Dormoy (dormoy-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: Dormoy (dormoy-il) Reynolds number: 50,000 Max Cl/Cd: 36.21 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dormoy-il-50000-n5.txt Download as CSV file: xf-dormoy-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Dormoy
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4139 0.10202 0.09595 -0.0276 1.0000 0.1509
-9.250 -0.3935 0.09655 0.09048 -0.0254 1.0000 0.1551
-8.750 -0.4199 0.09281 0.08707 -0.0290 1.0000 0.1660
-8.500 -0.4032 0.08818 0.08245 -0.0258 1.0000 0.1693
-7.500 -0.4010 0.06891 0.06324 -0.0388 1.0000 0.0764
-7.250 -0.3966 0.06437 0.05860 -0.0399 1.0000 0.0629
-7.000 -0.3914 0.05985 0.05375 -0.0413 1.0000 0.0535
-6.750 -0.3864 0.05670 0.05063 -0.0397 1.0000 0.0508
-6.500 -0.3802 0.05321 0.04699 -0.0389 1.0000 0.0476
-6.250 -0.3670 0.04995 0.04286 -0.0387 1.0000 0.0421
-6.000 -0.3577 0.04639 0.03937 -0.0374 1.0000 0.0405
-5.750 -0.3455 0.04342 0.03615 -0.0364 1.0000 0.0388
-5.500 -0.3303 0.04049 0.03278 -0.0354 1.0000 0.0369
-5.250 -0.3122 0.03776 0.02952 -0.0344 1.0000 0.0350
-5.000 -0.2771 0.03542 0.02623 -0.0353 0.9948 0.0328
-4.750 -0.2426 0.03269 0.02310 -0.0369 0.9887 0.0322
-4.500 -0.2076 0.03045 0.02043 -0.0382 0.9822 0.0317
-4.250 -0.1715 0.02885 0.01834 -0.0393 0.9757 0.0327
-4.000 -0.1375 0.02696 0.01628 -0.0405 0.9695 0.0352
-3.750 -0.1036 0.02570 0.01478 -0.0413 0.9624 0.0370
-3.500 -0.0662 0.02470 0.01345 -0.0429 0.9559 0.0388
-3.250 -0.0332 0.02390 0.01236 -0.0438 0.9474 0.0431
-2.750 0.0382 0.02183 0.01062 -0.0471 0.9320 0.1931
-2.500 0.0991 0.01915 0.01036 -0.0523 0.9298 1.0000
-2.250 0.1366 0.01924 0.00991 -0.0542 0.9179 1.0000
-2.000 0.1759 0.01928 0.00954 -0.0564 0.9055 1.0000
-1.750 0.2169 0.01926 0.00917 -0.0588 0.8925 1.0000
-1.500 0.2567 0.01918 0.00877 -0.0609 0.8783 1.0000
-1.250 0.2939 0.01912 0.00849 -0.0623 0.8642 1.0000
-1.000 0.3282 0.01910 0.00831 -0.0633 0.8507 1.0000
-0.750 0.3599 0.01916 0.00821 -0.0639 0.8382 1.0000
-0.500 0.3905 0.01923 0.00819 -0.0643 0.8257 1.0000
-0.250 0.4202 0.01929 0.00818 -0.0644 0.8119 1.0000
0.000 0.4486 0.01935 0.00820 -0.0642 0.7968 1.0000
0.250 0.4759 0.01941 0.00823 -0.0637 0.7805 1.0000
0.500 0.5030 0.01944 0.00824 -0.0631 0.7632 1.0000
0.750 0.5284 0.01949 0.00832 -0.0622 0.7447 1.0000
1.000 0.5513 0.01959 0.00844 -0.0609 0.7242 1.0000
1.250 0.5764 0.01962 0.00850 -0.0600 0.7047 1.0000
1.500 0.5992 0.01972 0.00866 -0.0587 0.6827 1.0000
1.750 0.6235 0.01974 0.00877 -0.0576 0.6591 1.0000
2.000 0.6467 0.01977 0.00882 -0.0561 0.6309 1.0000
2.250 0.6685 0.01984 0.00887 -0.0545 0.5960 1.0000
2.500 0.6900 0.01997 0.00892 -0.0528 0.5576 1.0000
2.750 0.7111 0.02023 0.00919 -0.0512 0.5204 1.0000
3.000 0.7327 0.02059 0.00955 -0.0500 0.4892 1.0000
3.250 0.7546 0.02100 0.01004 -0.0489 0.4627 1.0000
3.500 0.7767 0.02145 0.01060 -0.0479 0.4400 1.0000
3.750 0.7915 0.02213 0.01103 -0.0456 0.3854 1.0000
4.000 0.8029 0.02318 0.01162 -0.0432 0.3204 1.0000
4.250 0.8206 0.02397 0.01246 -0.0418 0.2782 1.0000
4.500 0.8360 0.02499 0.01332 -0.0401 0.1992 1.0000
4.750 0.8387 0.02781 0.01506 -0.0376 0.0645 1.0000
5.000 0.8512 0.02985 0.01729 -0.0356 0.0439 1.0000
5.250 0.8666 0.03135 0.01907 -0.0339 0.0344 1.0000
5.500 0.8803 0.03289 0.02094 -0.0321 0.0309 1.0000
5.750 0.8905 0.03464 0.02291 -0.0301 0.0286 1.0000
6.000 0.8990 0.03637 0.02489 -0.0279 0.0270 1.0000
6.250 0.9046 0.03816 0.02688 -0.0255 0.0250 1.0000
6.500 0.9086 0.03999 0.02888 -0.0232 0.0237 1.0000
6.750 0.9110 0.04204 0.03108 -0.0209 0.0226 1.0000
7.000 0.9150 0.04424 0.03342 -0.0188 0.0222 1.0000
7.250 0.9262 0.04640 0.03571 -0.0169 0.0219 1.0000
7.500 0.9598 0.04872 0.03813 -0.0160 0.0217 1.0000
7.750 1.0048 0.05214 0.04178 -0.0169 0.0217 1.0000
8.000 1.0313 0.05585 0.04590 -0.0166 0.0217 1.0000
8.250 1.0441 0.05926 0.04966 -0.0153 0.0217 1.0000
8.500 1.0479 0.06241 0.05316 -0.0134 0.0216 1.0000
8.750 1.0457 0.06560 0.05668 -0.0112 0.0215 1.0000
9.000 1.0402 0.06871 0.06009 -0.0092 0.0214 1.0000
9.250 1.0321 0.07204 0.06369 -0.0077 0.0214 1.0000
9.500 1.0214 0.07567 0.06757 -0.0067 0.0214 1.0000
9.750 1.0081 0.07955 0.07168 -0.0065 0.0214 1.0000
10.000 0.9958 0.08376 0.07609 -0.0069 0.0215 1.0000
10.250 0.9840 0.08827 0.08077 -0.0079 0.0217 1.0000
10.500 0.9700 0.09327 0.08594 -0.0096 0.0217 1.0000
10.750 0.9563 0.09852 0.09134 -0.0119 0.0218 1.0000
11.000 0.9383 0.10409 0.09719 -0.0157 0.0223 1.0000
11.250 0.9139 0.11202 0.10531 -0.0216 0.0229 1.0000
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Polar data table (+)
Polar graphs
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