EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 337 AIRFOIL (e337-il) Reynolds number: 100,000 Max Cl/Cd: 34.37 at α=11.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e337-il-100000.txt Download as CSV file: xf-e337-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3923 0.10783 0.10323 -0.0217 1.0000 0.0798
-9.500 -0.4095 0.10439 0.09987 -0.0279 1.0000 0.0804
-9.250 -0.4280 0.10087 0.09639 -0.0321 1.0000 0.0806
-9.000 -0.3836 0.09569 0.09126 -0.0241 1.0000 0.0839
-8.750 -0.3776 0.09242 0.08804 -0.0241 1.0000 0.0866
-8.500 -0.3796 0.08881 0.08451 -0.0260 1.0000 0.0890
-8.250 -0.3910 0.08483 0.08060 -0.0291 1.0000 0.0914
-8.000 -0.4115 0.08181 0.07762 -0.0301 1.0000 0.0931
-7.750 -0.4409 0.08020 0.07595 -0.0291 1.0000 0.0945
-7.500 -0.4680 0.07975 0.07530 -0.0264 1.0000 0.0953
-7.250 -0.4490 0.07277 0.06861 -0.0264 1.0000 0.0975
-7.000 -0.4390 0.06964 0.06563 -0.0246 1.0000 0.1006
-6.750 -0.4445 0.06748 0.06353 -0.0221 1.0000 0.1035
-6.500 -0.4570 0.06610 0.06220 -0.0198 0.9942 0.1066
-6.250 -0.4278 0.06067 0.05655 -0.0259 0.9706 0.1150
-6.000 -0.3996 0.05676 0.05225 -0.0306 0.9468 0.1284
-5.750 -0.3708 0.05342 0.04863 -0.0334 0.9224 0.1438
-5.500 -0.3408 0.04967 0.04472 -0.0358 0.9006 0.1601
-5.250 -0.3189 0.04636 0.04130 -0.0360 0.8743 0.1771
-5.000 -0.3002 0.04347 0.03835 -0.0350 0.8506 0.1957
-4.750 -0.2861 0.04149 0.03624 -0.0330 0.8267 0.2181
-4.500 -0.2743 0.03932 0.03400 -0.0306 0.8068 0.2464
-4.250 -0.2190 0.03262 0.02480 -0.0273 0.7940 0.0653
-4.000 -0.1960 0.03008 0.02194 -0.0257 0.7768 0.0610
-3.750 -0.1715 0.02822 0.01963 -0.0241 0.7606 0.0596
-3.500 -0.1455 0.02666 0.01770 -0.0228 0.7451 0.0600
-3.250 -0.1167 0.02504 0.01573 -0.0218 0.7304 0.0596
-3.000 -0.0864 0.02363 0.01408 -0.0213 0.7164 0.0606
-2.750 -0.0563 0.02249 0.01277 -0.0208 0.7034 0.0639
-2.500 -0.0281 0.02134 0.01159 -0.0203 0.6915 0.0737
-2.250 0.2463 0.01854 0.01120 -0.0574 0.6631 1.0000
-2.000 0.2672 0.01853 0.01095 -0.0566 0.6518 1.0000
-1.750 0.2884 0.01855 0.01070 -0.0556 0.6422 1.0000
-1.500 0.3098 0.01857 0.01057 -0.0548 0.6307 1.0000
-1.250 0.3313 0.01864 0.01045 -0.0540 0.6211 1.0000
-1.000 0.3531 0.01870 0.01033 -0.0532 0.6121 1.0000
-0.750 0.3752 0.01882 0.01033 -0.0525 0.6031 1.0000
-0.500 0.3973 0.01891 0.01025 -0.0516 0.5952 1.0000
-0.250 0.4195 0.01907 0.01033 -0.0510 0.5865 1.0000
0.000 0.4419 0.01921 0.01031 -0.0502 0.5795 1.0000
0.250 0.4642 0.01942 0.01048 -0.0495 0.5718 1.0000
0.500 0.4868 0.01959 0.01054 -0.0488 0.5648 1.0000
0.750 0.5092 0.01982 0.01069 -0.0480 0.5581 1.0000
1.000 0.5316 0.02005 0.01089 -0.0473 0.5508 1.0000
1.250 0.5547 0.02027 0.01095 -0.0466 0.5457 1.0000
1.500 0.5765 0.02062 0.01137 -0.0460 0.5383 1.0000
1.750 0.5992 0.02084 0.01152 -0.0452 0.5324 1.0000
2.000 0.6217 0.02118 0.01183 -0.0445 0.5269 1.0000
2.250 0.6435 0.02156 0.01226 -0.0438 0.5204 1.0000
2.500 0.6665 0.02182 0.01244 -0.0431 0.5154 1.0000
2.750 0.6879 0.02227 0.01294 -0.0423 0.5093 1.0000
