EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 1.0/9.0 (eh1090-il) Reynolds number: 50,000 Max Cl/Cd: 31.17 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1090-il-50000-n5.txt Download as CSV file: xf-eh1090-il-50000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.6095 0.10373 0.09699 -0.0021 1.0000 0.0428
-9.750 -0.6099 0.09862 0.09192 -0.0046 1.0000 0.0427
-9.500 -0.6104 0.09355 0.08689 -0.0071 1.0000 0.0424
-9.250 -0.6118 0.08840 0.08179 -0.0101 1.0000 0.0420
-9.000 -0.6171 0.08298 0.07640 -0.0136 1.0000 0.0416
-8.750 -0.6266 0.07796 0.07139 -0.0162 1.0000 0.0413
-8.500 -0.6362 0.07350 0.06691 -0.0175 1.0000 0.0410
-8.250 -0.6432 0.06892 0.06223 -0.0186 1.0000 0.0406
-8.000 -0.6486 0.06425 0.05740 -0.0192 1.0000 0.0404
-7.750 -0.6502 0.05975 0.05267 -0.0194 1.0000 0.0402
-7.500 -0.6489 0.05528 0.04789 -0.0191 1.0000 0.0401
-7.250 -0.6440 0.05098 0.04320 -0.0184 1.0000 0.0401
-7.000 -0.6359 0.04683 0.03852 -0.0175 1.0000 0.0404
-6.750 -0.6241 0.04297 0.03414 -0.0163 1.0000 0.0409
-6.500 -0.6089 0.03936 0.02995 -0.0150 1.0000 0.0417
-6.250 -0.5909 0.03625 0.02634 -0.0138 1.0000 0.0435
-6.000 -0.5719 0.03425 0.02425 -0.0131 1.0000 0.0479
-5.750 -0.5499 0.03195 0.02154 -0.0120 1.0000 0.0523
-5.500 -0.5253 0.02953 0.01868 -0.0109 1.0000 0.0558
-5.250 -0.5026 0.02779 0.01693 -0.0100 1.0000 0.0628
-5.000 -0.4792 0.02624 0.01527 -0.0091 1.0000 0.0737
-4.750 -0.4553 0.02464 0.01352 -0.0080 1.0000 0.0868
-4.500 -0.4327 0.02333 0.01220 -0.0070 1.0000 0.1107
-4.250 -0.4109 0.02200 0.01099 -0.0060 1.0000 0.1456
-4.000 -0.3905 0.02065 0.00992 -0.0050 1.0000 0.1962
-3.750 -0.3728 0.01930 0.00903 -0.0036 1.0000 0.2755
-3.500 -0.3603 0.01785 0.00844 -0.0011 1.0000 0.4153
-3.250 -0.3474 0.01682 0.00843 0.0031 1.0000 0.6179
-3.000 -0.3216 0.01672 0.00853 0.0059 1.0000 0.7621
-2.750 -0.2858 0.01692 0.00858 0.0065 1.0000 0.8477
-2.500 -0.2335 0.01721 0.00852 0.0035 1.0000 0.9088
-2.250 -0.1576 0.01736 0.00814 -0.0047 1.0000 0.9528
-2.000 -0.0834 0.01710 0.00749 -0.0138 1.0000 0.9846
-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 0.0390 0.01661 0.00656 -0.0128 0.9759 1.0000
-0.250 0.0889 0.01665 0.00649 -0.0178 0.9503 1.0000
0.000 0.1358 0.01664 0.00642 -0.0219 0.9235 1.0000
0.250 0.1779 0.01663 0.00635 -0.0248 0.8956 1.0000
0.500 0.2133 0.01666 0.00631 -0.0263 0.8670 1.0000
0.750 0.2428 0.01672 0.00631 -0.0264 0.8389 1.0000
1.000 0.2681 0.01682 0.00634 -0.0256 0.8120 1.0000
1.250 0.2913 0.01695 0.00642 -0.0244 0.7867 1.0000
1.500 0.3131 0.01711 0.00651 -0.0230 0.7621 1.0000
1.750 0.3344 0.01729 0.00665 -0.0214 0.7382 1.0000
2.000 0.3559 0.01749 0.00680 -0.0199 0.7160 1.0000
2.250 0.3773 0.01771 0.00699 -0.0184 0.6940 1.0000
2.500 0.3988 0.01795 0.00724 -0.0170 0.6726 1.0000
2.750 0.4206 0.01820 0.00748 -0.0156 0.6518 1.0000
3.000 0.4424 0.01847 0.00776 -0.0143 0.6312 1.0000
3.250 0.4643 0.01876 0.00807 -0.0129 0.6109 1.0000
3.500 0.4864 0.01906 0.00839 -0.0116 0.5913 1.0000
3.750 0.5085 0.01938 0.00883 -0.0104 0.5708 1.0000
4.000 0.5314 0.01970 0.00918 -0.0092 0.5515 1.0000
4.250 0.5539 0.02007 0.00966 -0.0081 0.5302 1.0000
4.500 0.5766 0.02042 0.01006 -0.0069 0.5104 1.0000
4.750 0.5989 0.02082 0.01059 -0.0058 0.4886 1.0000
5.000 0.6214 0.02121 0.01110 -0.0045 0.4677 1.0000
5.250 0.6434 0.02163 0.01168 -0.0033 0.4446 1.0000
5.500 0.6651 0.02206 0.01223 -0.0021 0.4206 1.0000
5.750 0.6865 0.02249 0.01278 -0.0007 0.3953 1.0000
6.000 0.7076 0.02296 0.01337 0.0006 0.3687 1.0000
6.250 0.7278 0.02345 0.01408 0.0020 0.3382 1.0000
6.500 0.7456 0.02392 0.01460 0.0037 0.2966 1.0000
6.750 0.7606 0.02458 0.01514 0.0054 0.2386 1.0000
7.000 0.7731 0.02587 0.01608 0.0069 0.1665 1.0000
7.250 0.7832 0.02805 0.01780 0.0083 0.1049 1.0000
7.500 0.7932 0.03037 0.01991 0.0100 0.0780 1.0000
7.750 0.8042 0.03243 0.02192 0.0115 0.0630 1.0000
8.000 0.8169 0.03439 0.02403 0.0132 0.0548 1.0000
8.250 0.8284 0.03652 0.02617 0.0148 0.0503 1.0000
8.500 0.8444 0.03859 0.02854 0.0163 0.0457 1.0000
8.750 0.8573 0.04066 0.03087 0.0175 0.0411 1.0000
9.000 0.8695 0.04328 0.03349 0.0187 0.0382 1.0000
9.250 0.8838 0.04610 0.03674 0.0200 0.0368 1.0000
9.500 0.8933 0.04924 0.04030 0.0212 0.0359 1.0000
9.750 0.8972 0.05266 0.04412 0.0224 0.0352 1.0000
10.000 0.8950 0.05628 0.04811 0.0234 0.0347 1.0000
10.250 0.8864 0.05981 0.05191 0.0245 0.0346 1.0000
10.500 0.8738 0.06373 0.05607 0.0245 0.0345 1.0000
10.750 0.8583 0.06833 0.06088 0.0230 0.0346 1.0000
11.000 0.8414 0.07366 0.06639 0.0201 0.0348 1.0000
11.250 0.8230 0.07997 0.07284 0.0160 0.0351 1.0000
11.500 0.8039 0.08730 0.08028 0.0109 0.0355 1.0000
11.750 0.7869 0.09503 0.08807 0.0057 0.0360 1.0000
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Polar data table (+)
Polar graphs
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