EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/12 (eh2012-il) Reynolds number: 500,000 Max Cl/Cd: 89.28 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2012-il-500000.txt Download as CSV file: xf-eh2012-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7155 0.06225 0.05995 -0.0301 1.0000 0.0142
-11.250 -0.7518 0.05306 0.05056 -0.0373 1.0000 0.0140
-11.000 -0.7808 0.04775 0.04505 -0.0383 1.0000 0.0139
-10.750 -0.8128 0.04314 0.04018 -0.0361 1.0000 0.0137
-10.500 -0.8375 0.03956 0.03633 -0.0318 1.0000 0.0136
-10.250 -0.8515 0.03578 0.03219 -0.0282 1.0000 0.0136
-10.000 -0.8558 0.03243 0.02847 -0.0252 1.0000 0.0137
-9.750 -0.8519 0.02970 0.02540 -0.0227 1.0000 0.0138
-9.500 -0.8424 0.02747 0.02287 -0.0205 1.0000 0.0141
-9.250 -0.8295 0.02556 0.02069 -0.0187 1.0000 0.0143
-9.000 -0.8135 0.02404 0.01894 -0.0171 1.0000 0.0146
-8.750 -0.7955 0.02280 0.01750 -0.0156 1.0000 0.0148
-8.500 -0.7781 0.02131 0.01581 -0.0141 1.0000 0.0151
-8.250 -0.7632 0.01923 0.01354 -0.0122 1.0000 0.0157
-8.000 -0.7441 0.01826 0.01251 -0.0108 1.0000 0.0162
-7.750 -0.7241 0.01760 0.01181 -0.0095 1.0000 0.0170
-7.500 -0.7040 0.01705 0.01122 -0.0082 1.0000 0.0179
-7.250 -0.6852 0.01639 0.01048 -0.0065 1.0000 0.0188
-7.000 -0.6552 0.01583 0.00983 -0.0071 0.9952 0.0196
-6.750 -0.6203 0.01438 0.00833 -0.0091 0.9842 0.0217
-6.500 -0.5821 0.01379 0.00770 -0.0113 0.9696 0.0241
-6.250 -0.5472 0.01303 0.00685 -0.0129 0.9469 0.0268
-6.000 -0.5172 0.01258 0.00636 -0.0132 0.9173 0.0308
-5.750 -0.4941 0.01217 0.00584 -0.0120 0.8861 0.0354
-5.500 -0.4708 0.01195 0.00554 -0.0109 0.8573 0.0406
-5.250 -0.4481 0.01160 0.00510 -0.0097 0.8316 0.0470
-5.000 -0.4232 0.01151 0.00487 -0.0090 0.8078 0.0528
-4.750 -0.3994 0.01117 0.00450 -0.0081 0.7859 0.0614
-4.500 -0.3747 0.01095 0.00419 -0.0073 0.7656 0.0694
-4.250 -0.3491 0.01082 0.00397 -0.0068 0.7469 0.0777
-4.000 -0.3240 0.01057 0.00370 -0.0062 0.7292 0.0892
-3.750 -0.2987 0.01036 0.00346 -0.0056 0.7123 0.1019
-3.500 -0.2731 0.01016 0.00325 -0.0051 0.6964 0.1171
-3.250 -0.2476 0.00995 0.00304 -0.0046 0.6815 0.1368
-3.000 -0.2222 0.00972 0.00284 -0.0041 0.6670 0.1637
-2.750 -0.1974 0.00943 0.00266 -0.0036 0.6534 0.2041
-2.500 -0.1734 0.00905 0.00248 -0.0030 0.6405 0.2693
-2.250 -0.1522 0.00840 0.00225 -0.0019 0.6280 0.3937
-2.000 -0.1359 0.00748 0.00207 0.0001 0.6164 0.5928
-1.750 -0.1151 0.00710 0.00205 0.0018 0.6050 0.7042
-1.500 -0.0908 0.00699 0.00206 0.0028 0.5940 0.7621
-1.250 -0.0654 0.00698 0.00207 0.0037 0.5830 0.7980
-1.000 -0.0391 0.00699 0.00209 0.0043 0.5720 0.8230
-0.750 -0.0128 0.00703 0.00211 0.0049 0.5618 0.8432
-0.500 0.0137 0.00710 0.00212 0.0055 0.5519 0.8594
-0.250 0.0403 0.00715 0.00216 0.0061 0.5415 0.8740
0.000 0.0669 0.00723 0.00219 0.0066 0.5319 0.8869
0.500 0.1184 0.00745 0.00235 0.0084 0.5131 0.9159
0.750 0.1442 0.00760 0.00246 0.0093 0.5042 0.9291
1.000 0.1709 0.00778 0.00260 0.0100 0.4950 0.9420
1.250 0.2060 0.00797 0.00274 0.0089 0.4854 0.9488
1.500 0.2324 0.00808 0.00277 0.0093 0.4772 0.9557
