EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.33 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2010-il-1000000.txt Download as CSV file: xf-eh2010-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5452 0.12784 0.12623 0.0137 1.0000 0.0094
-11.500 -0.5430 0.12306 0.12146 0.0117 1.0000 0.0094
-9.000 -0.8132 0.02566 0.02236 -0.0157 1.0000 0.0063
-8.750 -0.8070 0.02198 0.01821 -0.0133 1.0000 0.0064
-8.500 -0.7934 0.01956 0.01548 -0.0115 1.0000 0.0068
-8.250 -0.7717 0.01873 0.01457 -0.0107 1.0000 0.0071
-8.000 -0.7481 0.01830 0.01410 -0.0101 1.0000 0.0074
-7.750 -0.7250 0.01774 0.01348 -0.0094 1.0000 0.0078
-7.500 -0.7017 0.01719 0.01284 -0.0086 1.0000 0.0083
-7.250 -0.6799 0.01625 0.01177 -0.0076 1.0000 0.0087
-7.000 -0.6577 0.01547 0.01086 -0.0065 1.0000 0.0090
-6.750 -0.6358 0.01470 0.00999 -0.0054 1.0000 0.0092
-6.500 -0.6006 0.01405 0.00923 -0.0071 0.9897 0.0094
-6.250 -0.5672 0.01218 0.00712 -0.0086 0.9703 0.0100
-6.000 -0.5351 0.01129 0.00608 -0.0096 0.9350 0.0108
-5.750 -0.5118 0.01101 0.00566 -0.0084 0.8922 0.0115
-5.500 -0.4882 0.01084 0.00535 -0.0074 0.8555 0.0125
-5.250 -0.4637 0.01059 0.00493 -0.0065 0.8236 0.0136
-5.000 -0.4379 0.01049 0.00472 -0.0060 0.7956 0.0143
-4.750 -0.4149 0.00977 0.00382 -0.0049 0.7710 0.0177
-4.500 -0.3888 0.00961 0.00357 -0.0045 0.7480 0.0200
-4.250 -0.3622 0.00951 0.00338 -0.0042 0.7272 0.0212
-4.000 -0.3368 0.00913 0.00290 -0.0036 0.7078 0.0258
-3.750 -0.3102 0.00898 0.00267 -0.0033 0.6896 0.0291
-3.500 -0.2839 0.00878 0.00241 -0.0029 0.6730 0.0357
-3.250 -0.2573 0.00860 0.00223 -0.0026 0.6569 0.0473
-3.000 -0.2306 0.00844 0.00206 -0.0023 0.6417 0.0598
-2.750 -0.2037 0.00830 0.00191 -0.0021 0.6274 0.0731
-2.500 -0.1768 0.00817 0.00178 -0.0019 0.6138 0.0888
-2.250 -0.1498 0.00805 0.00166 -0.0017 0.6007 0.1074
-2.000 -0.1230 0.00789 0.00154 -0.0015 0.5879 0.1338
-1.750 -0.0964 0.00771 0.00143 -0.0013 0.5756 0.1699
-1.500 -0.0706 0.00741 0.00133 -0.0010 0.5637 0.2386
-1.250 -0.0487 0.00661 0.00117 -0.0002 0.5530 0.4356
-1.000 -0.0299 0.00570 0.00104 0.0014 0.5429 0.6772
-0.750 -0.0056 0.00548 0.00102 0.0022 0.5322 0.7570
-0.500 0.0205 0.00540 0.00102 0.0028 0.5217 0.7992
-0.250 0.0470 0.00537 0.00103 0.0032 0.5116 0.8286
0.000 0.0731 0.00536 0.00106 0.0038 0.5016 0.8578
0.250 0.0994 0.00538 0.00108 0.0044 0.4918 0.8807
0.500 0.1258 0.00541 0.00112 0.0049 0.4821 0.8993
0.750 0.1522 0.00546 0.00115 0.0054 0.4729 0.9136
1.000 0.1783 0.00552 0.00119 0.0060 0.4635 0.9265
1.250 0.2043 0.00558 0.00124 0.0066 0.4545 0.9387
1.500 0.2298 0.00568 0.00132 0.0074 0.4458 0.9514
1.750 0.2577 0.00579 0.00139 0.0077 0.4365 0.9607
2.000 0.2864 0.00587 0.00144 0.0076 0.4277 0.9663
2.250 0.3163 0.00596 0.00148 0.0072 0.4187 0.9702
2.500 0.3492 0.00605 0.00153 0.0061 0.4094 0.9726
2.750 0.3824 0.00614 0.00160 0.0049 0.4006 0.9750
3.000 0.4149 0.00625 0.00166 0.0038 0.3915 0.9777
3.250 0.4463 0.00634 0.00173 0.0031 0.3826 0.9808
