EPPLER E850 AIRFOIL (e850-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E850 AIRFOIL (e850-il) Reynolds number: 50,000 Max Cl/Cd: 26.7 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e850-il-50000-n5.txt Download as CSV file: xf-e850-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E850 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5074 0.09583 0.08870 -0.0347 1.0000 0.0210
-8.750 -0.5108 0.09171 0.08466 -0.0359 1.0000 0.0209
-8.500 -0.5142 0.08796 0.08098 -0.0367 1.0000 0.0204
-8.250 -0.5199 0.08383 0.07693 -0.0381 1.0000 0.0202
-8.000 -0.5287 0.07980 0.07297 -0.0393 1.0000 0.0199
-7.750 -0.5396 0.07601 0.06925 -0.0405 1.0000 0.0197
-7.500 -0.5480 0.07206 0.06531 -0.0416 1.0000 0.0194
-7.250 -0.5552 0.06813 0.06133 -0.0422 1.0000 0.0192
-7.000 -0.5595 0.06427 0.05737 -0.0426 1.0000 0.0190
-6.750 -0.5608 0.06038 0.05331 -0.0428 1.0000 0.0187
-6.500 -0.5589 0.05636 0.04907 -0.0428 1.0000 0.0187
-6.250 -0.5529 0.05247 0.04488 -0.0428 1.0000 0.0186
-6.000 -0.5431 0.04869 0.04073 -0.0426 1.0000 0.0186
-5.750 -0.5298 0.04502 0.03662 -0.0424 1.0000 0.0191
-5.500 -0.5129 0.04163 0.03271 -0.0420 1.0000 0.0201
-5.250 -0.4933 0.03871 0.02923 -0.0413 1.0000 0.0211
-5.000 -0.4723 0.03586 0.02587 -0.0407 1.0000 0.0226
-4.750 -0.4524 0.03294 0.02244 -0.0403 1.0000 0.0255
-4.500 -0.4297 0.03077 0.01995 -0.0393 1.0000 0.0278
-4.250 -0.4066 0.02881 0.01768 -0.0378 1.0000 0.0291
-4.000 -0.3843 0.02709 0.01568 -0.0360 1.0000 0.0311
-3.750 -0.3620 0.02558 0.01383 -0.0343 1.0000 0.0343
-3.500 -0.3394 0.02409 0.01223 -0.0336 1.0000 0.0473
-3.250 -0.3133 0.02167 0.01016 -0.0343 1.0000 0.1052
-3.000 -0.3015 0.01911 0.01021 -0.0311 1.0000 0.6084
-2.750 -0.2941 0.01928 0.01050 -0.0247 1.0000 0.6963
-2.500 -0.2826 0.01925 0.01034 -0.0200 1.0000 0.7452
-2.250 -0.2642 0.01905 0.00990 -0.0177 1.0000 0.7717
-2.000 -0.2431 0.01881 0.00940 -0.0162 1.0000 0.7910
-1.750 -0.2212 0.01858 0.00876 -0.0151 1.0000 0.8112
-1.500 -0.1998 0.01836 0.00838 -0.0139 1.0000 0.8323
-1.250 -0.1777 0.01814 0.00803 -0.0129 1.0000 0.8564
-1.000 -0.1526 0.01794 0.00773 -0.0126 1.0000 0.8862
-0.750 -0.1185 0.01777 0.00745 -0.0144 1.0000 0.9274
-0.500 -0.0840 0.01751 0.00706 -0.0169 1.0000 1.0000
-0.250 -0.0569 0.01757 0.00683 -0.0181 1.0000 1.0000
0.000 -0.0303 0.01768 0.00676 -0.0190 1.0000 1.0000
0.250 -0.0044 0.01783 0.00676 -0.0196 1.0000 1.0000
0.500 0.0209 0.01802 0.00683 -0.0200 1.0000 1.0000
0.750 0.0457 0.01824 0.00697 -0.0203 1.0000 1.0000
1.000 0.0699 0.01848 0.00715 -0.0205 1.0000 1.0000
1.250 0.0938 0.01875 0.00740 -0.0206 1.0000 1.0000
1.500 0.1172 0.01904 0.00770 -0.0205 1.0000 1.0000
1.750 0.1403 0.01937 0.00803 -0.0205 1.0000 1.0000
2.000 0.1630 0.01972 0.00843 -0.0204 1.0000 1.0000
2.250 0.1854 0.02011 0.00888 -0.0203 1.0000 1.0000
2.500 0.2222 0.02076 0.00967 -0.0231 0.9925 1.0000
2.750 0.2622 0.02142 0.01053 -0.0264 0.9827 1.0000
3.000 0.3023 0.02201 0.01159 -0.0296 0.9715 1.0000
3.250 0.3440 0.02256 0.01248 -0.0330 0.9587 1.0000
3.500 0.3893 0.02302 0.01336 -0.0368 0.9439 1.0000
3.750 0.4354 0.02318 0.01401 -0.0402 0.9222 1.0000
4.000 0.5127 0.02156 0.01325 -0.0458 0.8580 1.0000
4.250 0.5847 0.02190 0.01076 -0.0456 0.1498 1.0000
4.500 0.6053 0.02439 0.01271 -0.0445 0.0802 1.0000
4.750 0.6321 0.02642 0.01484 -0.0439 0.0583 1.0000
5.000 0.6641 0.02849 0.01708 -0.0441 0.0428 1.0000
5.250 0.7012 0.03164 0.02035 -0.0448 0.0375 1.0000
5.500 0.7348 0.03462 0.02384 -0.0445 0.0349 1.0000
5.750 0.7593 0.03710 0.02669 -0.0436 0.0296 1.0000
6.000 0.7786 0.04038 0.03025 -0.0426 0.0260 1.0000
6.250 0.7984 0.04362 0.03410 -0.0407 0.0250 1.0000
6.500 0.8140 0.04728 0.03829 -0.0386 0.0247 1.0000
6.750 0.8259 0.05104 0.04254 -0.0364 0.0246 1.0000
7.000 0.8347 0.05492 0.04685 -0.0342 0.0246 1.0000
7.250 0.8405 0.05888 0.05120 -0.0320 0.0246 1.0000
7.500 0.8432 0.06295 0.05560 -0.0299 0.0247 1.0000
7.750 0.8430 0.06704 0.05998 -0.0281 0.0248 1.0000
8.000 0.8399 0.07117 0.06434 -0.0264 0.0250 1.0000
8.250 0.8347 0.07518 0.06854 -0.0250 0.0252 1.0000
8.500 0.8263 0.07918 0.07267 -0.0238 0.0254 1.0000
8.750 0.8153 0.08305 0.07663 -0.0226 0.0256 1.0000
9.000 0.8045 0.08717 0.08081 -0.0224 0.0258 1.0000
9.250 0.7942 0.09162 0.08530 -0.0232 0.0261 1.0000
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Polar data table (+)
Polar graphs
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