E182 (8.47%) (e182-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 200,000 Max Cl/Cd: 58.8 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e182-il-200000-n5.txt Download as CSV file: xf-e182-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5905 0.09035 0.08721 0.0099 1.0000 0.0200
-8.500 -0.5900 0.08623 0.08313 0.0078 1.0000 0.0190
-8.250 -0.5944 0.08096 0.07791 0.0041 1.0000 0.0179
-8.000 -0.6117 0.06925 0.06620 -0.0065 1.0000 0.0150
-7.750 -0.6111 0.06373 0.06061 -0.0102 1.0000 0.0147
-7.500 -0.6083 0.05787 0.05463 -0.0134 1.0000 0.0143
-7.250 -0.6031 0.05193 0.04850 -0.0157 1.0000 0.0140
-7.000 -0.5955 0.04589 0.04217 -0.0173 1.0000 0.0136
-6.750 -0.5822 0.03980 0.03564 -0.0187 0.9501 0.0132
-6.500 -0.5686 0.03465 0.02992 -0.0185 0.9134 0.0129
-6.250 -0.5551 0.03056 0.02525 -0.0169 0.8897 0.0127
-6.000 -0.5383 0.02728 0.02139 -0.0154 0.8714 0.0127
-5.750 -0.5186 0.02467 0.01823 -0.0140 0.8560 0.0128
-5.500 -0.4970 0.02258 0.01568 -0.0127 0.8424 0.0130
-5.250 -0.4739 0.02109 0.01382 -0.0117 0.8301 0.0137
-5.000 -0.4496 0.01989 0.01230 -0.0108 0.8188 0.0146
-4.750 -0.4248 0.01869 0.01084 -0.0100 0.8079 0.0150
-4.500 -0.4001 0.01757 0.00951 -0.0093 0.7981 0.0152
-4.000 -0.3512 0.01548 0.00715 -0.0078 0.7799 0.0160
-3.750 -0.3262 0.01477 0.00632 -0.0072 0.7717 0.0168
-3.500 -0.3004 0.01422 0.00564 -0.0067 0.7634 0.0179
-3.250 -0.2742 0.01375 0.00504 -0.0062 0.7556 0.0195
-3.000 -0.2481 0.01331 0.00451 -0.0058 0.7481 0.0236
-2.750 -0.2217 0.01285 0.00403 -0.0054 0.7408 0.0340
-2.500 -0.1962 0.01228 0.00362 -0.0050 0.7338 0.0824
-2.250 -0.1708 0.01172 0.00335 -0.0048 0.7270 0.1593
-2.000 -0.1459 0.01117 0.00312 -0.0044 0.7203 0.2529
-1.750 -0.1246 0.01023 0.00296 -0.0036 0.7141 0.4475
-1.500 -0.1036 0.00951 0.00285 -0.0021 0.7075 0.6071
-1.250 -0.0818 0.00891 0.00278 -0.0002 0.7022 0.7648
-1.000 -0.0270 0.00871 0.00281 -0.0049 0.6954 0.9078
-0.750 0.0225 0.00877 0.00275 -0.0091 0.6896 0.9591
-0.500 0.0636 0.00883 0.00268 -0.0118 0.6834 0.9841
-0.250 0.1096 0.00883 0.00256 -0.0158 0.6771 0.9994
0.000 0.1362 0.00886 0.00248 -0.0155 0.6714 1.0000
0.250 0.1621 0.00888 0.00244 -0.0152 0.6649 1.0000
0.500 0.1877 0.00893 0.00240 -0.0147 0.6594 1.0000
0.750 0.2139 0.00898 0.00241 -0.0144 0.6528 1.0000
1.000 0.2398 0.00903 0.00241 -0.0140 0.6467 1.0000
1.250 0.2659 0.00909 0.00243 -0.0137 0.6405 1.0000
1.500 0.2920 0.00915 0.00247 -0.0134 0.6337 1.0000
1.750 0.3181 0.00922 0.00251 -0.0130 0.6268 1.0000
