EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 500,000 Max Cl/Cd: 85.36 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2012-il-500000-n5.txt Download as CSV file: xf-eh2012-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/12
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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8108 0.09003 0.08753 -0.0099 1.0000 0.0075
-13.750 -0.9108 0.06215 0.05933 -0.0285 1.0000 0.0072
-13.500 -0.9486 0.05056 0.04745 -0.0379 1.0000 0.0071
-13.250 -0.9687 0.04511 0.04180 -0.0404 1.0000 0.0072
-13.000 -0.9879 0.04084 0.03732 -0.0407 1.0000 0.0071
-12.750 -0.9991 0.03785 0.03414 -0.0396 1.0000 0.0071
-12.500 -1.0042 0.03564 0.03177 -0.0378 1.0000 0.0073
-12.250 -1.0101 0.03352 0.02946 -0.0352 1.0000 0.0073
-12.000 -1.0125 0.03174 0.02751 -0.0322 1.0000 0.0074
-11.750 -1.0112 0.03022 0.02581 -0.0292 1.0000 0.0075
-11.500 -1.0043 0.02874 0.02416 -0.0270 1.0000 0.0076
-11.250 -0.9945 0.02732 0.02256 -0.0250 1.0000 0.0078
-11.000 -0.9820 0.02605 0.02112 -0.0232 1.0000 0.0079
-10.750 -0.9679 0.02483 0.01974 -0.0216 1.0000 0.0080
-10.500 -0.9521 0.02375 0.01850 -0.0201 1.0000 0.0081
-10.250 -0.9357 0.02267 0.01728 -0.0187 1.0000 0.0083
-10.000 -0.9203 0.02145 0.01595 -0.0171 1.0000 0.0085
-9.750 -0.9020 0.02053 0.01493 -0.0158 1.0000 0.0088
-9.500 -0.8824 0.01973 0.01406 -0.0147 1.0000 0.0090
-9.250 -0.8621 0.01901 0.01325 -0.0136 1.0000 0.0093
-9.000 -0.8414 0.01832 0.01250 -0.0125 1.0000 0.0096
-8.750 -0.8204 0.01768 0.01176 -0.0114 1.0000 0.0100
-8.500 -0.7993 0.01707 0.01108 -0.0103 1.0000 0.0104
-8.250 -0.7726 0.01647 0.01040 -0.0104 0.9912 0.0109
-8.000 -0.7381 0.01576 0.00961 -0.0121 0.9675 0.0115
-7.750 -0.7032 0.01505 0.00883 -0.0139 0.9379 0.0125
-7.500 -0.6749 0.01459 0.00824 -0.0140 0.9018 0.0133
-7.250 -0.6521 0.01423 0.00772 -0.0129 0.8683 0.0141
-7.000 -0.6293 0.01392 0.00725 -0.0118 0.8389 0.0149
-6.750 -0.6066 0.01351 0.00673 -0.0108 0.8132 0.0163
-6.500 -0.5828 0.01320 0.00631 -0.0099 0.7898 0.0180
-6.250 -0.5583 0.01294 0.00591 -0.0092 0.7683 0.0196
-6.000 -0.5341 0.01262 0.00552 -0.0085 0.7481 0.0226
-5.750 -0.5089 0.01239 0.00519 -0.0079 0.7298 0.0256
-5.500 -0.4840 0.01210 0.00486 -0.0073 0.7124 0.0300
-5.250 -0.4585 0.01189 0.00457 -0.0068 0.6962 0.0342
-5.000 -0.4331 0.01166 0.00429 -0.0063 0.6806 0.0399
-4.750 -0.4073 0.01146 0.00403 -0.0059 0.6660 0.0452
-4.500 -0.3813 0.01127 0.00380 -0.0055 0.6523 0.0515
-4.250 -0.3554 0.01108 0.00358 -0.0051 0.6390 0.0586
-4.000 -0.3291 0.01093 0.00337 -0.0047 0.6262 0.0661
-3.750 -0.3029 0.01075 0.00318 -0.0044 0.6137 0.0756
-3.500 -0.2766 0.01058 0.00299 -0.0041 0.6018 0.0855
-3.250 -0.2502 0.01043 0.00282 -0.0037 0.5906 0.0968
-3.000 -0.2238 0.01029 0.00266 -0.0034 0.5794 0.1095
-2.750 -0.1975 0.01013 0.00251 -0.0031 0.5682 0.1256
-2.500 -0.1710 0.00997 0.00237 -0.0028 0.5578 0.1449
-2.250 -0.1447 0.00981 0.00224 -0.0025 0.5474 0.1686
-1.750 -0.0929 0.00939 0.00200 -0.0019 0.5276 0.2440
-1.500 -0.0683 0.00904 0.00187 -0.0014 0.5188 0.3171
-1.250 -0.0453 0.00856 0.00173 -0.0006 0.5097 0.4236
-1.000 -0.0244 0.00796 0.00161 0.0006 0.5011 0.5626
-0.500 0.0227 0.00746 0.00158 0.0026 0.4843 0.7174
-0.250 0.0484 0.00740 0.00160 0.0032 0.4759 0.7565
0.000 0.0747 0.00738 0.00162 0.0037 0.4674 0.7866
0.250 0.1008 0.00738 0.00167 0.0043 0.4596 0.8170
