EPPLER 642 AIRFOIL (e642-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 642 AIRFOIL (e642-il) Reynolds number: 500,000 Max Cl/Cd: 98.22 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e642-il-500000.txt Download as CSV file: xf-e642-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 642 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.2138 0.10238 0.09931 -0.0628 0.7624 0.0243
-11.750 -0.2713 0.10333 0.10014 -0.0711 0.7835 0.0225
-11.500 -0.2710 0.09922 0.09600 -0.0730 0.7781 0.0230
-11.250 -0.2352 0.08432 0.08123 -0.0712 0.7569 0.0253
-11.000 -0.2295 0.08170 0.07862 -0.0716 0.7541 0.0258
-10.750 -0.2294 0.07766 0.07458 -0.0732 0.7514 0.0260
-10.500 -0.2322 0.07313 0.07005 -0.0750 0.7490 0.0263
-10.250 -0.2369 0.06822 0.06514 -0.0772 0.7468 0.0266
-10.000 -0.2525 0.06073 0.05765 -0.0817 0.7451 0.0267
-9.750 -0.3140 0.04717 0.04393 -0.0909 0.7442 0.0261
-9.500 -0.3394 0.04289 0.03953 -0.0907 0.7418 0.0262
-9.250 -0.3578 0.03973 0.03628 -0.0890 0.7394 0.0263
-9.000 -0.3699 0.03743 0.03390 -0.0865 0.7367 0.0266
-8.750 -0.3817 0.03517 0.03154 -0.0832 0.7341 0.0269
-8.500 -0.3865 0.03258 0.02883 -0.0807 0.7317 0.0274
-7.000 -0.3870 0.02363 0.01701 -0.0650 0.7225 0.0199
-6.500 -0.3403 0.02101 0.01406 -0.0637 0.7182 0.0198
-6.250 -0.3146 0.01955 0.01244 -0.0634 0.7164 0.0197
-6.000 -0.2878 0.01795 0.01073 -0.0633 0.7146 0.0195
-5.750 -0.2616 0.01699 0.00966 -0.0631 0.7129 0.0196
-5.500 -0.2358 0.01630 0.00887 -0.0628 0.7109 0.0197
-5.250 -0.2117 0.01535 0.00789 -0.0623 0.7092 0.0200
-5.000 -0.1897 0.01448 0.00702 -0.0614 0.7073 0.0206
-4.750 -0.1667 0.01395 0.00648 -0.0607 0.7055 0.0214
-4.500 -0.1430 0.01353 0.00605 -0.0601 0.7036 0.0220
-4.250 -0.1188 0.01318 0.00567 -0.0595 0.7016 0.0231
-4.000 -0.0939 0.01290 0.00534 -0.0591 0.6997 0.0244
-3.750 -0.0698 0.01253 0.00493 -0.0585 0.6980 0.0265
-3.500 -0.0445 0.01230 0.00467 -0.0582 0.6962 0.0292
-3.250 -0.0197 0.01205 0.00443 -0.0577 0.6944 0.0371
-3.000 -0.0003 0.01129 0.00416 -0.0565 0.6926 0.1362
-2.750 0.0191 0.01062 0.00398 -0.0555 0.6906 0.2586
-2.500 0.0334 0.00965 0.00377 -0.0536 0.6884 0.4540
-2.250 0.0415 0.00850 0.00375 -0.0499 0.6864 0.7182
-2.000 0.0664 0.00889 0.00428 -0.0486 0.6844 0.8024
-1.750 0.0936 0.00920 0.00451 -0.0482 0.6825 0.8219
-1.500 0.1197 0.00968 0.00495 -0.0472 0.6807 0.8389
-1.250 0.1449 0.01020 0.00545 -0.0459 0.6788 0.8513
-1.000 0.1700 0.01047 0.00571 -0.0450 0.6767 0.8611
-0.750 0.1959 0.01071 0.00596 -0.0441 0.6745 0.8666
-0.500 0.2206 0.01097 0.00619 -0.0430 0.6722 0.8759
-0.250 0.2473 0.01129 0.00650 -0.0419 0.6700 0.8830
0.000 0.2724 0.01142 0.00658 -0.0411 0.6679 0.8905
0.250 0.3027 0.01159 0.00671 -0.0411 0.6658 0.8944
0.500 0.3309 0.01175 0.00682 -0.0411 0.6637 0.8993
0.750 0.3526 0.01171 0.00679 -0.0401 0.6611 0.9045
1.000 0.3811 0.01169 0.00677 -0.0402 0.6583 0.9066
1.250 0.4101 0.01168 0.00675 -0.0404 0.6555 0.9088
1.500 0.4379 0.01165 0.00670 -0.0405 0.6529 0.9111
1.750 0.4644 0.01161 0.00661 -0.0404 0.6503 0.9134
2.000 0.4886 0.01161 0.00658 -0.0400 0.6475 0.9158
2.250 0.5105 0.01153 0.00654 -0.0393 0.6441 0.9181
2.500 0.5364 0.01139 0.00641 -0.0390 0.6405 0.9192
2.750 0.5637 0.01129 0.00629 -0.0391 0.6372 0.9202
