E182 (8.47%) (e182-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: E182 (8.47%) (e182-il) Reynolds number: 50,000 Max Cl/Cd: 32.83 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e182-il-50000.txt Download as CSV file: xf-e182-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5750 0.12236 0.11603 0.0233 1.0000 0.2065
-9.250 -0.5568 0.11696 0.11063 0.0239 1.0000 0.2139
-9.000 -0.5760 0.11606 0.10986 0.0201 1.0000 0.2215
-8.750 -0.5509 0.11019 0.10396 0.0216 1.0000 0.2326
-8.500 -0.5446 0.10622 0.10004 0.0209 1.0000 0.2413
-8.250 -0.5588 0.10437 0.09833 0.0180 1.0000 0.2510
-8.000 -0.5536 0.10090 0.09491 0.0176 1.0000 0.2642
-7.750 -0.5393 0.09652 0.09054 0.0181 1.0000 0.2774
-7.500 -0.5326 0.09279 0.08683 0.0180 1.0000 0.2912
-7.250 -0.5278 0.08939 0.08350 0.0177 1.0000 0.3056
-7.000 -0.5399 0.08709 0.08135 0.0163 1.0000 0.3221
-6.500 -0.5106 0.07922 0.07354 0.0189 1.0000 0.3630
-6.250 -0.4975 0.07566 0.07003 0.0205 1.0000 0.3896
-5.750 -0.4987 0.05195 0.04509 -0.0223 1.0000 0.1345
-5.500 -0.4799 0.04646 0.03915 -0.0234 1.0000 0.1186
-5.250 -0.4611 0.04181 0.03357 -0.0238 1.0000 0.1080
-5.000 -0.4410 0.03836 0.02975 -0.0234 1.0000 0.1073
-4.750 -0.4215 0.03544 0.02634 -0.0226 1.0000 0.1078
-4.500 -0.4032 0.03292 0.02337 -0.0212 1.0000 0.1083
-4.250 -0.3874 0.03046 0.02067 -0.0195 1.0000 0.1093
-4.000 -0.3719 0.02844 0.01851 -0.0176 1.0000 0.1120
-3.750 -0.3553 0.02677 0.01662 -0.0158 1.0000 0.1168
-3.500 -0.3379 0.02524 0.01495 -0.0141 1.0000 0.1285
-3.250 -0.3184 0.02376 0.01334 -0.0126 1.0000 0.1482
-3.000 -0.1212 0.01643 0.00916 -0.0330 1.0000 1.0000
-2.750 -0.1262 0.01643 0.00892 -0.0299 1.0000 1.0000
-2.500 -0.1336 0.01661 0.00885 -0.0258 1.0000 1.0000
-2.250 -0.1347 0.01680 0.00876 -0.0224 1.0000 1.0000
-2.000 -0.1312 0.01702 0.00868 -0.0195 1.0000 1.0000
-1.750 -0.1246 0.01725 0.00863 -0.0171 1.0000 1.0000
-1.500 -0.1157 0.01751 0.00861 -0.0151 1.0000 1.0000
-1.250 -0.1048 0.01779 0.00864 -0.0133 1.0000 1.0000
-1.000 -0.0923 0.01809 0.00867 -0.0118 1.0000 1.0000
-0.750 -0.0788 0.01843 0.00878 -0.0106 1.0000 1.0000
-0.500 -0.0645 0.01879 0.00895 -0.0095 1.0000 1.0000
-0.250 -0.0272 0.01940 0.00933 -0.0128 0.9918 1.0000
0.000 0.0149 0.02011 0.00983 -0.0169 0.9820 1.0000
0.250 0.0579 0.02086 0.01042 -0.0211 0.9719 1.0000
0.500 0.0940 0.02154 0.01098 -0.0240 0.9614 1.0000
0.750 0.1302 0.02227 0.01162 -0.0269 0.9512 1.0000
1.000 0.1684 0.02304 0.01233 -0.0300 0.9413 1.0000
1.250 0.2075 0.02385 0.01310 -0.0332 0.9310 1.0000
1.500 0.2366 0.02460 0.01384 -0.0346 0.9199 1.0000
1.750 0.2669 0.02540 0.01466 -0.0362 0.9090 1.0000
2.000 0.2997 0.02625 0.01553 -0.0381 0.8978 1.0000
2.250 0.3352 0.02711 0.01645 -0.0404 0.8861 1.0000
2.500 0.3731 0.02797 0.01744 -0.0430 0.8737 1.0000
2.750 0.4070 0.02882 0.01840 -0.0448 0.8605 1.0000
3.000 0.4388 0.02967 0.01937 -0.0460 0.8464 1.0000
3.250 0.4698 0.03051 0.02035 -0.0469 0.8315 1.0000
3.500 0.4931 0.03140 0.02141 -0.0465 0.8152 1.0000
3.750 0.5179 0.03224 0.02241 -0.0461 0.7974 1.0000
4.000 0.5506 0.03288 0.02326 -0.0463 0.7784 1.0000
4.250 0.5827 0.03338 0.02399 -0.0458 0.7581 1.0000
4.500 0.6095 0.03379 0.02468 -0.0443 0.7356 1.0000
4.750 0.6365 0.03397 0.02511 -0.0422 0.7115 1.0000
5.000 0.6682 0.03345 0.02487 -0.0392 0.6865 1.0000
5.250 0.6978 0.03242 0.02416 -0.0350 0.6602 1.0000
5.500 0.7208 0.03144 0.02345 -0.0303 0.6293 1.0000
5.750 0.7441 0.02992 0.02220 -0.0250 0.5942 1.0000
6.000 0.7681 0.02743 0.01994 -0.0184 0.5513 1.0000
6.250 0.7883 0.02433 0.01692 -0.0109 0.4785 1.0000
6.500 0.7915 0.02411 0.01538 -0.0042 0.3020 1.0000
6.750 0.7890 0.02799 0.01781 -0.0011 0.1741 1.0000
7.000 0.8029 0.03105 0.02025 0.0012 0.1254 1.0000
7.250 0.8300 0.03365 0.02287 0.0030 0.1076 1.0000
7.500 0.8561 0.03640 0.02563 0.0041 0.0973 1.0000
7.750 0.8793 0.03900 0.02848 0.0051 0.0898 1.0000
8.000 0.9019 0.04264 0.03230 0.0059 0.0862 1.0000
8.250 0.9200 0.04627 0.03647 0.0071 0.0855 1.0000
8.500 0.9347 0.05026 0.04093 0.0081 0.0855 1.0000
8.750 0.9464 0.05466 0.04574 0.0090 0.0861 1.0000
9.000 0.9556 0.05896 0.05046 0.0099 0.0873 1.0000
9.250 0.9381 0.06377 0.05614 0.0108 0.0907 1.0000
9.500 0.9227 0.06894 0.06169 0.0108 0.0933 1.0000
9.750 0.9070 0.07390 0.06686 0.0104 0.0954 1.0000
10.000 0.8908 0.07871 0.07176 0.0099 0.0972 1.0000
10.250 0.8994 0.08391 0.07701 0.0098 0.1002 1.0000
10.500 0.8415 0.09101 0.08419 0.0029 0.1019 1.0000
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Polar data table (+)
Polar graphs
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