EPPLER 908 AIRFOIL (e908-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 908 AIRFOIL (e908-il) Reynolds number: 100,000 Max Cl/Cd: 32.2 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e908-il-100000.txt Download as CSV file: xf-e908-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4998 0.10549 0.10106 -0.0297 1.0000 0.0876
-8.000 -0.5211 0.10373 0.09941 -0.0303 1.0000 0.0883
-7.750 -0.5425 0.10177 0.09754 -0.0305 1.0000 0.0886
-7.500 -0.5147 0.09616 0.09190 -0.0257 1.0000 0.0942
-7.250 -0.5261 0.09389 0.08970 -0.0243 1.0000 0.0966
-7.000 -0.5403 0.09116 0.08705 -0.0249 1.0000 0.0989
-6.750 -0.5572 0.08703 0.08291 -0.0321 1.0000 0.1012
-6.500 -0.5590 0.08235 0.07828 -0.0317 1.0000 0.1037
-6.250 -0.5524 0.07973 0.07570 -0.0280 1.0000 0.1088
-6.000 -0.5601 0.07471 0.07038 -0.0373 1.0000 0.1157
-5.750 -0.5505 0.07139 0.06729 -0.0314 1.0000 0.1201
-5.500 -0.5459 0.06664 0.06234 -0.0357 1.0000 0.1301
-5.250 -0.5359 0.06355 0.05918 -0.0339 1.0000 0.1376
-5.000 -0.5253 0.05958 0.05512 -0.0349 1.0000 0.1477
-4.750 -0.5117 0.05575 0.05116 -0.0361 1.0000 0.1606
-4.500 -0.4955 0.05215 0.04742 -0.0370 1.0000 0.1748
-4.250 -0.4767 0.04870 0.04381 -0.0381 1.0000 0.1903
-4.000 -0.4004 0.03416 0.02639 -0.0457 1.0000 0.0501
-3.750 -0.3741 0.03007 0.02199 -0.0460 1.0000 0.0458
-3.500 -0.3457 0.02738 0.01871 -0.0455 1.0000 0.0420
-3.250 -0.3187 0.02553 0.01644 -0.0446 1.0000 0.0401
-3.000 -0.2929 0.02400 0.01469 -0.0438 1.0000 0.0396
-2.750 -0.2677 0.02266 0.01327 -0.0431 1.0000 0.0407
-2.500 -0.2430 0.02173 0.01228 -0.0427 1.0000 0.0470
-2.250 -0.2166 0.02067 0.01119 -0.0424 1.0000 0.0650
-2.000 -0.1926 0.01768 0.01117 -0.0415 1.0000 0.6628
-1.750 -0.1986 0.01748 0.01164 -0.0319 1.0000 0.8571
-1.500 -0.1739 0.01699 0.01097 -0.0308 1.0000 1.0000
-1.250 -0.1478 0.01718 0.01079 -0.0316 1.0000 1.0000
-1.000 -0.1224 0.01743 0.01072 -0.0323 1.0000 1.0000
-0.750 -0.0975 0.01771 0.01073 -0.0328 1.0000 1.0000
-0.500 -0.0733 0.01803 0.01083 -0.0331 1.0000 1.0000
-0.250 -0.0497 0.01838 0.01098 -0.0333 1.0000 1.0000
0.000 -0.0266 0.01876 0.01109 -0.0334 1.0000 1.0000
0.250 -0.0040 0.01917 0.01135 -0.0335 1.0000 1.0000
0.500 0.0182 0.01961 0.01166 -0.0335 1.0000 1.0000
0.750 0.0400 0.02008 0.01203 -0.0334 1.0000 1.0000
1.000 0.0614 0.02057 0.01244 -0.0333 1.0000 1.0000
1.250 0.0971 0.02149 0.01328 -0.0360 0.9950 1.0000
1.500 0.1382 0.02240 0.01415 -0.0398 0.9858 1.0000
1.750 0.1760 0.02320 0.01492 -0.0428 0.9769 1.0000
2.000 0.2170 0.02420 0.01590 -0.0464 0.9702 1.0000
2.250 0.2488 0.02467 0.01640 -0.0482 0.9605 1.0000
2.500 0.2814 0.02525 0.01702 -0.0501 0.9514 1.0000
2.750 0.3186 0.02597 0.01787 -0.0527 0.9437 1.0000
3.000 0.3521 0.02652 0.01852 -0.0547 0.9347 1.0000
3.250 0.3824 0.02702 0.01913 -0.0560 0.9248 1.0000
3.500 0.4167 0.02758 0.01984 -0.0580 0.9160 1.0000
3.750 0.4555 0.02814 0.02059 -0.0607 0.9079 1.0000
4.000 0.4854 0.02854 0.02120 -0.0617 0.8969 1.0000
4.250 0.5186 0.02890 0.02194 -0.0632 0.8857 1.0000
4.500 0.5567 0.02908 0.02247 -0.0651 0.8733 1.0000
4.750 0.7210 0.02239 0.01216 -0.0680 0.0406 1.0000
5.000 0.7588 0.02558 0.01522 -0.0695 0.0386 1.0000
5.250 0.8107 0.02884 0.01871 -0.0728 0.0390 1.0000
5.500 0.8553 0.03323 0.02338 -0.0749 0.0385 1.0000
5.750 0.8763 0.03411 0.02475 -0.0724 0.0360 1.0000
6.000 0.9092 0.03935 0.03022 -0.0730 0.0387 1.0000
6.250 0.9397 0.04171 0.03361 -0.0689 0.0588 1.0000
9.250 0.8889 0.08395 0.07972 -0.0267 0.1011 1.0000
9.500 0.8621 0.08786 0.08374 -0.0246 0.1011 1.0000
9.750 0.8364 0.09247 0.08844 -0.0240 0.1010 1.0000
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Polar data table (+)
Polar graphs
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