EPPLER 637 AIRFOIL (e637-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 637 AIRFOIL (e637-il) Reynolds number: 50,000 Max Cl/Cd: 24.93 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e637-il-50000-n5.txt Download as CSV file: xf-e637-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 637 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 -0.3572 0.10100 0.09495 -0.0152 1.0000 0.1177
-8.250 -0.3641 0.09825 0.09233 -0.0181 1.0000 0.1226
-8.000 -0.3940 0.09651 0.09075 -0.0234 1.0000 0.1248
-7.750 -0.3682 0.09116 0.08548 -0.0214 1.0000 0.1283
-7.500 -0.3617 0.08789 0.08230 -0.0213 1.0000 0.1320
-7.250 -0.3671 0.08501 0.07954 -0.0220 1.0000 0.1359
-7.000 -0.3897 0.08270 0.07732 -0.0248 1.0000 0.1426
-6.750 -0.3762 0.07887 0.07362 -0.0236 1.0000 0.1454
-6.500 -0.3739 0.07601 0.07089 -0.0231 1.0000 0.1486
-6.250 -0.3632 0.06682 0.06099 -0.0324 0.9494 0.0667
-6.000 -0.3364 0.06094 0.05469 -0.0362 0.9116 0.0546
-5.750 -0.3075 0.05680 0.05038 -0.0388 0.8811 0.0518
-5.500 -0.2871 0.05312 0.04637 -0.0397 0.8529 0.0498
-5.250 -0.2706 0.04989 0.04272 -0.0392 0.8279 0.0480
-5.000 -0.2551 0.04682 0.03913 -0.0378 0.8064 0.0461
-4.750 -0.2386 0.04413 0.03559 -0.0355 0.7879 0.0441
-4.500 -0.2206 0.04182 0.03292 -0.0339 0.7698 0.0439
-4.250 -0.2022 0.03965 0.03032 -0.0322 0.7531 0.0444
-4.000 -0.1828 0.03779 0.02829 -0.0311 0.7369 0.0460
-3.750 -0.1616 0.03609 0.02622 -0.0297 0.7224 0.0473
-3.500 -0.1387 0.03440 0.02413 -0.0284 0.7081 0.0484
-3.250 -0.1138 0.03271 0.02205 -0.0272 0.6945 0.0489
-3.000 -0.0872 0.03118 0.02012 -0.0263 0.6815 0.0497
-2.750 -0.0584 0.02978 0.01835 -0.0257 0.6697 0.0509
-2.500 -0.0275 0.02861 0.01678 -0.0253 0.6585 0.0538
-2.250 0.0044 0.02748 0.01561 -0.0257 0.6461 0.0591
-2.000 0.0380 0.02657 0.01441 -0.0260 0.6350 0.0642
-1.750 0.0666 0.02572 0.01342 -0.0257 0.6255 0.0719
-1.250 0.2562 0.02124 0.01137 -0.0475 0.5984 1.0000
-1.000 0.2787 0.02135 0.01110 -0.0465 0.5901 1.0000
-0.750 0.3010 0.02149 0.01096 -0.0457 0.5809 1.0000
-0.500 0.3233 0.02166 0.01085 -0.0448 0.5731 1.0000
-0.250 0.3457 0.02185 0.01083 -0.0440 0.5647 1.0000
0.000 0.3684 0.02206 0.01080 -0.0432 0.5576 1.0000
0.250 0.3909 0.02233 0.01090 -0.0425 0.5497 1.0000
0.500 0.4135 0.02254 0.01087 -0.0415 0.5437 1.0000
0.750 0.4356 0.02290 0.01114 -0.0409 0.5356 1.0000
1.000 0.4580 0.02315 0.01121 -0.0399 0.5297 1.0000
1.250 0.4798 0.02355 0.01153 -0.0392 0.5228 1.0000
1.500 0.5017 0.02390 0.01176 -0.0383 0.5165 1.0000
1.750 0.5241 0.02420 0.01191 -0.0373 0.5114 1.0000
2.000 0.5449 0.02474 0.01244 -0.0366 0.5042 1.0000
2.250 0.5669 0.02510 0.01271 -0.0356 0.4990 1.0000
2.500 0.5883 0.02557 0.01311 -0.0347 0.4936 1.0000
2.750 0.6086 0.02615 0.01370 -0.0338 0.4872 1.0000
3.000 0.6305 0.02653 0.01400 -0.0328 0.4825 1.0000
3.250 0.6508 0.02714 0.01461 -0.0319 0.4772 1.0000
3.500 0.6702 0.02782 0.01533 -0.0309 0.4712 1.0000
3.750 0.6918 0.02826 0.01571 -0.0299 0.4668 1.0000
4.000 0.7114 0.02893 0.01640 -0.0289 0.4618 1.0000
4.250 0.7289 0.02980 0.01737 -0.0279 0.4560 1.0000
4.500 0.7499 0.03031 0.01785 -0.0268 0.4515 1.0000
4.750 0.7701 0.03093 0.01847 -0.0258 0.4473 1.0000
5.000 0.7839 0.03213 0.01982 -0.0245 0.4410 1.0000
5.250 0.8034 0.03278 0.02052 -0.0234 0.4366 1.0000
5.500 0.8264 0.03315 0.02085 -0.0225 0.4333 1.0000
5.750 0.8337 0.03489 0.02280 -0.0209 0.4265 1.0000
6.000 0.8507 0.03575 0.02372 -0.0196 0.4217 1.0000
6.250 0.8732 0.03616 0.02416 -0.0187 0.4183 1.0000
6.500 0.8759 0.03823 0.02643 -0.0168 0.4117 1.0000
6.750 0.8886 0.03943 0.02772 -0.0154 0.4067 1.0000
7.000 0.9111 0.03982 0.02813 -0.0144 0.4032 1.0000
7.250 0.9041 0.04261 0.03111 -0.0121 0.3964 1.0000
7.500 0.9121 0.04412 0.03274 -0.0104 0.3911 1.0000
7.750 0.9358 0.04440 0.03307 -0.0094 0.3878 1.0000
8.000 0.9014 0.04927 0.03809 -0.0064 0.3787 1.0000
8.250 0.9145 0.05035 0.03924 -0.0050 0.3744 1.0000
8.500 0.9454 0.05001 0.03898 -0.0042 0.3716 1.0000
9.000 0.8299 0.06549 0.05443 -0.0021 0.3486 1.0000
9.250 0.8418 0.06685 0.05587 -0.0013 0.3437 1.0000
9.500 0.8532 0.06834 0.05742 -0.0005 0.3392 1.0000
10.000 0.8551 0.07370 0.06292 0.0001 0.3264 1.0000
10.250 0.8230 0.08040 0.06960 -0.0014 0.3156 1.0000
10.500 0.8463 0.08050 0.06985 -0.0003 0.3120 1.0000
10.750 0.8225 0.08632 0.07568 -0.0016 0.3021 1.0000
11.000 0.8432 0.08674 0.07621 -0.0006 0.2978 1.0000
11.500 0.8434 0.09268 0.08230 -0.0010 0.2838 1.0000
11.750 0.8297 0.09755 0.08721 -0.0022 0.2750 1.0000
12.000 0.8455 0.09850 0.08831 -0.0015 0.2698 1.0000
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Polar data table (+)
Polar graphs
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