Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 500,000 Max Cl/Cd: 67.09 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1070-il-500000.txt Download as CSV file: xf-eh1070-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5147 0.08129 0.07931 0.0054 1.0000 0.0139
-8.250 -0.5175 0.07628 0.07432 0.0031 1.0000 0.0139
-8.000 -0.5225 0.07101 0.06907 0.0001 1.0000 0.0139
-7.750 -0.5325 0.06540 0.06348 -0.0047 1.0000 0.0139
-7.500 -0.5435 0.06066 0.05870 -0.0073 1.0000 0.0139
-7.250 -0.5930 0.06510 0.06288 -0.0095 1.0000 0.0138
-7.000 -0.5862 0.06002 0.05767 -0.0112 1.0000 0.0139
-6.750 -0.5782 0.05504 0.05252 -0.0121 1.0000 0.0139
-6.500 -0.5685 0.05035 0.04762 -0.0124 1.0000 0.0140
-6.250 -0.5764 0.04034 0.03725 -0.0129 1.0000 0.0151
-6.000 -0.5612 0.03849 0.03534 -0.0129 1.0000 0.0163
-5.750 -0.5431 0.03651 0.03324 -0.0127 1.0000 0.0183
-5.500 -0.5242 0.03318 0.02964 -0.0119 1.0000 0.0200
-5.250 -0.4963 0.03258 0.02875 -0.0107 1.0000 0.0232
-5.000 -0.4748 0.03059 0.02644 -0.0095 1.0000 0.0236
-4.750 -0.4637 0.02341 0.01869 -0.0082 1.0000 0.0254
-4.500 -0.4392 0.01853 0.01322 -0.0056 1.0000 0.0147
-4.250 -0.4156 0.01597 0.01042 -0.0044 1.0000 0.0127
-4.000 -0.3918 0.01395 0.00811 -0.0031 1.0000 0.0126
-3.750 -0.3679 0.01266 0.00668 -0.0019 1.0000 0.0132
-3.500 -0.3439 0.01188 0.00580 -0.0009 1.0000 0.0141
-3.250 -0.3237 0.01032 0.00413 0.0007 1.0000 0.0167
-3.000 -0.3008 0.00972 0.00349 0.0017 1.0000 0.0186
-2.750 -0.2779 0.00920 0.00290 0.0029 1.0000 0.0215
-2.500 -0.2518 0.00847 0.00223 0.0033 0.9983 0.0523
-2.250 -0.2149 0.00763 0.00193 0.0007 0.9897 0.1850
-2.000 -0.1808 0.00640 0.00167 -0.0015 0.9797 0.4441
-1.750 -0.1543 0.00518 0.00161 -0.0014 0.9634 0.7487
-1.500 -0.1240 0.00494 0.00161 -0.0013 0.9437 0.8403
-1.250 -0.0964 0.00487 0.00156 -0.0006 0.9180 0.8825
-1.000 -0.0716 0.00490 0.00154 0.0008 0.8891 0.9160
-0.750 -0.0452 0.00499 0.00152 0.0017 0.8595 0.9378
-0.500 -0.0166 0.00510 0.00149 0.0020 0.8299 0.9540
-0.250 0.0171 0.00524 0.00147 0.0011 0.8006 0.9670
0.000 0.0593 0.00539 0.00147 -0.0017 0.7714 0.9760
0.250 0.1102 0.00559 0.00150 -0.0064 0.7414 0.9863
0.500 0.1532 0.00573 0.00149 -0.0097 0.7121 0.9935
0.750 0.1913 0.00580 0.00143 -0.0120 0.6837 0.9976
1.000 0.2234 0.00587 0.00137 -0.0130 0.6560 1.0000
1.250 0.2463 0.00592 0.00133 -0.0121 0.6306 1.0000
1.500 0.2696 0.00599 0.00131 -0.0113 0.6077 1.0000
1.750 0.2932 0.00606 0.00131 -0.0105 0.5865 1.0000
2.000 0.3169 0.00615 0.00135 -0.0098 0.5647 1.0000
2.250 0.3407 0.00625 0.00139 -0.0090 0.5433 1.0000
2.500 0.3646 0.00638 0.00145 -0.0083 0.5205 1.0000
2.750 0.3888 0.00650 0.00152 -0.0076 0.4979 1.0000
3.000 0.4130 0.00664 0.00161 -0.0069 0.4754 1.0000
3.250 0.4373 0.00680 0.00174 -0.0062 0.4521 1.0000
3.500 0.4617 0.00698 0.00187 -0.0056 0.4258 1.0000
3.750 0.4857 0.00724 0.00199 -0.0049 0.3801 1.0000
4.000 0.5090 0.00763 0.00215 -0.0042 0.3177 1.0000
4.250 0.5326 0.00806 0.00237 -0.0036 0.2581 1.0000
4.500 0.5526 0.00919 0.00285 -0.0028 0.1154 1.0000
4.750 0.5723 0.01070 0.00394 -0.0015 0.0182 1.0000
5.000 0.5963 0.01130 0.00466 -0.0007 0.0155 1.0000
5.250 0.6199 0.01196 0.00540 0.0001 0.0133 1.0000
5.500 0.6405 0.01328 0.00686 0.0013 0.0110 1.0000
5.750 0.6609 0.01480 0.00852 0.0026 0.0102 1.0000
6.000 0.6838 0.01590 0.00974 0.0036 0.0096 1.0000
6.250 0.7056 0.01760 0.01162 0.0048 0.0094 1.0000
6.500 0.7269 0.02001 0.01425 0.0061 0.0097 1.0000
6.750 0.7495 0.02229 0.01667 0.0072 0.0112 1.0000
7.250 0.7925 0.03000 0.02524 0.0109 0.0204 1.0000
7.500 0.7889 0.03937 0.03521 0.0121 0.0186 1.0000
7.750 0.8005 0.04233 0.03849 0.0132 0.0185 1.0000
8.000 0.8232 0.04133 0.03777 0.0145 0.0171 1.0000
8.250 0.8346 0.04408 0.04081 0.0156 0.0159 1.0000
8.500 0.8391 0.04768 0.04468 0.0164 0.0151 1.0000
8.750 0.8385 0.05150 0.04874 0.0170 0.0146 1.0000
9.000 0.8316 0.05557 0.05301 0.0173 0.0142 1.0000
9.250 0.8167 0.05930 0.05689 0.0178 0.0142 1.0000
9.500 0.7954 0.06389 0.06160 0.0156 0.0144 1.0000
9.750 0.7731 0.07118 0.06899 0.0089 0.0149 1.0000
10.000 0.7536 0.08181 0.07968 -0.0002 0.0158 1.0000
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Polar data table (+)
Polar graphs
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