EPPLER 638 AIRFOIL (e638-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: EPPLER 638 AIRFOIL (e638-il) Reynolds number: 100,000 Max Cl/Cd: 32.15 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e638-il-100000.txt Download as CSV file: xf-e638-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 638 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3194 0.10543 0.10105 -0.0269 1.0000 0.0686
-9.000 -0.3287 0.10318 0.09890 -0.0311 1.0000 0.0690
-8.750 -0.3417 0.10064 0.09646 -0.0350 1.0000 0.0692
-8.500 -0.3032 0.09378 0.08960 -0.0277 1.0000 0.0722
-8.250 -0.2953 0.09081 0.08670 -0.0272 1.0000 0.0764
-8.000 -0.2970 0.08792 0.08392 -0.0286 1.0000 0.0788
-7.750 -0.3082 0.08527 0.08141 -0.0311 1.0000 0.0811
-7.500 -0.3234 0.08316 0.07944 -0.0323 1.0000 0.0821
-7.250 -0.3414 0.08211 0.07844 -0.0368 0.9877 0.0833
-7.000 -0.3091 0.07482 0.07125 -0.0405 0.9655 0.0861
-6.750 -0.2717 0.06993 0.06631 -0.0458 0.9375 0.0928
-6.500 -0.2496 0.06483 0.06077 -0.0564 0.9041 0.1001
-6.250 -0.2203 0.06046 0.05640 -0.0571 0.8759 0.1056
-6.000 -0.2161 0.05906 0.05437 -0.0590 0.8472 0.1151
-5.750 -0.1980 0.05463 0.05007 -0.0578 0.8242 0.1190
-5.500 -0.1906 0.05341 0.04834 -0.0573 0.8041 0.1310
-5.250 -0.1741 0.04973 0.04478 -0.0560 0.7850 0.1362
-5.000 -0.1628 0.04756 0.04234 -0.0550 0.7683 0.1492
-4.750 -0.1499 0.04535 0.03995 -0.0536 0.7531 0.1650
-4.500 -0.1357 0.04321 0.03772 -0.0521 0.7387 0.1837
-4.250 -0.1235 0.04138 0.03575 -0.0503 0.7258 0.2130
-4.000 -0.1105 0.03942 0.03376 -0.0481 0.7135 0.2464
-3.750 -0.0993 0.03801 0.03224 -0.0457 0.7008 0.2893
-3.500 -0.0851 0.03573 0.03006 -0.0431 0.6894 0.3238
-3.250 -0.0189 0.03211 0.02399 -0.0450 0.6821 0.1134
-3.000 0.0077 0.02912 0.02065 -0.0437 0.6712 0.0939
-2.750 0.0342 0.02729 0.01830 -0.0422 0.6616 0.0872
-2.500 0.0623 0.02629 0.01681 -0.0408 0.6522 0.0827
-2.250 0.0894 0.02487 0.01519 -0.0401 0.6421 0.0818
-2.000 0.1174 0.02390 0.01390 -0.0393 0.6343 0.0845
-1.750 0.1449 0.02270 0.01272 -0.0390 0.6246 0.0874
-1.500 0.1723 0.02191 0.01186 -0.0384 0.6168 0.0907
-1.250 0.1982 0.02141 0.01130 -0.0376 0.6081 0.0978
-1.000 0.3766 0.01734 0.00971 -0.0635 0.5931 1.0000
-0.750 0.3993 0.01751 0.00958 -0.0626 0.5866 1.0000
-0.500 0.4214 0.01771 0.00962 -0.0617 0.5785 1.0000
-0.250 0.4444 0.01790 0.00954 -0.0608 0.5730 1.0000
0.000 0.4660 0.01821 0.00979 -0.0600 0.5654 1.0000
0.250 0.4887 0.01843 0.00983 -0.0591 0.5597 1.0000
0.500 0.5106 0.01877 0.01008 -0.0582 0.5534 1.0000
0.750 0.5326 0.01907 0.01028 -0.0573 0.5470 1.0000
1.000 0.5559 0.01933 0.01034 -0.0564 0.5425 1.0000
1.250 0.5765 0.01982 0.01087 -0.0556 0.5360 1.0000
1.500 0.5987 0.02015 0.01111 -0.0547 0.5306 1.0000
1.750 0.6220 0.02047 0.01127 -0.0538 0.5264 1.0000
2.000 0.6413 0.02106 0.01194 -0.0528 0.5199 1.0000
2.250 0.6635 0.02144 0.01226 -0.0519 0.5151 1.0000
2.500 0.6871 0.02179 0.01247 -0.0511 0.5115 1.0000
2.750 0.7046 0.02257 0.01339 -0.0499 0.5052 1.0000
3.000 0.7263 0.02300 0.01377 -0.0489 0.5004 1.0000
3.250 0.7500 0.02333 0.01401 -0.0481 0.4967 1.0000
3.500 0.7661 0.02429 0.01511 -0.0468 0.4912 1.0000
3.750 0.7858 0.02493 0.01577 -0.0458 0.4864 1.0000
4.000 0.8094 0.02527 0.01603 -0.0449 0.4826 1.0000
4.250 0.8266 0.02616 0.01702 -0.0437 0.4778 1.0000
4.500 0.8421 0.02717 0.01814 -0.0423 0.4726 1.0000
4.750 0.8641 0.02767 0.01862 -0.0414 0.4688 1.0000
5.000 0.8898 0.02796 0.01882 -0.0408 0.4657 1.0000
5.250 0.8946 0.02977 0.02090 -0.0385 0.4591 1.0000
5.500 0.9134 0.03053 0.02171 -0.0374 0.4548 1.0000
5.750 0.9394 0.03078 0.02191 -0.0368 0.4518 1.0000
6.000 0.9439 0.03271 0.02404 -0.0346 0.4461 1.0000
6.250 0.9546 0.03408 0.02552 -0.0329 0.4407 1.0000
6.500 0.9801 0.03432 0.02577 -0.0322 0.4374 1.0000
6.750 0.9961 0.03541 0.02692 -0.0309 0.4334 1.0000
7.000 0.9816 0.03872 0.03048 -0.0275 0.4259 1.0000
7.250 1.0108 0.03859 0.03035 -0.0271 0.4226 1.0000
7.500 1.0508 0.03784 0.02954 -0.0275 0.4203 1.0000
7.750 0.9781 0.04569 0.03774 -0.0209 0.4093 1.0000
8.000 1.0267 0.04393 0.03599 -0.0213 0.4070 1.0000
8.250 1.0751 0.04242 0.03445 -0.0220 0.4046 1.0000
8.500 0.9058 0.05925 0.05140 -0.0144 0.3893 1.0000
8.750 1.0315 0.05004 0.04233 -0.0155 0.3908 1.0000
12.250 0.8249 0.11439 0.10717 -0.0180 0.2802 1.0000
12.500 0.8614 0.11251 0.10541 -0.0160 0.2750 1.0000
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Polar data table (+)
Polar graphs
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