3.000 0.5921 0.01123 0.00619 -0.0394 0.6341 0.9211
3.250 0.6176 0.01117 0.00616 -0.0392 0.6304 0.9222
3.500 0.6428 0.01107 0.00610 -0.0389 0.6261 0.9231
3.750 0.6696 0.01098 0.00601 -0.0389 0.6220 0.9242
4.000 0.6974 0.01091 0.00591 -0.0392 0.6183 0.9251
4.250 0.7215 0.01082 0.00588 -0.0387 0.6133 0.9260
4.500 0.7474 0.01071 0.00580 -0.0386 0.6080 0.9269
4.750 0.7746 0.01063 0.00569 -0.0388 0.6035 0.9279
5.000 0.7992 0.01054 0.00568 -0.0384 0.5973 0.9288
5.250 0.8255 0.01045 0.00561 -0.0385 0.5912 0.9295
5.500 0.8517 0.01039 0.00558 -0.0385 0.5848 0.9301
5.750 0.8775 0.01032 0.00556 -0.0384 0.5771 0.9308
6.000 0.9035 0.01028 0.00556 -0.0384 0.5693 0.9315
6.250 0.9289 0.01025 0.00554 -0.0382 0.5596 0.9323
6.500 0.9527 0.01021 0.00555 -0.0378 0.5480 0.9330
6.750 0.9759 0.01020 0.00556 -0.0372 0.5349 0.9337
7.000 0.9979 0.01025 0.00561 -0.0364 0.5197 0.9345
7.250 1.0184 0.01037 0.00570 -0.0353 0.5027 0.9354
7.500 1.0372 0.01056 0.00585 -0.0339 0.4831 0.9364
7.750 1.0541 0.01082 0.00605 -0.0323 0.4610 0.9376
8.000 1.0653 0.01120 0.00633 -0.0297 0.4313 0.9393
8.250 1.0710 0.01163 0.00664 -0.0260 0.4011 0.9416
8.500 1.0781 0.01214 0.00705 -0.0228 0.3743 0.9435
8.750 1.0834 0.01280 0.00760 -0.0196 0.3454 0.9455
9.000 1.0878 0.01350 0.00820 -0.0164 0.3202 0.9477
9.250 1.0925 0.01423 0.00887 -0.0133 0.2962 0.9502
9.500 1.0964 0.01511 0.00968 -0.0105 0.2746 0.9532
9.750 1.1018 0.01607 0.01058 -0.0082 0.2527 0.9563
10.000 1.1046 0.01727 0.01168 -0.0058 0.2295 0.9599
10.250 1.1107 0.01841 0.01278 -0.0041 0.2088 0.9645
10.500 1.1179 0.01976 0.01405 -0.0029 0.1882 0.9693
10.750 1.1296 0.02114 0.01537 -0.0027 0.1667 0.9743
11.000 1.1425 0.02269 0.01683 -0.0031 0.1466 0.9808
11.250 1.1543 0.02411 0.01820 -0.0032 0.1282 1.0000
11.500 1.1612 0.02564 0.01966 -0.0023 0.1104 1.0000
11.750 1.1677 0.02724 0.02118 -0.0015 0.0946 1.0000
12.000 1.1735 0.02890 0.02276 -0.0007 0.0783 1.0000
12.250 1.1765 0.03079 0.02455 0.0002 0.0605 1.0000
12.500 1.1752 0.03306 0.02668 0.0013 0.0407 1.0000
12.750 1.1752 0.03531 0.02885 0.0023 0.0273 1.0000
13.000 1.1755 0.03761 0.03110 0.0032 0.0195 1.0000
13.250 1.1790 0.03972 0.03323 0.0038 0.0162 1.0000
13.500 1.1852 0.04164 0.03521 0.0042 0.0152 1.0000
13.750 1.1917 0.04357 0.03722 0.0045 0.0142 1.0000
14.000 1.1974 0.04562 0.03934 0.0048 0.0136 1.0000
14.250 1.2006 0.04796 0.04175 0.0051 0.0130 1.0000
14.500 1.2016 0.05058 0.04445 0.0053 0.0125 1.0000
14.750 1.2012 0.05345 0.04741 0.0054 0.0122 1.0000
15.000 1.2018 0.05628 0.05033 0.0054 0.0119 1.0000
15.250 1.2030 0.05911 0.05326 0.0052 0.0119 1.0000
15.500 1.2058 0.06183 0.05607 0.0050 0.0115 1.0000
15.750 1.2057 0.06495 0.05929 0.0046 0.0114 1.0000
16.000 1.2060 0.06811 0.06254 0.0041 0.0111 1.0000
16.250 1.2056 0.07141 0.06594 0.0035 0.0109 1.0000
16.500 1.2046 0.07485 0.06946 0.0028 0.0108 1.0000
16.750 1.2037 0.07836 0.07306 0.0020 0.0106 1.0000
17.000 1.2029 0.08191 0.07671 0.0011 0.0104 1.0000
17.250 1.2016 0.08558 0.08047 0.0000 0.0102 1.0000
17.500 1.1995 0.08941 0.08437 -0.0012 0.0099 1.0000
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Polar data table (+)
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