2.000 0.3442 0.00928 0.00257 -0.0126 0.6185 1.0000
2.250 0.3704 0.00935 0.00263 -0.0122 0.6097 1.0000
2.500 0.3964 0.00942 0.00267 -0.0118 0.6010 1.0000
2.750 0.4227 0.00948 0.00276 -0.0114 0.5900 1.0000
3.000 0.4489 0.00955 0.00287 -0.0111 0.5787 1.0000
3.250 0.4751 0.00963 0.00296 -0.0107 0.5669 1.0000
3.500 0.5012 0.00971 0.00306 -0.0103 0.5539 1.0000
3.750 0.5273 0.00980 0.00320 -0.0099 0.5390 1.0000
4.000 0.5534 0.00990 0.00333 -0.0095 0.5215 1.0000
4.250 0.5791 0.01003 0.00344 -0.0090 0.4949 1.0000
4.500 0.6039 0.01027 0.00352 -0.0084 0.4425 1.0000
4.750 0.6281 0.01072 0.00373 -0.0080 0.3720 1.0000
5.000 0.6493 0.01187 0.00423 -0.0077 0.2458 1.0000
5.250 0.6710 0.01295 0.00486 -0.0074 0.1551 1.0000
5.500 0.6923 0.01406 0.00555 -0.0071 0.0802 1.0000
5.750 0.7137 0.01510 0.00631 -0.0066 0.0308 1.0000
6.000 0.7363 0.01590 0.00709 -0.0060 0.0196 1.0000
6.250 0.7595 0.01655 0.00784 -0.0054 0.0172 1.0000
6.500 0.7820 0.01729 0.00867 -0.0047 0.0157 1.0000
6.750 0.8033 0.01819 0.00967 -0.0040 0.0144 1.0000
7.000 0.8249 0.01896 0.01057 -0.0033 0.0133 1.0000
7.250 0.8454 0.01989 0.01164 -0.0025 0.0126 1.0000
7.500 0.8647 0.02095 0.01281 -0.0016 0.0121 1.0000
7.750 0.8833 0.02208 0.01404 -0.0006 0.0117 1.0000
8.000 0.9013 0.02332 0.01538 0.0005 0.0114 1.0000
8.250 0.9189 0.02465 0.01680 0.0016 0.0111 1.0000
8.500 0.9363 0.02608 0.01835 0.0027 0.0109 1.0000
8.750 0.9534 0.02769 0.02008 0.0038 0.0107 1.0000
9.000 0.9703 0.02945 0.02203 0.0049 0.0106 1.0000
9.250 0.9864 0.03138 0.02415 0.0060 0.0105 1.0000
9.500 1.0009 0.03359 0.02660 0.0071 0.0105 1.0000
9.750 1.0132 0.03589 0.02916 0.0083 0.0104 1.0000
10.000 1.0212 0.03864 0.03220 0.0097 0.0103 1.0000
10.500 1.0199 0.04479 0.03894 0.0129 0.0100 1.0000
10.750 1.0134 0.04685 0.04129 0.0148 0.0098 1.0000
11.000 1.0044 0.04992 0.04461 0.0156 0.0097 1.0000
11.250 0.9945 0.05337 0.04829 0.0156 0.0097 1.0000
11.500 0.9827 0.05726 0.05241 0.0148 0.0096 1.0000
11.750 0.9683 0.06194 0.05730 0.0131 0.0096 1.0000
12.000 0.9532 0.06710 0.06265 0.0107 0.0096 1.0000
12.250 0.9372 0.07287 0.06860 0.0075 0.0096 1.0000
12.500 0.9198 0.07948 0.07537 0.0035 0.0097 1.0000
12.750 0.9006 0.08717 0.08318 -0.0014 0.0098 1.0000
13.000 0.8843 0.09501 0.09113 -0.0064 0.0099 1.0000
13.250 0.8612 0.10601 0.10225 -0.0137 0.0099 1.0000
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Polar data table (+)
Polar graphs
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