EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 50,000 Max Cl/Cd: 29.17 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1090-il-50000.txt Download as CSV file: xf-eh1090-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 1.0/9.0
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5506 0.10074 0.09424 0.0176 1.0000 0.2938
-8.250 -0.5472 0.09741 0.09096 0.0179 1.0000 0.3105
-8.000 -0.5593 0.09514 0.08880 0.0176 1.0000 0.3286
-7.750 -0.5390 0.09089 0.08450 0.0197 1.0000 0.3540
-7.250 -0.5276 0.08370 0.07740 0.0211 1.0000 0.3891
-7.000 -0.6258 0.06597 0.05938 -0.0143 1.0000 0.1633
-6.750 -0.6135 0.05812 0.05122 -0.0161 1.0000 0.1297
-6.500 -0.6071 0.05226 0.04484 -0.0166 1.0000 0.1170
-6.250 -0.5993 0.04714 0.03875 -0.0159 1.0000 0.1077
-6.000 -0.5844 0.04332 0.03443 -0.0147 1.0000 0.1079
-5.750 -0.5656 0.04000 0.03117 -0.0139 1.0000 0.1137
-5.500 -0.5464 0.03666 0.02735 -0.0126 1.0000 0.1155
-5.250 -0.5246 0.03344 0.02357 -0.0112 1.0000 0.1179
-5.000 -0.5017 0.03067 0.02045 -0.0100 1.0000 0.1258
-4.750 -0.4785 0.02843 0.01798 -0.0088 1.0000 0.1418
-4.500 -0.4527 0.02610 0.01537 -0.0075 1.0000 0.1621
-4.250 -0.4281 0.02391 0.01343 -0.0063 1.0000 0.1999
-4.000 -0.4042 0.02178 0.01167 -0.0050 1.0000 0.2637
-3.750 -0.3851 0.01932 0.01012 -0.0030 1.0000 0.3805
-3.500 -0.3800 0.01724 0.01041 0.0063 1.0000 0.7399
-3.250 -0.1273 0.01908 0.01009 -0.0239 1.0000 1.0000
-3.000 -0.1127 0.01847 0.00925 -0.0234 1.0000 1.0000
-2.750 -0.0973 0.01798 0.00859 -0.0228 1.0000 1.0000
-2.500 -0.0815 0.01757 0.00804 -0.0220 1.0000 1.0000
-2.250 -0.0658 0.01723 0.00757 -0.0210 1.0000 1.0000
-2.000 -0.0505 0.01695 0.00720 -0.0199 1.0000 1.0000
-1.750 -0.0360 0.01673 0.00690 -0.0185 1.0000 1.0000
-1.500 -0.0229 0.01657 0.00665 -0.0169 1.0000 1.0000
-1.250 -0.0125 0.01647 0.00653 -0.0148 1.0000 1.0000
-1.000 -0.0061 0.01646 0.00650 -0.0120 1.0000 1.0000
-0.750 -0.0046 0.01655 0.00658 -0.0086 1.0000 1.0000
-0.500 -0.0083 0.01676 0.00677 -0.0046 1.0000 1.0000
-0.250 -0.0130 0.01707 0.00702 -0.0006 1.0000 1.0000
0.000 -0.0153 0.01745 0.00733 0.0027 1.0000 1.0000
0.250 -0.0144 0.01790 0.00770 0.0054 1.0000 1.0000
0.500 -0.0102 0.01841 0.00812 0.0073 1.0000 1.0000
0.750 0.0371 0.01925 0.00893 0.0013 0.9855 1.0000
1.000 0.1118 0.02008 0.00979 -0.0091 0.9597 1.0000
1.250 0.1847 0.02066 0.01045 -0.0186 0.9339 1.0000
1.500 0.2629 0.02095 0.01088 -0.0285 0.9088 1.0000
1.750 0.3271 0.02105 0.01114 -0.0349 0.8830 1.0000
2.000 0.3759 0.02115 0.01136 -0.0381 0.8570 1.0000
2.250 0.4111 0.02136 0.01165 -0.0387 0.8309 1.0000
2.500 0.4371 0.02170 0.01210 -0.0376 0.8050 1.0000
2.750 0.4600 0.02210 0.01255 -0.0359 0.7800 1.0000
3.000 0.4823 0.02248 0.01299 -0.0340 0.7565 1.0000
3.250 0.5040 0.02284 0.01340 -0.0318 0.7338 1.0000
3.500 0.5230 0.02338 0.01406 -0.0296 0.7098 1.0000
3.750 0.5432 0.02383 0.01458 -0.0273 0.6873 1.0000
4.000 0.5637 0.02426 0.01508 -0.0249 0.6648 1.0000
4.250 0.5830 0.02485 0.01577 -0.0228 0.6410 1.0000
4.500 0.6036 0.02532 0.01631 -0.0205 0.6182 1.0000
4.750 0.6246 0.02573 0.01680 -0.0181 0.5947 1.0000
5.000 0.6444 0.02631 0.01757 -0.0159 0.5693 1.0000
5.250 0.6649 0.02680 0.01817 -0.0136 0.5433 1.0000
5.500 0.6857 0.02721 0.01868 -0.0112 0.5160 1.0000
5.750 0.7067 0.02755 0.01912 -0.0088 0.4871 1.0000
6.000 0.7283 0.02784 0.01948 -0.0062 0.4567 1.0000
6.250 0.7481 0.02795 0.01972 -0.0034 0.4188 1.0000
6.500 0.7672 0.02731 0.01889 0.0002 0.3699 1.0000
6.750 0.7798 0.02673 0.01802 0.0041 0.3012 1.0000
7.000 0.7845 0.02781 0.01838 0.0081 0.2074 1.0000
7.250 0.7957 0.03046 0.02057 0.0108 0.1486 1.0000
7.500 0.8125 0.03289 0.02287 0.0125 0.1205 1.0000
7.750 0.8345 0.03581 0.02589 0.0139 0.1071 1.0000
8.000 0.8555 0.03895 0.02911 0.0150 0.0986 1.0000
8.250 0.8716 0.04183 0.03242 0.0164 0.0913 1.0000
8.500 0.8881 0.04545 0.03615 0.0173 0.0865 1.0000
8.750 0.8971 0.04949 0.04086 0.0188 0.0856 1.0000
9.000 0.9017 0.05383 0.04571 0.0201 0.0855 1.0000
9.250 0.9027 0.05841 0.05068 0.0211 0.0858 1.0000
9.500 0.9017 0.06313 0.05569 0.0219 0.0865 1.0000
9.750 0.9013 0.06821 0.06099 0.0223 0.0872 1.0000
10.000 0.8467 0.07284 0.06617 0.0217 0.0903 1.0000
10.250 0.8051 0.07979 0.07313 0.0171 0.0934 1.0000
10.500 0.7783 0.08794 0.08126 0.0110 0.0964 1.0000
10.750 0.7667 0.09516 0.08844 0.0071 0.0985 1.0000
11.000 0.7671 0.10095 0.09424 0.0054 0.1004 1.0000
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Polar data table (+)
Polar graphs
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