1.750 0.2686 0.00816 0.00282 0.0076 0.4675 0.9577
2.000 0.3045 0.00826 0.00287 0.0059 0.4585 0.9599
2.250 0.3402 0.00838 0.00292 0.0042 0.4495 0.9624
2.500 0.3750 0.00846 0.00298 0.0027 0.4403 0.9654
2.750 0.4045 0.00858 0.00303 0.0023 0.4323 0.9702
3.000 0.4424 0.00865 0.00309 0.0001 0.4229 0.9716
3.250 0.4793 0.00875 0.00315 -0.0019 0.4142 0.9733
3.500 0.5149 0.00886 0.00321 -0.0037 0.4054 0.9756
3.750 0.5490 0.00894 0.00330 -0.0051 0.3968 0.9786
4.000 0.5790 0.00909 0.00339 -0.0057 0.3888 0.9829
4.250 0.6160 0.00915 0.00346 -0.0077 0.3796 0.9844
4.500 0.6519 0.00925 0.00355 -0.0096 0.3715 0.9865
4.750 0.6867 0.00936 0.00364 -0.0113 0.3627 0.9890
5.000 0.7205 0.00946 0.00375 -0.0127 0.3542 0.9918
5.500 0.7894 0.00968 0.00398 -0.0159 0.3366 0.9964
5.750 0.8241 0.00981 0.00410 -0.0176 0.3279 0.9988
6.000 0.8536 0.00994 0.00424 -0.0183 0.3194 1.0000
6.250 0.8750 0.01007 0.00440 -0.0172 0.3117 1.0000
6.500 0.8959 0.01024 0.00456 -0.0161 0.3038 1.0000
6.750 0.9171 0.01038 0.00474 -0.0149 0.2957 1.0000
7.250 0.9582 0.01075 0.00514 -0.0125 0.2782 1.0000
7.500 0.9785 0.01096 0.00535 -0.0112 0.2673 1.0000
7.750 0.9983 0.01119 0.00556 -0.0099 0.2540 1.0000
8.000 1.0180 0.01145 0.00580 -0.0086 0.2393 1.0000
8.250 1.0374 0.01175 0.00608 -0.0072 0.2246 1.0000
8.500 1.0568 0.01208 0.00639 -0.0059 0.2111 1.0000
8.750 1.0759 0.01245 0.00672 -0.0045 0.1961 1.0000
9.000 1.0945 0.01287 0.00710 -0.0031 0.1794 1.0000
9.250 1.1122 0.01338 0.00754 -0.0016 0.1620 1.0000
9.500 1.1291 0.01395 0.00804 -0.0001 0.1407 1.0000
9.750 1.1436 0.01471 0.00868 0.0017 0.1152 1.0000
10.000 1.1533 0.01582 0.00957 0.0041 0.0814 1.0000
10.250 1.1557 0.01740 0.01086 0.0073 0.0415 1.0000
10.500 1.1603 0.01875 0.01209 0.0102 0.0256 1.0000
10.750 1.1690 0.01974 0.01313 0.0126 0.0211 1.0000
11.000 1.1715 0.02082 0.01425 0.0159 0.0187 1.0000
11.250 1.1729 0.02190 0.01542 0.0191 0.0174 1.0000
11.500 1.1778 0.02296 0.01657 0.0213 0.0165 1.0000
11.750 1.1801 0.02434 0.01805 0.0233 0.0154 1.0000
12.000 1.1803 0.02609 0.01988 0.0247 0.0145 1.0000
12.250 1.1765 0.02844 0.02232 0.0257 0.0140 1.0000
12.500 1.1650 0.03183 0.02585 0.0261 0.0134 1.0000
12.750 1.1652 0.03436 0.02848 0.0260 0.0132 1.0000
13.000 1.1640 0.03715 0.03138 0.0257 0.0130 1.0000
13.250 1.1642 0.03991 0.03424 0.0253 0.0124 1.0000
13.500 1.1605 0.04315 0.03758 0.0247 0.0122 1.0000
13.750 1.1556 0.04662 0.04115 0.0239 0.0119 1.0000
14.000 1.1499 0.05021 0.04483 0.0230 0.0118 1.0000
14.250 1.1449 0.05381 0.04851 0.0221 0.0114 1.0000
14.500 1.1387 0.05757 0.05236 0.0210 0.0112 1.0000
14.750 1.1329 0.06143 0.05629 0.0198 0.0108 1.0000
15.000 1.1268 0.06539 0.06034 0.0186 0.0108 1.0000
15.250 1.1223 0.06923 0.06426 0.0173 0.0107 1.0000
15.500 1.1128 0.07376 0.06884 0.0158 0.0102 1.0000
15.750 1.1123 0.07721 0.07239 0.0146 0.0103 1.0000
16.000 1.1042 0.08125 0.07649 0.0138 0.0099 1.0000
16.250 1.1020 0.08480 0.08012 0.0129 0.0098 1.0000
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Polar data table (+)
Polar graphs
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