EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.39 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2070-il-1000000.txt Download as CSV file: xf-eh2070-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/7.0
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5367 0.09551 0.09400 0.0122 1.0000 0.0066
-8.250 -0.5344 0.09174 0.09025 0.0102 1.0000 0.0066
-8.000 -0.5335 0.08792 0.08645 0.0080 1.0000 0.0066
-7.750 -0.5353 0.08416 0.08272 0.0057 1.0000 0.0066
-7.500 -0.5386 0.08033 0.07890 0.0027 1.0000 0.0066
-7.250 -0.5344 0.07593 0.07448 -0.0006 1.0000 0.0066
-7.000 -0.5278 0.07160 0.07012 -0.0034 1.0000 0.0066
-6.750 -0.5195 0.06711 0.06559 -0.0058 1.0000 0.0066
-6.500 -0.5091 0.06263 0.06105 -0.0078 1.0000 0.0066
-6.250 -0.4968 0.05815 0.05649 -0.0093 1.0000 0.0066
-6.000 -0.4827 0.05377 0.05201 -0.0105 1.0000 0.0066
-5.750 -0.4673 0.04934 0.04746 -0.0113 1.0000 0.0066
-5.500 -0.4624 0.04039 0.03824 -0.0120 1.0000 0.0071
-5.250 -0.4447 0.03667 0.03436 -0.0119 1.0000 0.0074
-5.000 -0.4253 0.03372 0.03125 -0.0116 1.0000 0.0077
-4.750 -0.4049 0.03069 0.02806 -0.0110 1.0000 0.0080
-4.500 -0.3838 0.02774 0.02489 -0.0102 1.0000 0.0085
-4.250 -0.3469 0.02385 0.02068 -0.0123 0.9609 0.0093
-4.000 -0.3234 0.01589 0.01169 -0.0091 0.9074 0.0071
-3.750 -0.3011 0.01490 0.01034 -0.0074 0.8545 0.0068
-3.500 -0.2795 0.01181 0.00669 -0.0057 0.8152 0.0079
-3.250 -0.2541 0.01137 0.00606 -0.0051 0.7807 0.0088
-3.000 -0.2285 0.01059 0.00506 -0.0044 0.7514 0.0092
-2.750 -0.2024 0.01010 0.00441 -0.0039 0.7252 0.0100
-2.500 -0.1764 0.00953 0.00368 -0.0033 0.7018 0.0106
-2.250 -0.1508 0.00885 0.00281 -0.0027 0.6814 0.0108
-2.000 -0.1245 0.00842 0.00223 -0.0022 0.6622 0.0115
-1.750 -0.0982 0.00799 0.00162 -0.0016 0.6446 0.0147
-1.500 -0.0713 0.00773 0.00131 -0.0013 0.6278 0.0279
-1.250 -0.0447 0.00749 0.00117 -0.0011 0.6116 0.0713
-1.000 -0.0178 0.00731 0.00106 -0.0010 0.5959 0.1142
-0.750 0.0085 0.00700 0.00097 -0.0008 0.5813 0.2037
-0.500 0.0230 0.00506 0.00081 0.0011 0.5689 0.7676
-0.250 0.0453 0.00480 0.00083 0.0026 0.5560 0.8695
0.000 0.0689 0.00476 0.00086 0.0039 0.5434 0.9200
0.250 0.0945 0.00480 0.00087 0.0047 0.5309 0.9468
0.500 0.1230 0.00488 0.00089 0.0048 0.5184 0.9641
0.750 0.1559 0.00498 0.00091 0.0039 0.5059 0.9750
1.250 0.2336 0.00519 0.00096 -0.0009 0.4791 0.9862
1.500 0.2776 0.00530 0.00100 -0.0044 0.4651 0.9914
2.000 0.3461 0.00543 0.00102 -0.0074 0.4421 0.9958
2.250 0.3799 0.00548 0.00104 -0.0088 0.4311 0.9975
2.500 0.4134 0.00554 0.00107 -0.0102 0.4198 0.9993
2.750 0.4424 0.00561 0.00110 -0.0105 0.4090 1.0000
3.250 0.4908 0.00576 0.00120 -0.0092 0.3870 1.0000
3.500 0.5152 0.00585 0.00129 -0.0086 0.3750 1.0000
3.750 0.5397 0.00595 0.00137 -0.0079 0.3641 1.0000
4.000 0.5642 0.00606 0.00147 -0.0073 0.3502 1.0000
4.250 0.5885 0.00624 0.00157 -0.0067 0.3289 1.0000
4.500 0.6126 0.00649 0.00170 -0.0061 0.2940 1.0000
4.750 0.6362 0.00685 0.00190 -0.0055 0.2499 1.0000
5.000 0.6582 0.00754 0.00223 -0.0048 0.1704 1.0000
5.250 0.6756 0.00920 0.00313 -0.0037 0.0171 1.0000
5.500 0.6995 0.00968 0.00364 -0.0029 0.0089 1.0000
5.750 0.7223 0.01051 0.00467 -0.0019 0.0064 1.0000
6.000 0.7456 0.01115 0.00542 -0.0011 0.0062 1.0000
6.250 0.7681 0.01197 0.00639 -0.0002 0.0061 1.0000
6.500 0.7896 0.01298 0.00753 0.0008 0.0060 1.0000
6.750 0.8119 0.01382 0.00845 0.0016 0.0057 1.0000
7.000 0.8348 0.01453 0.00924 0.0023 0.0053 1.0000
7.250 0.8559 0.01565 0.01045 0.0032 0.0051 1.0000
7.500 0.8767 0.01690 0.01181 0.0042 0.0049 1.0000
7.750 0.8983 0.01797 0.01297 0.0050 0.0046 1.0000
8.000 0.9197 0.01897 0.01405 0.0057 0.0042 1.0000
8.250 0.9391 0.02035 0.01553 0.0064 0.0037 1.0000
8.500 0.9520 0.02404 0.01949 0.0081 0.0035 1.0000
8.750 0.9705 0.02589 0.02156 0.0093 0.0037 1.0000
10.500 0.9390 0.05348 0.05121 0.0206 0.0047 1.0000
10.750 0.9230 0.05796 0.05581 0.0181 0.0046 1.0000
11.000 0.9071 0.06337 0.06135 0.0144 0.0048 1.0000
11.250 0.8896 0.06991 0.06800 0.0094 0.0047 1.0000
11.500 0.8722 0.07723 0.07543 0.0038 0.0049 1.0000
11.750 0.8498 0.08654 0.08484 -0.0030 0.0052 1.0000
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Polar data table (+)
Polar graphs
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