EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 50,000 Max Cl/Cd: 24.42 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e908-il-50000-n5.txt Download as CSV file: xf-e908-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 908 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 -0.4023 0.09843 0.09219 -0.0343 1.0000 0.0379
-8.250 -0.4806 0.10201 0.09553 -0.0351 1.0000 0.0392
-8.000 -0.4859 0.09903 0.09262 -0.0345 1.0000 0.0381
-7.750 -0.4943 0.09585 0.08954 -0.0339 1.0000 0.0369
-7.500 -0.5053 0.09282 0.08661 -0.0333 1.0000 0.0361
-7.250 -0.5154 0.08950 0.08337 -0.0334 1.0000 0.0354
-7.000 -0.5222 0.08538 0.07931 -0.0351 1.0000 0.0345
-6.750 -0.5278 0.08076 0.07472 -0.0369 1.0000 0.0334
-6.500 -0.5312 0.07572 0.06963 -0.0390 1.0000 0.0321
-6.250 -0.5313 0.06973 0.06342 -0.0422 1.0000 0.0302
-6.000 -0.5241 0.06581 0.05922 -0.0428 1.0000 0.0291
-5.750 -0.5182 0.06134 0.05461 -0.0432 1.0000 0.0287
-5.500 -0.5089 0.05694 0.04997 -0.0438 1.0000 0.0282
-5.250 -0.4958 0.05240 0.04491 -0.0447 1.0000 0.0279
-5.000 -0.4790 0.04815 0.04023 -0.0454 1.0000 0.0276
-4.750 -0.4587 0.04413 0.03570 -0.0460 1.0000 0.0275
-4.500 -0.4358 0.04048 0.03146 -0.0464 1.0000 0.0275
-4.250 -0.4107 0.03719 0.02754 -0.0465 1.0000 0.0279
-4.000 -0.3852 0.03449 0.02425 -0.0461 1.0000 0.0284
-3.750 -0.3598 0.03235 0.02161 -0.0454 1.0000 0.0296
-3.500 -0.3368 0.03025 0.01934 -0.0452 1.0000 0.0354
-3.250 -0.3128 0.02892 0.01762 -0.0440 1.0000 0.0412
-3.000 -0.2892 0.02731 0.01585 -0.0429 1.0000 0.0454
-2.750 -0.2646 0.02611 0.01436 -0.0421 1.0000 0.0538
-2.500 -0.2372 0.02463 0.01306 -0.0423 1.0000 0.0935
-2.250 -0.2200 0.02172 0.01323 -0.0408 1.0000 0.6062
-2.000 -0.2169 0.02148 0.01328 -0.0337 1.0000 0.7911
-1.750 -0.2019 0.02130 0.01272 -0.0302 1.0000 0.8621
-1.500 -0.1694 0.02081 0.01192 -0.0313 1.0000 1.0000
-1.250 -0.1453 0.02093 0.01159 -0.0316 1.0000 1.0000
-1.000 -0.1214 0.02111 0.01136 -0.0318 1.0000 1.0000
-0.750 -0.0957 0.02137 0.01127 -0.0323 0.9991 1.0000
-0.500 -0.0604 0.02192 0.01144 -0.0348 0.9944 1.0000
-0.250 -0.0273 0.02235 0.01158 -0.0368 0.9890 1.0000
0.000 0.0071 0.02290 0.01172 -0.0390 0.9841 1.0000
0.250 0.0394 0.02336 0.01197 -0.0408 0.9787 1.0000
0.500 0.0719 0.02385 0.01230 -0.0426 0.9731 1.0000
0.750 0.1044 0.02436 0.01267 -0.0445 0.9677 1.0000
1.000 0.1351 0.02479 0.01302 -0.0459 0.9615 1.0000
1.250 0.1680 0.02533 0.01348 -0.0478 0.9562 1.0000
1.500 0.1972 0.02574 0.01385 -0.0489 0.9494 1.0000
1.750 0.2304 0.02628 0.01438 -0.0508 0.9440 1.0000
2.000 0.2582 0.02669 0.01481 -0.0516 0.9367 1.0000
2.250 0.2910 0.02723 0.01540 -0.0534 0.9309 1.0000
2.500 0.3186 0.02766 0.01591 -0.0542 0.9233 1.0000
2.750 0.3493 0.02817 0.01664 -0.0555 0.9168 1.0000
3.000 0.3787 0.02864 0.01725 -0.0565 0.9094 1.0000
3.250 0.4065 0.02911 0.01788 -0.0573 0.9015 1.0000
3.500 0.4397 0.02962 0.01862 -0.0589 0.8948 1.0000
3.750 0.4650 0.03006 0.01928 -0.0591 0.8853 1.0000
4.000 0.4941 0.03052 0.02004 -0.0600 0.8765 1.0000
4.250 0.5282 0.03098 0.02109 -0.0615 0.8685 1.0000
4.500 0.5542 0.03138 0.02190 -0.0616 0.8575 1.0000
4.750 0.5823 0.03175 0.02275 -0.0619 0.8459 1.0000
5.000 0.6646 0.02722 0.01439 -0.0545 0.0473 1.0000
5.250 0.6829 0.02883 0.01608 -0.0529 0.0328 1.0000
5.500 0.7046 0.03079 0.01823 -0.0517 0.0289 1.0000
5.750 0.7518 0.03301 0.02086 -0.0537 0.0264 1.0000
6.000 0.8204 0.03668 0.02495 -0.0589 0.0248 1.0000
6.250 0.8634 0.04022 0.02894 -0.0603 0.0246 1.0000
6.500 0.8932 0.04364 0.03306 -0.0598 0.0245 1.0000
6.750 0.9146 0.04688 0.03678 -0.0582 0.0241 1.0000
7.000 0.9302 0.05001 0.04038 -0.0559 0.0232 1.0000
7.250 0.9415 0.05311 0.04390 -0.0533 0.0222 1.0000
7.500 0.9489 0.05616 0.04731 -0.0506 0.0209 1.0000
7.750 0.9539 0.05933 0.05081 -0.0479 0.0203 1.0000
8.000 0.9562 0.06262 0.05433 -0.0453 0.0193 1.0000
8.250 0.9550 0.06612 0.05810 -0.0425 0.0188 1.0000
8.500 0.9505 0.06972 0.06196 -0.0394 0.0186 1.0000
8.750 0.9446 0.07303 0.06553 -0.0363 0.0186 1.0000
9.000 0.9349 0.07611 0.06884 -0.0329 0.0187 1.0000
9.250 0.9187 0.07926 0.07236 -0.0290 0.0201 1.0000
9.500 0.9029 0.08301 0.07629 -0.0268 0.0205 1.0000
9.750 0.8862 0.08711 0.08054 -0.0256 0.0208 1.0000
10.000 0.8679 0.09208 0.08566 -0.0258 0.0224 1.0000
10.250 0.8520 0.09729 0.09096 -0.0273 0.0231 1.0000
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Polar data table (+)
Polar graphs
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