Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 500,000 Max Cl/Cd: 61.46 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1070-il-500000-n5.txt Download as CSV file: xf-eh1070-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eh 1.0/7.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6128 0.08428 0.08218 0.0065 1.0000 0.0033
-8.250 -0.6189 0.07935 0.07728 0.0031 1.0000 0.0032
-8.000 -0.6299 0.07424 0.07220 -0.0012 1.0000 0.0032
-7.750 -0.6343 0.06801 0.06592 -0.0056 1.0000 0.0030
-7.500 -0.6352 0.06172 0.05954 -0.0089 1.0000 0.0030
-7.250 -0.6332 0.05514 0.05282 -0.0111 1.0000 0.0030
-7.000 -0.6282 0.04844 0.04590 -0.0123 1.0000 0.0030
-6.750 -0.6206 0.04153 0.03869 -0.0124 1.0000 0.0030
-6.500 -0.6092 0.03545 0.03226 -0.0117 1.0000 0.0031
-6.250 -0.5955 0.02975 0.02613 -0.0104 1.0000 0.0033
-6.000 -0.5788 0.02512 0.02103 -0.0089 1.0000 0.0037
-5.750 -0.5592 0.02170 0.01717 -0.0076 1.0000 0.0042
-5.500 -0.5371 0.01938 0.01448 -0.0065 1.0000 0.0046
-5.250 -0.5126 0.01842 0.01333 -0.0060 1.0000 0.0052
-5.000 -0.4865 0.01835 0.01317 -0.0056 1.0000 0.0056
-4.750 -0.4654 0.01515 0.00947 -0.0042 1.0000 0.0060
-4.500 -0.4426 0.01330 0.00736 -0.0031 1.0000 0.0063
-4.250 -0.4194 0.01210 0.00604 -0.0021 1.0000 0.0069
-4.000 -0.3955 0.01140 0.00527 -0.0013 1.0000 0.0079
-3.750 -0.3673 0.01081 0.00461 -0.0014 0.9952 0.0091
-3.500 -0.3332 0.01034 0.00407 -0.0029 0.9821 0.0104
-3.250 -0.2992 0.00986 0.00350 -0.0042 0.9649 0.0112
-3.000 -0.2651 0.00938 0.00286 -0.0055 0.9411 0.0115
-2.750 -0.2353 0.00902 0.00233 -0.0056 0.9095 0.0130
-2.500 -0.2098 0.00879 0.00201 -0.0048 0.8752 0.0214
-2.250 -0.1853 0.00853 0.00177 -0.0040 0.8438 0.0531
-2.000 -0.1605 0.00830 0.00159 -0.0034 0.8140 0.0971
-1.750 -0.1361 0.00793 0.00142 -0.0028 0.7859 0.1788
-1.500 -0.1130 0.00725 0.00121 -0.0023 0.7593 0.3443
-1.250 -0.0918 0.00641 0.00105 -0.0013 0.7337 0.5646
-1.000 -0.0695 0.00597 0.00099 -0.0001 0.7092 0.6983
-0.750 -0.0458 0.00579 0.00097 0.0010 0.6859 0.7742
-0.500 -0.0209 0.00574 0.00096 0.0019 0.6638 0.8212
-0.250 0.0043 0.00573 0.00095 0.0027 0.6427 0.8571
0.000 0.0295 0.00574 0.00096 0.0036 0.6221 0.8927
0.250 0.0567 0.00580 0.00101 0.0041 0.6018 0.9315
0.500 0.0899 0.00591 0.00105 0.0033 0.5809 0.9575
0.750 0.1217 0.00601 0.00107 0.0025 0.5612 0.9684
1.000 0.1557 0.00611 0.00108 0.0011 0.5410 0.9731
1.250 0.1877 0.00622 0.00109 0.0002 0.5195 0.9787
1.500 0.2203 0.00633 0.00111 -0.0010 0.4978 0.9828
1.750 0.2545 0.00643 0.00115 -0.0024 0.4785 0.9860
2.000 0.2877 0.00653 0.00119 -0.0037 0.4612 0.9898
2.250 0.3198 0.00664 0.00128 -0.0047 0.4427 0.9937
2.500 0.3531 0.00677 0.00134 -0.0061 0.4197 0.9968
2.750 0.3861 0.00691 0.00142 -0.0073 0.3961 0.9999
3.000 0.4107 0.00706 0.00152 -0.0068 0.3750 1.0000
3.250 0.4349 0.00724 0.00164 -0.0061 0.3513 1.0000
3.500 0.4591 0.00747 0.00182 -0.0055 0.3182 1.0000
3.750 0.4821 0.00794 0.00200 -0.0048 0.2476 1.0000
4.000 0.5049 0.00850 0.00226 -0.0042 0.1771 1.0000
4.250 0.5270 0.00923 0.00263 -0.0035 0.0957 1.0000
4.500 0.5486 0.01010 0.00314 -0.0027 0.0230 1.0000
4.750 0.5728 0.01050 0.00356 -0.0021 0.0131 1.0000
5.000 0.5971 0.01096 0.00407 -0.0014 0.0098 1.0000
5.250 0.6206 0.01161 0.00490 -0.0006 0.0072 1.0000
5.500 0.6451 0.01202 0.00538 0.0000 0.0063 1.0000
5.750 0.6690 0.01261 0.00607 0.0006 0.0055 1.0000
6.000 0.6925 0.01327 0.00681 0.0013 0.0046 1.0000
6.250 0.7154 0.01408 0.00772 0.0020 0.0041 1.0000
6.500 0.7366 0.01530 0.00907 0.0030 0.0037 1.0000
6.750 0.7560 0.01701 0.01097 0.0043 0.0035 1.0000
7.000 0.7755 0.01894 0.01311 0.0055 0.0035 1.0000
7.250 0.7946 0.02118 0.01561 0.0067 0.0034 1.0000
7.500 0.8135 0.02343 0.01813 0.0078 0.0034 1.0000
7.750 0.8312 0.02581 0.02087 0.0090 0.0034 1.0000
8.000 0.8478 0.02820 0.02355 0.0101 0.0034 1.0000
8.250 0.8627 0.03065 0.02629 0.0112 0.0035 1.0000
8.500 0.8751 0.03332 0.02927 0.0123 0.0035 1.0000
8.750 0.8847 0.03614 0.03239 0.0135 0.0036 1.0000
9.000 0.8866 0.03979 0.03637 0.0148 0.0035 1.0000
9.250 0.8767 0.04445 0.04136 0.0161 0.0035 1.0000
10.250 0.8232 0.06088 0.05844 0.0112 0.0035 1.0000
10.750 0.8033 0.07490 0.07268 -0.0005 0.0036 1.0000
11.250 0.6618 0.10057 0.09854 -0.0129 0.0044 1.0000
11.500 0.6489 0.10919 0.10714 -0.0163 0.0046 1.0000
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Polar data table (+)
Polar graphs
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