EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 500,000 Max Cl/Cd: 83.77 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2010-il-500000-n5.txt Download as CSV file: xf-eh2010-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.8249 0.03714 0.03422 -0.0213 1.0000 0.0058
-9.500 -0.8309 0.03180 0.02834 -0.0191 1.0000 0.0059
-9.250 -0.8227 0.02881 0.02496 -0.0174 1.0000 0.0061
-9.000 -0.8156 0.02540 0.02109 -0.0153 1.0000 0.0062
-8.750 -0.8020 0.02310 0.01846 -0.0138 1.0000 0.0064
-8.500 -0.7832 0.02174 0.01693 -0.0127 1.0000 0.0067
-8.250 -0.7627 0.02065 0.01568 -0.0117 1.0000 0.0070
-8.000 -0.7412 0.01973 0.01463 -0.0109 1.0000 0.0072
-7.750 -0.7196 0.01875 0.01350 -0.0100 1.0000 0.0075
-7.500 -0.6974 0.01790 0.01252 -0.0091 1.0000 0.0078
-7.250 -0.6754 0.01698 0.01146 -0.0081 1.0000 0.0081
-7.000 -0.6486 0.01612 0.01044 -0.0082 0.9909 0.0086
-6.750 -0.6132 0.01536 0.00954 -0.0100 0.9624 0.0091
-6.500 -0.5780 0.01455 0.00856 -0.0117 0.9259 0.0097
-6.250 -0.5538 0.01382 0.00766 -0.0109 0.8844 0.0105
-6.000 -0.5309 0.01342 0.00710 -0.0097 0.8483 0.0112
-5.750 -0.5075 0.01305 0.00656 -0.0087 0.8169 0.0121
-5.500 -0.4833 0.01271 0.00604 -0.0079 0.7899 0.0132
-5.250 -0.4584 0.01242 0.00557 -0.0072 0.7657 0.0141
-4.750 -0.4088 0.01168 0.00460 -0.0059 0.7236 0.0181
-4.500 -0.3829 0.01148 0.00429 -0.0054 0.7044 0.0203
-4.000 -0.3314 0.01097 0.00363 -0.0045 0.6706 0.0269
-3.750 -0.3050 0.01079 0.00334 -0.0042 0.6551 0.0310
-3.500 -0.2790 0.01056 0.00308 -0.0038 0.6402 0.0383
-3.250 -0.2526 0.01037 0.00286 -0.0035 0.6262 0.0473
-3.000 -0.2261 0.01022 0.00265 -0.0032 0.6127 0.0567
-2.750 -0.1994 0.01008 0.00246 -0.0029 0.5999 0.0668
-2.500 -0.1728 0.00993 0.00230 -0.0027 0.5875 0.0791
-2.000 -0.1196 0.00961 0.00202 -0.0022 0.5636 0.1198
-1.750 -0.0934 0.00939 0.00188 -0.0019 0.5525 0.1563
-1.500 -0.0673 0.00917 0.00176 -0.0016 0.5419 0.2018
-1.000 -0.0174 0.00843 0.00151 -0.0008 0.5211 0.3759
-0.750 0.0012 0.00749 0.00136 0.0007 0.5119 0.6095
-0.500 0.0221 0.00705 0.00137 0.0023 0.5027 0.7450
-0.250 0.0465 0.00693 0.00141 0.0033 0.4930 0.8066
0.000 0.0722 0.00691 0.00145 0.0040 0.4838 0.8435
0.250 0.0983 0.00694 0.00147 0.0047 0.4746 0.8699
0.500 0.1248 0.00698 0.00152 0.0052 0.4653 0.8900
0.750 0.1514 0.00704 0.00156 0.0058 0.4564 0.9088
1.000 0.1779 0.00714 0.00163 0.0064 0.4476 0.9275
1.250 0.2061 0.00722 0.00169 0.0065 0.4385 0.9396
1.500 0.2364 0.00731 0.00172 0.0061 0.4298 0.9441
1.750 0.2662 0.00740 0.00175 0.0057 0.4209 0.9487
2.000 0.2942 0.00747 0.00179 0.0057 0.4123 0.9545
2.250 0.3261 0.00757 0.00184 0.0048 0.4037 0.9575
2.500 0.3576 0.00766 0.00189 0.0040 0.3946 0.9610
2.750 0.3879 0.00776 0.00196 0.0035 0.3862 0.9652
3.000 0.4174 0.00787 0.00203 0.0030 0.3778 0.9694
3.250 0.4504 0.00797 0.00211 0.0019 0.3686 0.9716
