E182 (8.47%) (e182-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 1,000,000 Max Cl/Cd: 92.68 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e182-il-1000000.txt Download as CSV file: xf-e182-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: E182 (8.47%)
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6092 0.08212 0.08075 0.0095 1.0000 0.0095
-8.250 -0.6175 0.07721 0.07587 0.0059 1.0000 0.0095
-8.000 -0.6272 0.07136 0.07004 0.0005 1.0000 0.0094
-7.750 -0.6295 0.06469 0.06316 -0.0048 0.9050 0.0096
-7.500 -0.6319 0.05814 0.05639 -0.0075 0.8702 0.0100
-7.250 -0.6293 0.05109 0.04908 -0.0095 0.8478 0.0104
-7.000 -0.6166 0.04355 0.04114 -0.0098 0.8315 0.0113
-6.750 -0.6084 0.03846 0.03565 -0.0096 0.8163 0.0113
-6.250 -0.5919 0.02751 0.02387 -0.0084 0.7915 0.0126
-6.000 -0.5704 0.02587 0.02204 -0.0080 0.7803 0.0131
-5.750 -0.5483 0.02406 0.01996 -0.0074 0.7702 0.0139
-4.750 -0.4529 0.01465 0.00912 -0.0035 0.7362 0.0109
-4.500 -0.4281 0.01286 0.00710 -0.0027 0.7291 0.0103
-4.250 -0.4024 0.01177 0.00586 -0.0020 0.7217 0.0101
-4.000 -0.3764 0.01100 0.00497 -0.0015 0.7150 0.0103
-3.750 -0.3499 0.01043 0.00430 -0.0011 0.7082 0.0107
-3.500 -0.3229 0.01005 0.00385 -0.0009 0.7020 0.0112
-3.250 -0.2962 0.00955 0.00326 -0.0005 0.6955 0.0116
-3.000 -0.2696 0.00907 0.00266 -0.0002 0.6896 0.0122
-2.750 -0.2422 0.00875 0.00228 0.0000 0.6838 0.0129
-2.500 -0.2147 0.00852 0.00200 0.0002 0.6778 0.0143
-2.250 -0.1870 0.00833 0.00174 0.0003 0.6723 0.0157
-2.000 -0.1598 0.00796 0.00149 0.0006 0.6667 0.0453
-1.750 -0.1337 0.00748 0.00131 0.0008 0.6613 0.1290
-1.500 -0.1070 0.00713 0.00119 0.0009 0.6559 0.2003
-1.250 -0.0806 0.00675 0.00108 0.0010 0.6504 0.2884
-1.000 -0.0554 0.00623 0.00100 0.0013 0.6452 0.4269
-0.750 -0.0299 0.00579 0.00094 0.0017 0.6398 0.5422
-0.500 -0.0080 0.00514 0.00089 0.0029 0.6345 0.7255
-0.250 0.0129 0.00455 0.00091 0.0048 0.6295 0.9031
0.000 0.0647 0.00458 0.00100 -0.0002 0.6234 0.9651
0.500 0.1426 0.00472 0.00103 -0.0048 0.6103 0.9880
1.000 0.2251 0.00480 0.00102 -0.0106 0.5948 0.9978
1.250 0.2612 0.00483 0.00100 -0.0125 0.5869 1.0000
1.500 0.2877 0.00484 0.00099 -0.0122 0.5788 1.0000
1.750 0.3141 0.00487 0.00098 -0.0118 0.5707 1.0000
2.000 0.3406 0.00490 0.00099 -0.0116 0.5620 1.0000
2.250 0.3672 0.00494 0.00101 -0.0113 0.5531 1.0000
2.500 0.3938 0.00499 0.00104 -0.0110 0.5433 1.0000
2.750 0.4205 0.00505 0.00107 -0.0107 0.5323 1.0000
3.000 0.4472 0.00510 0.00111 -0.0105 0.5208 1.0000
3.250 0.4738 0.00520 0.00116 -0.0102 0.5000 1.0000
3.500 0.5001 0.00541 0.00122 -0.0100 0.4582 1.0000
3.750 0.5264 0.00568 0.00133 -0.0099 0.4105 1.0000
4.000 0.5523 0.00610 0.00150 -0.0098 0.3467 1.0000
4.250 0.5773 0.00682 0.00183 -0.0097 0.2523 1.0000
4.500 0.6021 0.00755 0.00218 -0.0097 0.1679 1.0000
4.750 0.6262 0.00839 0.00261 -0.0096 0.0803 1.0000
5.000 0.6499 0.00930 0.00315 -0.0093 0.0142 1.0000
5.250 0.6753 0.00961 0.00348 -0.0089 0.0120 1.0000
5.500 0.7006 0.00996 0.00388 -0.0084 0.0107 1.0000
5.750 0.7254 0.01040 0.00439 -0.0080 0.0099 1.0000
6.000 0.7503 0.01080 0.00484 -0.0075 0.0095 1.0000
6.250 0.7746 0.01129 0.00540 -0.0070 0.0091 1.0000
6.500 0.7984 0.01187 0.00605 -0.0064 0.0088 1.0000
6.750 0.8215 0.01252 0.00678 -0.0057 0.0087 1.0000
7.000 0.8440 0.01326 0.00759 -0.0050 0.0085 1.0000
7.250 0.8663 0.01394 0.00833 -0.0043 0.0083 1.0000
7.500 0.8880 0.01468 0.00914 -0.0035 0.0080 1.0000
7.750 0.9087 0.01558 0.01011 -0.0025 0.0079 1.0000
8.000 0.9289 0.01654 0.01114 -0.0015 0.0078 1.0000
8.250 0.9486 0.01759 0.01229 -0.0005 0.0078 1.0000
8.500 0.9680 0.01871 0.01350 0.0006 0.0077 1.0000
8.750 0.9871 0.01990 0.01477 0.0017 0.0076 1.0000
9.000 1.0056 0.02121 0.01619 0.0027 0.0074 1.0000
9.250 1.0230 0.02277 0.01786 0.0038 0.0073 1.0000
9.500 1.0392 0.02468 0.01994 0.0051 0.0072 1.0000
13.500 0.6825 0.12435 0.12286 -0.0193 0.0112 1.0000
13.750 0.6701 0.13080 0.12931 -0.0226 0.0112 1.0000
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Polar data table (+)
Polar graphs
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