E182 (8.47%) (e182-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 500,000 Max Cl/Cd: 81.91 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e182-il-500000.txt Download as CSV file: xf-e182-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.6000 0.08449 0.08256 0.0088 1.0000 0.0178
-8.250 -0.6035 0.08001 0.07812 0.0056 1.0000 0.0179
-8.000 -0.6115 0.07492 0.07307 0.0010 1.0000 0.0179
-7.750 -0.6102 0.06973 0.06786 -0.0037 1.0000 0.0183
-7.500 -0.6064 0.06427 0.06233 -0.0079 1.0000 0.0190
-7.250 -0.6002 0.05847 0.05644 -0.0115 1.0000 0.0195
-7.000 -0.5906 0.05218 0.04997 -0.0145 1.0000 0.0210
-6.750 -0.5718 0.04774 0.04499 -0.0154 0.9162 0.0228
-6.500 -0.5661 0.02725 0.02416 -0.0113 0.8467 0.0236
-6.250 -0.5535 0.02360 0.02041 -0.0112 0.8340 0.0244
-6.000 -0.5363 0.02127 0.01793 -0.0109 0.8222 0.0253
-5.750 -0.5178 0.01912 0.01560 -0.0106 0.8116 0.0273
-5.500 -0.4900 0.01961 0.01568 -0.0094 0.8009 0.0316
-5.250 -0.4817 0.01265 0.00823 -0.0092 0.7934 0.0337
-5.000 -0.4597 0.01098 0.00645 -0.0089 0.7851 0.0350
-4.750 -0.4417 0.01769 0.01157 -0.0066 0.7953 0.0166
-4.500 -0.4160 0.01621 0.00991 -0.0059 0.7865 0.0159
-4.250 -0.3907 0.01458 0.00805 -0.0052 0.7777 0.0158
-4.000 -0.3648 0.01352 0.00684 -0.0046 0.7694 0.0159
-3.750 -0.3387 0.01281 0.00599 -0.0040 0.7617 0.0162
-3.500 -0.3140 0.01165 0.00472 -0.0033 0.7538 0.0169
-3.250 -0.2883 0.01101 0.00396 -0.0028 0.7468 0.0182
-3.000 -0.2613 0.01062 0.00353 -0.0025 0.7394 0.0201
-2.750 -0.2344 0.01028 0.00307 -0.0022 0.7329 0.0216
-2.500 -0.2070 0.00992 0.00265 -0.0019 0.7259 0.0260
-2.250 -0.1816 0.00923 0.00226 -0.0015 0.7196 0.1061
-2.000 -0.1559 0.00869 0.00208 -0.0013 0.7133 0.2022
-1.750 -0.1309 0.00809 0.00193 -0.0010 0.7069 0.3303
-1.500 -0.1068 0.00749 0.00181 -0.0004 0.7012 0.4738
-1.250 -0.0857 0.00672 0.00172 0.0008 0.6950 0.6612
-1.000 -0.0648 0.00598 0.00174 0.0030 0.6897 0.8795
-0.750 0.0008 0.00606 0.00186 -0.0045 0.6835 0.9669
-0.500 0.0430 0.00617 0.00186 -0.0074 0.6775 0.9848
-0.250 0.0919 0.00623 0.00182 -0.0119 0.6717 0.9952
0.000 0.1323 0.00622 0.00174 -0.0147 0.6653 1.0000
0.250 0.1580 0.00625 0.00168 -0.0143 0.6599 1.0000
0.500 0.1842 0.00624 0.00165 -0.0140 0.6533 1.0000
0.750 0.2101 0.00627 0.00161 -0.0135 0.6472 1.0000
1.000 0.2363 0.00629 0.00160 -0.0132 0.6401 1.0000
1.250 0.2624 0.00632 0.00158 -0.0128 0.6330 1.0000
1.500 0.2888 0.00634 0.00159 -0.0125 0.6253 1.0000
1.750 0.3149 0.00638 0.00158 -0.0121 0.6179 1.0000
2.000 0.3415 0.00640 0.00161 -0.0118 0.6092 1.0000
2.250 0.3678 0.00645 0.00163 -0.0114 0.6013 1.0000
2.500 0.3943 0.00648 0.00166 -0.0111 0.5920 1.0000
2.750 0.4208 0.00652 0.00171 -0.0108 0.5830 1.0000
3.000 0.4473 0.00658 0.00174 -0.0105 0.5731 1.0000
3.250 0.4739 0.00663 0.00181 -0.0102 0.5618 1.0000
3.500 0.5005 0.00668 0.00188 -0.0099 0.5501 1.0000
3.750 0.5269 0.00676 0.00193 -0.0096 0.5325 1.0000
4.000 0.5531 0.00687 0.00198 -0.0092 0.5006 1.0000
4.250 0.5791 0.00707 0.00208 -0.0089 0.4598 1.0000
4.500 0.6045 0.00747 0.00224 -0.0087 0.3931 1.0000
4.750 0.6288 0.00823 0.00258 -0.0086 0.2963 1.0000
5.000 0.6523 0.00915 0.00306 -0.0085 0.1995 1.0000
5.250 0.6748 0.01026 0.00367 -0.0083 0.0984 1.0000
5.500 0.6964 0.01151 0.00445 -0.0079 0.0206 1.0000
5.750 0.7211 0.01197 0.00495 -0.0074 0.0172 1.0000
6.000 0.7452 0.01255 0.00560 -0.0068 0.0153 1.0000
6.250 0.7683 0.01329 0.00646 -0.0061 0.0143 1.0000
6.500 0.7913 0.01398 0.00723 -0.0054 0.0138 1.0000
6.750 0.8132 0.01480 0.00815 -0.0046 0.0135 1.0000
7.000 0.8341 0.01575 0.00919 -0.0037 0.0132 1.0000
7.250 0.8542 0.01681 0.01035 -0.0026 0.0131 1.0000
7.500 0.8735 0.01805 0.01169 -0.0014 0.0132 1.0000
7.750 0.8931 0.01929 0.01304 -0.0003 0.0131 1.0000
8.000 0.9135 0.02039 0.01423 0.0007 0.0126 1.0000
8.250 0.9333 0.02182 0.01577 0.0018 0.0125 1.0000
8.500 0.9525 0.02364 0.01776 0.0030 0.0127 1.0000
8.750 0.9708 0.02594 0.02029 0.0043 0.0129 1.0000
9.000 0.9863 0.02897 0.02362 0.0057 0.0135 1.0000
13.750 0.7755 0.14606 0.14370 -0.0291 0.0206 1.0000
14.000 0.7752 0.15245 0.15007 -0.0322 0.0205 1.0000
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Polar data table (+)
Polar graphs
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