3.500 0.4830 0.00808 0.00220 0.0008 0.3602 0.9742
3.750 0.5150 0.00820 0.00230 -0.0002 0.3511 0.9770
4.000 0.5457 0.00831 0.00241 -0.0009 0.3425 0.9803
4.250 0.5771 0.00845 0.00252 -0.0018 0.3336 0.9830
4.500 0.6103 0.00858 0.00264 -0.0031 0.3241 0.9848
4.750 0.6429 0.00871 0.00279 -0.0043 0.3150 0.9870
5.000 0.6748 0.00886 0.00294 -0.0053 0.3060 0.9896
5.250 0.7058 0.00903 0.00310 -0.0062 0.2959 0.9923
5.500 0.7373 0.00918 0.00328 -0.0071 0.2859 0.9946
5.750 0.7695 0.00936 0.00347 -0.0083 0.2755 0.9968
6.000 0.8012 0.00959 0.00367 -0.0094 0.2594 0.9990
6.250 0.8274 0.00989 0.00389 -0.0094 0.2394 1.0000
6.500 0.8494 0.01014 0.00413 -0.0084 0.2240 1.0000
6.750 0.8708 0.01048 0.00443 -0.0074 0.2025 1.0000
7.000 0.8906 0.01100 0.00479 -0.0063 0.1702 1.0000
7.250 0.9102 0.01158 0.00522 -0.0051 0.1375 1.0000
7.500 0.9288 0.01226 0.00574 -0.0038 0.1045 1.0000
7.750 0.9448 0.01324 0.00645 -0.0023 0.0605 1.0000
8.000 0.9611 0.01417 0.00720 -0.0008 0.0304 1.0000
8.250 0.9797 0.01486 0.00784 0.0004 0.0189 1.0000
8.500 0.9999 0.01540 0.00844 0.0015 0.0140 1.0000
8.750 1.0195 0.01602 0.00909 0.0026 0.0103 1.0000
9.000 1.0393 0.01661 0.00973 0.0036 0.0083 1.0000
9.250 1.0575 0.01736 0.01053 0.0048 0.0068 1.0000
9.500 1.0763 0.01802 0.01129 0.0059 0.0060 1.0000
9.750 1.0945 0.01871 0.01205 0.0070 0.0054 1.0000
10.000 1.1109 0.01952 0.01292 0.0083 0.0048 1.0000
10.250 1.1238 0.02057 0.01406 0.0099 0.0043 1.0000
10.500 1.1394 0.02131 0.01492 0.0112 0.0041 1.0000
10.750 1.1518 0.02223 0.01594 0.0129 0.0039 1.0000
11.000 1.1601 0.02326 0.01708 0.0150 0.0037 1.0000
11.250 1.1648 0.02427 0.01818 0.0176 0.0035 1.0000
11.500 1.1653 0.02567 0.01969 0.0200 0.0035 1.0000
11.750 1.1674 0.02721 0.02133 0.0215 0.0034 1.0000
12.000 1.1678 0.02916 0.02339 0.0225 0.0033 1.0000
12.250 1.1679 0.03143 0.02578 0.0228 0.0032 1.0000
12.500 1.1691 0.03382 0.02827 0.0227 0.0031 1.0000
12.750 1.1673 0.03673 0.03130 0.0222 0.0030 1.0000
13.000 1.1664 0.03968 0.03436 0.0215 0.0029 1.0000
13.250 1.1638 0.04295 0.03772 0.0206 0.0028 1.0000
13.500 1.1588 0.04659 0.04148 0.0195 0.0028 1.0000
13.750 1.1529 0.05041 0.04543 0.0183 0.0029 1.0000
14.000 1.1475 0.05427 0.04939 0.0169 0.0028 1.0000
14.250 1.1393 0.05854 0.05381 0.0155 0.0029 1.0000
14.500 1.1320 0.06284 0.05820 0.0137 0.0027 1.0000
14.750 1.1245 0.06724 0.06271 0.0120 0.0027 1.0000
15.000 1.1169 0.07188 0.06745 0.0100 0.0027 1.0000
15.250 1.1031 0.07756 0.07324 0.0076 0.0025 1.0000
15.500 1.0990 0.08196 0.07775 0.0056 0.0026 1.0000
15.750 1.0900 0.08725 0.08314 0.0032 0.0026 1.0000
16.000 1.0749 0.09367 0.08969 0.0003 0.0024 1.0000
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Polar data table (+)
Polar graphs
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