3.500 0.4793 0.00644 0.00179 0.0019 0.3737 0.9828
4.000 0.5492 0.00664 0.00195 -0.0014 0.3551 0.9851
4.250 0.5834 0.00675 0.00203 -0.0029 0.3461 0.9866
4.750 0.6499 0.00697 0.00223 -0.0055 0.3269 0.9905
5.000 0.6819 0.00710 0.00234 -0.0065 0.3177 0.9927
5.250 0.7145 0.00724 0.00246 -0.0077 0.3074 0.9944
5.500 0.7483 0.00739 0.00259 -0.0092 0.2939 0.9957
5.750 0.7817 0.00755 0.00271 -0.0106 0.2783 0.9972
6.000 0.8148 0.00772 0.00286 -0.0119 0.2641 0.9988
6.250 0.8464 0.00796 0.00302 -0.0131 0.2431 1.0000
6.500 0.8678 0.00822 0.00322 -0.0120 0.2246 1.0000
6.750 0.8886 0.00855 0.00346 -0.0109 0.2003 1.0000
7.000 0.9085 0.00898 0.00376 -0.0096 0.1711 1.0000
7.250 0.9279 0.00946 0.00410 -0.0083 0.1415 1.0000
7.500 0.9461 0.01010 0.00455 -0.0069 0.1068 1.0000
7.750 0.9627 0.01090 0.00514 -0.0052 0.0676 1.0000
8.000 0.9788 0.01178 0.00581 -0.0035 0.0331 1.0000
8.250 0.9968 0.01250 0.00645 -0.0021 0.0172 1.0000
8.500 1.0161 0.01312 0.00706 -0.0008 0.0104 1.0000
8.750 1.0344 0.01383 0.00780 0.0007 0.0069 1.0000
9.000 1.0553 0.01430 0.00832 0.0017 0.0062 1.0000
9.250 1.0754 0.01486 0.00893 0.0027 0.0055 1.0000
9.500 1.0943 0.01553 0.00966 0.0039 0.0050 1.0000
9.750 1.1107 0.01644 0.01069 0.0054 0.0046 1.0000
10.000 1.1247 0.01751 0.01188 0.0071 0.0043 1.0000
10.250 1.1421 0.01823 0.01269 0.0084 0.0042 1.0000
10.500 1.1586 0.01896 0.01349 0.0097 0.0040 1.0000
10.750 1.1728 0.01982 0.01444 0.0112 0.0038 1.0000
11.000 1.1841 0.02079 0.01550 0.0131 0.0037 1.0000
11.250 1.1949 0.02165 0.01642 0.0150 0.0034 1.0000
11.500 1.1928 0.02290 0.01778 0.0187 0.0035 1.0000
11.750 1.1955 0.02408 0.01905 0.0210 0.0033 1.0000
12.000 1.1954 0.02570 0.02076 0.0229 0.0032 1.0000
12.250 1.1953 0.02764 0.02280 0.0239 0.0031 1.0000
12.500 1.1966 0.02976 0.02501 0.0243 0.0031 1.0000
12.750 1.1938 0.03254 0.02791 0.0242 0.0030 1.0000
13.000 1.1917 0.03546 0.03092 0.0238 0.0029 1.0000
13.250 1.1865 0.03889 0.03446 0.0231 0.0028 1.0000
13.500 1.1832 0.04220 0.03788 0.0222 0.0028 1.0000
13.750 1.1792 0.04564 0.04147 0.0214 0.0030 1.0000
14.000 1.1726 0.04952 0.04544 0.0202 0.0029 1.0000
14.250 1.1653 0.05351 0.04955 0.0191 0.0029 1.0000
14.500 1.1563 0.05783 0.05396 0.0175 0.0028 1.0000
14.750 1.1491 0.06200 0.05824 0.0160 0.0028 1.0000
15.000 1.1415 0.06640 0.06275 0.0144 0.0028 1.0000
15.250 1.1284 0.07173 0.06819 0.0122 0.0027 1.0000
15.500 1.1234 0.07615 0.07273 0.0103 0.0028 1.0000
15.750 1.1146 0.08125 0.07793 0.0080 0.0028 1.0000
16.000 1.1006 0.08734 0.08415 0.0053 0.0027 1.0000
16.250 1.0926 0.09271 0.08963 0.0027 0.0028 1.0000
16.500 1.0836 0.09839 0.09543 -0.0001 0.0028 1.0000
16.750 1.0714 0.10485 0.10201 -0.0033 0.0028 1.0000
17.000 1.0607 0.11122 0.10852 -0.0067 0.0028 1.0000
17.250 1.0431 0.11922 0.11669 -0.0108 0.0029 1.0000
17.500 1.0238 0.12794 0.12557 -0.0154 0.0030 1.0000
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Polar data table (+)
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