EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 337 AIRFOIL (e337-il) Reynolds number: 50,000 Max Cl/Cd: 15.97 at α=1° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e337-il-50000.txt Download as CSV file: xf-e337-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 337 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3934 0.11671 0.11036 -0.0108 1.0000 0.2062
-9.500 -0.3737 0.11211 0.10579 -0.0094 1.0000 0.2182
-9.250 -0.4017 0.11108 0.10492 -0.0127 1.0000 0.2232
-9.000 -0.3862 0.10699 0.10087 -0.0114 1.0000 0.2386
-8.750 -0.3772 0.10341 0.09736 -0.0105 1.0000 0.2541
-8.500 -0.3715 0.10017 0.09421 -0.0099 1.0000 0.2699
-8.250 -0.3779 0.09756 0.09172 -0.0096 1.0000 0.2872
-8.000 -0.3545 0.09342 0.08763 -0.0073 1.0000 0.3095
-7.750 -0.3551 0.09101 0.08533 -0.0059 1.0000 0.3339
-7.500 -0.3382 0.08775 0.08215 -0.0037 1.0000 0.3618
-7.250 -0.3301 0.08522 0.07972 -0.0011 1.0000 0.3967
-7.000 -0.3106 0.08235 0.07692 0.0025 1.0000 0.4441
-6.750 -0.2991 0.08040 0.07507 0.0065 1.0000 0.4965
-6.500 -0.2487 0.07672 0.07141 0.0097 1.0000 0.5735
-6.250 -0.1954 0.07297 0.06766 0.0113 1.0000 0.6646
-5.500 -0.2041 0.06556 0.06075 0.0131 1.0000 0.6623
-5.250 -0.2678 0.06581 0.06145 0.0184 1.0000 0.6271
-5.000 -0.3073 0.06735 0.06327 0.0258 1.0000 0.6296
-4.750 -0.3832 0.06161 0.05764 0.0122 0.9626 0.5229
-4.500 -0.3918 0.05075 0.04456 -0.0200 0.9285 0.2186
-4.250 -0.3349 0.04566 0.03809 -0.0239 0.9148 0.1375
-4.000 -0.2857 0.04195 0.03364 -0.0267 0.9011 0.1195
-3.750 -0.2437 0.03936 0.03028 -0.0279 0.8862 0.1127
-3.500 -0.2011 0.03700 0.02743 -0.0295 0.8713 0.1125
-3.250 0.1885 0.02410 0.01691 -0.0772 0.8786 1.0000
-3.000 0.2173 0.02409 0.01632 -0.0775 0.8546 1.0000
-2.750 0.2396 0.02427 0.01609 -0.0768 0.8333 1.0000
-2.500 0.2596 0.02453 0.01602 -0.0757 0.8139 1.0000
-2.250 0.2793 0.02484 0.01603 -0.0746 0.7965 1.0000
-2.000 0.2989 0.02518 0.01612 -0.0735 0.7810 1.0000
-1.750 0.3190 0.02556 0.01625 -0.0725 0.7669 1.0000
-1.500 0.3398 0.02593 0.01639 -0.0715 0.7541 1.0000
-1.250 0.3597 0.02638 0.01665 -0.0705 0.7413 1.0000
-1.000 0.3790 0.02696 0.01708 -0.0697 0.7290 1.0000
-0.750 0.3984 0.02752 0.01749 -0.0687 0.7184 1.0000
-0.500 0.4183 0.02799 0.01779 -0.0675 0.7084 1.0000
-0.250 0.4365 0.02880 0.01852 -0.0669 0.6976 1.0000
0.000 0.4565 0.02936 0.01893 -0.0657 0.6894 1.0000
0.250 0.4740 0.03025 0.01977 -0.0650 0.6794 1.0000
0.500 0.4924 0.03105 0.02048 -0.0640 0.6712 1.0000
0.750 0.5096 0.03198 0.02136 -0.0631 0.6626 1.0000
1.000 0.5265 0.03296 0.02229 -0.0621 0.6549 1.0000
1.250 0.5418 0.03409 0.02339 -0.0611 0.6468 1.0000
1.500 0.5587 0.03508 0.02432 -0.0599 0.6400 1.0000
1.750 0.5682 0.03675 0.02602 -0.0589 0.6321 1.0000
2.000 0.5895 0.03736 0.02654 -0.0576 0.6264 1.0000
2.250 0.5879 0.03991 0.02918 -0.0561 0.6184 1.0000
2.500 0.6026 0.04109 0.03033 -0.0547 0.6124 1.0000
2.750 0.6043 0.04327 0.03253 -0.0529 0.6063 1.0000
3.000 0.5970 0.04592 0.03522 -0.0505 0.6000 1.0000
3.250 0.6187 0.04672 0.03597 -0.0493 0.5947 1.0000
3.500 0.5927 0.05048 0.03977 -0.0458 0.5903 1.0000
3.750 0.5599 0.05416 0.04344 -0.0414 0.5872 1.0000
4.000 0.5260 0.05724 0.04649 -0.0361 0.5858 1.0000
4.250 0.4980 0.06008 0.04930 -0.0315 0.5866 1.0000
4.500 0.4803 0.06269 0.05188 -0.0282 0.5880 1.0000
4.750 0.4710 0.06518 0.05435 -0.0259 0.5901 1.0000
5.000 0.4741 0.06773 0.05690 -0.0250 0.5944 1.0000
5.250 0.3199 0.07423 0.06346 -0.0187 0.7414 1.0000
5.500 0.3274 0.07560 0.06480 -0.0172 0.7272 1.0000
5.750 0.3348 0.07717 0.06633 -0.0158 0.7149 1.0000
6.000 0.3548 0.07973 0.06888 -0.0162 0.7053 1.0000
6.250 0.3758 0.08206 0.07120 -0.0163 0.6916 1.0000
6.500 0.3768 0.08307 0.07218 -0.0141 0.6777 1.0000
6.750 0.3801 0.08458 0.07368 -0.0125 0.6660 1.0000
7.000 0.4039 0.08766 0.07677 -0.0133 0.6574 1.0000
7.250 0.4153 0.08941 0.07853 -0.0124 0.6436 1.0000
7.500 0.4144 0.09059 0.07971 -0.0104 0.6307 1.0000
7.750 0.4223 0.09272 0.08184 -0.0096 0.6212 1.0000
8.000 0.4525 0.09623 0.08539 -0.0108 0.6102 1.0000
8.250 0.4468 0.09700 0.08615 -0.0086 0.5971 1.0000
8.500 0.4496 0.09889 0.08805 -0.0076 0.5870 1.0000
8.750 0.4832 0.10305 0.09230 -0.0091 0.5778 1.0000
9.000 0.4744 0.10361 0.09286 -0.0070 0.5648 1.0000
9.250 0.4766 0.10561 0.09488 -0.0061 0.5548 1.0000
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Polar data table (+)
Polar graphs
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