3.000 0.7096 0.02268 0.01339 -0.0416 0.5034 1.0000
3.250 0.7328 0.02294 0.01358 -0.0408 0.4989 1.0000
3.500 0.7528 0.02356 0.01431 -0.0399 0.4928 1.0000
3.750 0.7740 0.02399 0.01478 -0.0391 0.4871 1.0000
4.000 0.7972 0.02427 0.01502 -0.0383 0.4828 1.0000
4.250 0.8153 0.02506 0.01597 -0.0373 0.4767 1.0000
4.500 0.8359 0.02554 0.01650 -0.0363 0.4711 1.0000
4.750 0.8591 0.02582 0.01671 -0.0355 0.4670 1.0000
5.000 0.8746 0.02681 0.01792 -0.0342 0.4607 1.0000
5.250 0.8943 0.02735 0.01853 -0.0331 0.4552 1.0000
5.500 0.9181 0.02757 0.01868 -0.0323 0.4512 1.0000
5.750 0.9300 0.02881 0.02019 -0.0306 0.4446 1.0000
6.000 0.9493 0.02934 0.02077 -0.0294 0.4392 1.0000
6.250 0.9745 0.02943 0.02080 -0.0286 0.4352 1.0000
6.500 0.9806 0.03106 0.02271 -0.0263 0.4280 1.0000
6.750 1.0009 0.03141 0.02312 -0.0251 0.4228 1.0000
7.000 1.0289 0.03130 0.02292 -0.0246 0.4190 1.0000
7.250 1.0265 0.03334 0.02532 -0.0214 0.4108 1.0000
7.500 1.0523 0.03320 0.02517 -0.0206 0.4060 1.0000
7.750 1.0608 0.03439 0.02652 -0.0183 0.3996 1.0000
8.000 1.0718 0.03526 0.02753 -0.0161 0.3931 1.0000
8.250 1.1059 0.03456 0.02674 -0.0160 0.3887 1.0000
8.500 1.0916 0.03713 0.02964 -0.0115 0.3809 1.0000
8.750 1.1198 0.03671 0.02924 -0.0108 0.3756 1.0000
9.000 1.1277 0.03769 0.03034 -0.0082 0.3695 1.0000
9.250 1.1286 0.03888 0.03170 -0.0049 0.3625 1.0000
9.500 1.1827 0.03679 0.02946 -0.0067 0.3572 1.0000
9.750 1.1426 0.04026 0.03330 0.0008 0.3494 1.0000
10.000 1.2043 0.03760 0.03051 -0.0017 0.3431 1.0000
10.250 1.1650 0.04081 0.03403 0.0059 0.3363 1.0000
10.500 1.2208 0.03845 0.03160 0.0040 0.3288 1.0000
10.750 1.1949 0.04064 0.03400 0.0104 0.3225 1.0000
11.000 1.2453 0.03851 0.03184 0.0091 0.3140 1.0000
11.250 1.2201 0.04045 0.03396 0.0154 0.3079 1.0000
11.500 1.2874 0.03746 0.03082 0.0123 0.2976 1.0000
11.750 1.2349 0.04052 0.03417 0.0215 0.2929 1.0000
12.000 1.2865 0.03819 0.03178 0.0203 0.2820 1.0000
12.250 1.2380 0.04087 0.03464 0.0288 0.2780 1.0000
12.500 1.1169 0.05104 0.04490 0.0352 0.2768 1.0000
12.750 1.2395 0.04174 0.03562 0.0347 0.2619 1.0000
13.000 1.2629 0.04085 0.03471 0.0360 0.2514 1.0000
13.250 1.2850 0.04009 0.03387 0.0373 0.2400 1.0000
13.500 1.2469 0.04394 0.03795 0.0402 0.2348 1.0000
13.750 1.0915 0.06326 0.05743 0.0369 0.2369 1.0000
14.000 0.9902 0.08115 0.07519 0.0306 0.2273 1.0000
14.250 1.2364 0.04935 0.04346 0.0429 0.2070 1.0000
14.500 1.2415 0.05059 0.04468 0.0436 0.1966 1.0000
14.750 1.2483 0.05171 0.04571 0.0442 0.1853 1.0000
15.000 1.2175 0.05728 0.05149 0.0432 0.1800 1.0000
15.250 1.2200 0.05911 0.05325 0.0434 0.1699 1.0000
15.500 1.2284 0.06031 0.05433 0.0439 0.1590 1.0000
15.750 1.1963 0.06674 0.06101 0.0419 0.1550 1.0000
16.000 1.2039 0.06814 0.06229 0.0422 0.1450 1.0000
16.250 1.1756 0.07465 0.06901 0.0399 0.1408 1.0000
16.500 1.1826 0.07625 0.07052 0.0400 0.1316 1.0000
16.750 1.1551 0.08317 0.07764 0.0372 0.1280 1.0000
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