.00330 -0.0977 0.8055 0.2781
0.750 0.5387 0.00952 0.00329 -0.0966 0.7854 0.5601
1.000 0.5855 0.00869 0.00310 -0.1001 0.7622 1.0000
1.250 0.6113 0.00881 0.00301 -0.0992 0.7391 1.0000
1.500 0.6366 0.00898 0.00300 -0.0983 0.7147 1.0000
1.750 0.6619 0.00917 0.00301 -0.0975 0.6914 1.0000
2.000 0.6871 0.00939 0.00306 -0.0967 0.6693 1.0000
2.250 0.7122 0.00961 0.00314 -0.0959 0.6479 1.0000
2.500 0.7373 0.00985 0.00326 -0.0951 0.6278 1.0000
2.750 0.7625 0.01011 0.00339 -0.0944 0.6096 1.0000
3.000 0.7876 0.01036 0.00355 -0.0937 0.5912 1.0000
3.250 0.8127 0.01063 0.00374 -0.0930 0.5740 1.0000
3.500 0.8377 0.01091 0.00396 -0.0923 0.5575 1.0000
3.750 0.8628 0.01119 0.00419 -0.0917 0.5418 1.0000
4.000 0.8878 0.01149 0.00444 -0.0910 0.5267 1.0000
4.250 0.9129 0.01179 0.00471 -0.0904 0.5123 1.0000
4.500 0.9378 0.01209 0.00502 -0.0897 0.4981 1.0000
4.750 0.9626 0.01238 0.00531 -0.0890 0.4836 1.0000
5.000 0.9873 0.01267 0.00562 -0.0884 0.4696 1.0000
5.250 1.0115 0.01294 0.00590 -0.0876 0.4539 1.0000
5.500 1.0339 0.01313 0.00609 -0.0864 0.4299 1.0000
5.750 1.0560 0.01336 0.00627 -0.0852 0.4046 1.0000
6.000 1.0786 0.01360 0.00654 -0.0842 0.3794 1.0000
6.250 1.0999 0.01394 0.00682 -0.0829 0.3480 1.0000
6.500 1.1202 0.01439 0.00717 -0.0816 0.3029 1.0000
6.750 1.1290 0.01611 0.00805 -0.0789 0.1530 1.0000
7.000 1.1335 0.01880 0.00993 -0.0756 0.0505 1.0000
7.250 1.1505 0.01992 0.01114 -0.0738 0.0421 1.0000
7.500 1.1629 0.02142 0.01273 -0.0713 0.0381 1.0000
7.750 1.1781 0.02258 0.01402 -0.0692 0.0357 1.0000
8.000 1.1925 0.02379 0.01529 -0.0672 0.0328 1.0000
8.250 1.2038 0.02536 0.01692 -0.0648 0.0306 1.0000
8.500 1.2144 0.02762 0.01920 -0.0624 0.0293 1.0000
8.750 1.2322 0.02993 0.02158 -0.0609 0.0285 1.0000
9.000 1.2528 0.03177 0.02356 -0.0597 0.0280 1.0000
9.250 1.2733 0.03375 0.02572 -0.0585 0.0274 1.0000
9.500 1.2907 0.03542 0.02761 -0.0570 0.0260 1.0000
9.750 1.3085 0.03778 0.03023 -0.0556 0.0253 1.0000
10.000 1.3244 0.04077 0.03353 -0.0540 0.0254 1.0000
10.250 1.3358 0.04428 0.03740 -0.0520 0.0258 1.0000
10.500 1.3419 0.04825 0.04175 -0.0496 0.0266 1.0000
10.750 1.3431 0.05302 0.04686 -0.0473 0.0276 1.0000
11.000 1.2900 0.04940 0.04376 -0.0393 0.0300 1.0000
11.250 1.2403 0.05415 0.04924 -0.0319 0.0342 1.0000
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Polar data table (+)
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