EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 50,000 Max Cl/Cd: 31.02 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e851-il-50000-n5.txt Download as CSV file: xf-e851-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E851 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4818 0.08641 0.07960 -0.0473 1.0000 0.0295
-8.250 -0.4901 0.08281 0.07609 -0.0475 1.0000 0.0292
-8.000 -0.5019 0.07952 0.07289 -0.0475 1.0000 0.0289
-7.750 -0.5131 0.07597 0.06941 -0.0480 1.0000 0.0287
-7.500 -0.5229 0.07242 0.06586 -0.0481 1.0000 0.0284
-7.250 -0.5312 0.06893 0.06234 -0.0480 1.0000 0.0282
-7.000 -0.5378 0.06522 0.05855 -0.0479 1.0000 0.0279
-6.750 -0.5411 0.06147 0.05465 -0.0477 1.0000 0.0277
-6.500 -0.5404 0.05777 0.05075 -0.0476 1.0000 0.0274
-6.250 -0.5362 0.05384 0.04654 -0.0476 1.0000 0.0271
-6.000 -0.5279 0.04991 0.04225 -0.0475 1.0000 0.0270
-5.750 -0.5156 0.04616 0.03808 -0.0474 1.0000 0.0269
-5.500 -0.4995 0.04246 0.03388 -0.0473 1.0000 0.0270
-5.250 -0.4803 0.03906 0.02994 -0.0470 1.0000 0.0274
-5.000 -0.4587 0.03602 0.02635 -0.0464 1.0000 0.0280
-4.750 -0.4357 0.03343 0.02323 -0.0455 1.0000 0.0291
-4.500 -0.4138 0.03101 0.02057 -0.0447 1.0000 0.0321
-4.250 -0.3914 0.02964 0.01888 -0.0438 1.0000 0.0410
-4.000 -0.3698 0.02770 0.01689 -0.0424 1.0000 0.0478
-3.750 -0.3474 0.02597 0.01479 -0.0411 1.0000 0.0593
-3.500 -0.3241 0.02447 0.01327 -0.0408 1.0000 0.0869
-3.250 -0.2960 0.02217 0.01140 -0.0420 1.0000 0.1660
-3.000 -0.2770 0.02053 0.01148 -0.0409 1.0000 0.5263
-2.750 -0.2627 0.02067 0.01170 -0.0372 1.0000 0.6182
-2.500 -0.2519 0.02083 0.01190 -0.0326 1.0000 0.6834
-2.250 -0.2396 0.02086 0.01186 -0.0286 1.0000 0.7299
-2.000 -0.2230 0.02075 0.01160 -0.0260 1.0000 0.7581
-1.750 -0.2029 0.02062 0.01125 -0.0247 1.0000 0.7781
-1.500 -0.1821 0.02049 0.01094 -0.0236 1.0000 0.7982
-1.250 -0.1617 0.02037 0.01054 -0.0224 1.0000 0.8197
-1.000 -0.1414 0.02024 0.01030 -0.0213 1.0000 0.8439
-0.750 -0.1195 0.02012 0.01010 -0.0205 1.0000 0.8751
-0.500 -0.0898 0.01998 0.00989 -0.0216 1.0000 0.9225
-0.250 -0.0526 0.01992 0.00967 -0.0250 0.9960 1.0000
0.000 -0.0157 0.02030 0.00981 -0.0283 0.9918 1.0000
0.250 0.0194 0.02066 0.00990 -0.0310 0.9870 1.0000
0.500 0.0555 0.02114 0.01021 -0.0338 0.9825 1.0000
0.750 0.0888 0.02154 0.01048 -0.0359 0.9773 1.0000
1.000 0.1226 0.02199 0.01083 -0.0381 0.9718 1.0000
1.250 0.1566 0.02245 0.01123 -0.0402 0.9664 1.0000
1.500 0.1887 0.02287 0.01163 -0.0420 0.9599 1.0000
1.750 0.2232 0.02336 0.01211 -0.0441 0.9540 1.0000
2.000 0.2550 0.02378 0.01255 -0.0457 0.9467 1.0000
2.250 0.2883 0.02424 0.01307 -0.0475 0.9397 1.0000
2.500 0.3227 0.02470 0.01362 -0.0495 0.9321 1.0000
2.750 0.3539 0.02511 0.01427 -0.0508 0.9232 1.0000
3.000 0.3897 0.02555 0.01486 -0.0529 0.9148 1.0000
3.250 0.4253 0.02594 0.01545 -0.0548 0.9052 1.0000
3.500 0.4582 0.02626 0.01599 -0.0561 0.8937 1.0000
3.750 0.4934 0.02652 0.01652 -0.0576 0.8812 1.0000
4.000 0.5320 0.02663 0.01712 -0.0594 0.8669 1.0000
4.250 0.5708 0.02648 0.01737 -0.0608 0.8484 1.0000
4.500 0.6172 0.02548 0.01687 -0.0619 0.8180 1.0000
4.750 0.6669 0.02302 0.01496 -0.0608 0.7598 1.0000
5.000 0.6834 0.02203 0.01425 -0.0560 0.6762 1.0000
5.250 0.7199 0.02375 0.01307 -0.0534 0.1931 1.0000
5.500 0.7314 0.02626 0.01480 -0.0513 0.1071 1.0000
5.750 0.7505 0.02835 0.01675 -0.0499 0.0760 1.0000
6.000 0.7796 0.03066 0.01920 -0.0495 0.0575 1.0000
6.250 0.8148 0.03322 0.02216 -0.0499 0.0408 1.0000
6.500 0.8531 0.03678 0.02592 -0.0508 0.0346 1.0000
6.750 0.8774 0.03905 0.02858 -0.0500 0.0277 1.0000
7.000 0.8983 0.04260 0.03238 -0.0492 0.0245 1.0000
7.250 0.9183 0.04623 0.03661 -0.0475 0.0237 1.0000
7.500 0.9323 0.05000 0.04094 -0.0454 0.0232 1.0000
7.750 0.9410 0.05391 0.04536 -0.0429 0.0229 1.0000
8.000 0.9454 0.05783 0.04973 -0.0403 0.0227 1.0000
8.250 0.9458 0.06178 0.05409 -0.0376 0.0227 1.0000
8.500 0.9424 0.06570 0.05835 -0.0350 0.0227 1.0000
8.750 0.9358 0.06955 0.06248 -0.0326 0.0228 1.0000
9.000 0.9249 0.07325 0.06641 -0.0301 0.0229 1.0000
9.250 0.9112 0.07689 0.07022 -0.0279 0.0230 1.0000
9.500 0.8959 0.08083 0.07431 -0.0266 0.0231 1.0000
9.750 0.8803 0.08512 0.07874 -0.0264 0.0233 1.0000
10.000 0.8645 0.08997 0.08368 -0.0275 0.0234 1.0000
10.250 0.8504 0.09527 0.08905 -0.0297 0.0236 1.0000
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Polar data table (+)
Polar graphs
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