0.500 0.1269 0.00741 0.00173 0.0050 0.4512 0.8441
0.750 0.1530 0.00745 0.00179 0.0056 0.4434 0.8660
1.000 0.1791 0.00753 0.00187 0.0063 0.4354 0.8856
1.250 0.2058 0.00760 0.00193 0.0067 0.4276 0.8990
1.500 0.2334 0.00767 0.00197 0.0069 0.4199 0.9055
1.750 0.2609 0.00774 0.00200 0.0070 0.4124 0.9118
2.250 0.3169 0.00790 0.00210 0.0071 0.3971 0.9231
2.750 0.3739 0.00809 0.00224 0.0069 0.3820 0.9333
3.000 0.4012 0.00820 0.00230 0.0071 0.3746 0.9395
3.250 0.4309 0.00829 0.00239 0.0067 0.3668 0.9436
3.500 0.4608 0.00842 0.00249 0.0062 0.3595 0.9480
3.750 0.4893 0.00852 0.00258 0.0061 0.3521 0.9532
4.000 0.5191 0.00865 0.00269 0.0056 0.3446 0.9573
4.250 0.5508 0.00877 0.00281 0.0047 0.3367 0.9604
4.500 0.5814 0.00892 0.00293 0.0041 0.3293 0.9643
4.750 0.6100 0.00904 0.00306 0.0039 0.3220 0.9691
5.000 0.6421 0.00920 0.00320 0.0028 0.3146 0.9716
5.250 0.6748 0.00935 0.00335 0.0016 0.3065 0.9740
5.500 0.7069 0.00951 0.00351 0.0006 0.2988 0.9766
5.750 0.7380 0.00969 0.00369 -0.0003 0.2900 0.9797
6.000 0.7680 0.00986 0.00387 -0.0009 0.2821 0.9831
6.500 0.8338 0.01024 0.00427 -0.0035 0.2649 0.9869
6.750 0.8654 0.01046 0.00449 -0.0046 0.2561 0.9895
7.000 0.8961 0.01070 0.00472 -0.0055 0.2464 0.9923
7.250 0.9272 0.01093 0.00497 -0.0064 0.2361 0.9947
7.500 0.9586 0.01123 0.00525 -0.0076 0.2214 0.9971
7.750 0.9890 0.01164 0.00557 -0.0087 0.2004 0.9995
8.000 1.0091 0.01210 0.00593 -0.0076 0.1774 1.0000
8.250 1.0260 0.01259 0.00633 -0.0060 0.1555 1.0000
8.500 1.0430 0.01310 0.00676 -0.0043 0.1366 1.0000
8.750 1.0595 0.01367 0.00724 -0.0026 0.1170 1.0000
9.000 1.0745 0.01435 0.00781 -0.0008 0.0956 1.0000
9.250 1.0899 0.01502 0.00839 0.0009 0.0769 1.0000
9.500 1.1032 0.01583 0.00909 0.0029 0.0573 1.0000
9.750 1.1158 0.01669 0.00987 0.0049 0.0401 1.0000
10.000 1.1278 0.01758 0.01070 0.0070 0.0264 1.0000
10.250 1.1401 0.01841 0.01151 0.0089 0.0191 1.0000
10.500 1.1535 0.01913 0.01226 0.0107 0.0158 1.0000
10.750 1.1649 0.01993 0.01309 0.0127 0.0136 1.0000
11.000 1.1745 0.02063 0.01386 0.0151 0.0126 1.0000
11.250 1.1815 0.02141 0.01470 0.0177 0.0116 1.0000
11.500 1.1876 0.02234 0.01571 0.0200 0.0109 1.0000
11.750 1.1905 0.02360 0.01704 0.0221 0.0101 1.0000
12.000 1.1956 0.02490 0.01841 0.0236 0.0095 1.0000
12.250 1.2007 0.02635 0.01996 0.0247 0.0092 1.0000
12.500 1.2045 0.02808 0.02179 0.0255 0.0087 1.0000
12.750 1.2079 0.03001 0.02380 0.0259 0.0084 1.0000
13.000 1.2101 0.03220 0.02608 0.0260 0.0082 1.0000
13.250 1.2103 0.03472 0.02869 0.0259 0.0077 1.0000
13.500 1.2091 0.03752 0.03158 0.0255 0.0075 1.0000
13.750 1.2028 0.04100 0.03516 0.0249 0.0072 1.0000
14.000 1.1975 0.04448 0.03876 0.0240 0.0071 1.0000
14.250 1.1943 0.04778 0.04215 0.0232 0.0070 1.0000
14.500 1.1889 0.05142 0.04592 0.0222 0.0069 1.0000
14.750 1.1850 0.05494 0.04954 0.0212 0.0066 1.0000
15.000 1.1756 0.05924 0.05394 0.0198 0.0066 1.0000
15.250 1.1681 0.06346 0.05827 0.0183 0.0066 1.0000
15.500 1.1633 0.06741 0.06232 0.0169 0.0063 1.0000
15.750 1.1543 0.07208 0.06709 0.0151 0.0064 1.0000
16.000 1.1470 0.07665 0.07176 0.0133 0.0062 1.0000
16.250 1.1391 0.08135 0.07656 0.0113 0.0062 1.0000
16.500 1.1318 0.08611 0.08141 0.0093 0.0060 1.0000
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Polar data table (+)
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