EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 337 AIRFOIL (e337-il) Reynolds number: 500,000 Max Cl/Cd: 84.14 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e337-il-500000-n5.txt Download as CSV file: xf-e337-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3998 0.11123 0.10893 -0.0154 1.0000 0.0091
-10.750 -0.3936 0.10941 0.10714 -0.0149 1.0000 0.0095
-10.250 -0.3942 0.10057 0.09835 -0.0188 1.0000 0.0094
-9.500 -0.3477 0.08443 0.08175 -0.0384 0.8131 0.0084
-9.250 -0.3592 0.07884 0.07602 -0.0414 0.7742 0.0087
-9.000 -0.3652 0.07531 0.07238 -0.0436 0.7425 0.0082
-8.750 -0.3820 0.07028 0.06724 -0.0463 0.7220 0.0083
-8.500 -0.3980 0.06631 0.06317 -0.0461 0.7044 0.0084
-8.250 -0.4146 0.06297 0.05971 -0.0439 0.6895 0.0079
-7.750 -0.4315 0.05532 0.05175 -0.0401 0.6628 0.0077
-7.500 -0.4355 0.05111 0.04733 -0.0377 0.6518 0.0075
-7.250 -0.4536 0.04196 0.03774 -0.0325 0.6458 0.0069
-7.000 -0.4509 0.03767 0.03315 -0.0293 0.6352 0.0069
-6.750 -0.4284 0.03915 0.03462 -0.0295 0.6202 0.0074
-6.250 -0.4293 0.02487 0.01898 -0.0190 0.6063 0.0069
-5.750 -0.3910 0.02116 0.01454 -0.0156 0.5838 0.0067
-5.500 -0.3693 0.01971 0.01281 -0.0144 0.5732 0.0067
-5.250 -0.3460 0.01844 0.01127 -0.0134 0.5626 0.0067
-5.000 -0.3214 0.01732 0.00992 -0.0126 0.5531 0.0067
-4.750 -0.2964 0.01641 0.00881 -0.0119 0.5439 0.0067
-4.500 -0.2712 0.01567 0.00792 -0.0113 0.5345 0.0067
-4.250 -0.2462 0.01500 0.00712 -0.0106 0.5252 0.0067
-4.000 -0.2216 0.01441 0.00643 -0.0099 0.5159 0.0068
-3.750 -0.1978 0.01378 0.00572 -0.0090 0.5076 0.0069
-3.500 -0.1740 0.01330 0.00517 -0.0081 0.4997 0.0071
-3.250 -0.1497 0.01292 0.00473 -0.0074 0.4924 0.0073
-3.000 -0.1253 0.01261 0.00435 -0.0066 0.4845 0.0075
-2.750 -0.1006 0.01235 0.00403 -0.0059 0.4770 0.0078
-2.500 -0.0759 0.01210 0.00372 -0.0051 0.4694 0.0083
-2.250 -0.0509 0.01190 0.00346 -0.0045 0.4629 0.0088
-2.000 -0.0260 0.01168 0.00320 -0.0038 0.4564 0.0101
-1.750 -0.0010 0.01153 0.00299 -0.0032 0.4502 0.0120
-1.500 0.0241 0.01133 0.00281 -0.0025 0.4443 0.0195
-1.250 0.0486 0.01115 0.00268 -0.0019 0.4377 0.0388
-1.000 0.0722 0.01088 0.00258 -0.0011 0.4323 0.0872
-0.750 0.0909 0.01021 0.00244 0.0005 0.4274 0.2442
-0.500 0.0764 0.00810 0.00263 0.0093 0.4242 0.8455
0.000 0.1243 0.00862 0.00303 0.0119 0.4145 0.8960
0.250 0.1511 0.00896 0.00331 0.0128 0.4090 0.9085
0.500 0.1742 0.00922 0.00349 0.0142 0.4044 0.9189
0.750 0.2152 0.00966 0.00387 0.0121 0.3996 0.9249
1.000 0.2440 0.00981 0.00395 0.0120 0.3949 0.9291
1.250 0.2643 0.00980 0.00388 0.0136 0.3907 0.9319
1.500 0.2859 0.00980 0.00382 0.0148 0.3867 0.9341
1.750 0.3143 0.00982 0.00380 0.0147 0.3826 0.9347
2.000 0.3425 0.00987 0.00379 0.0145 0.3785 0.9355
2.250 0.3700 0.00992 0.00379 0.0145 0.3744 0.9363
2.500 0.3975 0.00997 0.00381 0.0145 0.3708 0.9371
2.750 0.4251 0.01002 0.00383 0.0145 0.3669 0.9381
3.000 0.4518 0.01007 0.00385 0.0146 0.3631 0.9390
3.250 0.4776 0.01013 0.00387 0.0149 0.3591 0.9400
3.500 0.5033 0.01018 0.00390 0.0152 0.3558 0.9411
3.750 0.5290 0.01023 0.00394 0.0156 0.3523 0.9425
4.000 0.5537 0.01028 0.00398 0.0161 0.3486 0.9438
4.250 0.5775 0.01034 0.00402 0.0168 0.3449 0.9451
4.500 0.6006 0.01040 0.00406 0.0176 0.3417 0.9465
4.750 0.6242 0.01043 0.00411 0.0183 0.3384 0.9478
5.000 0.6498 0.01049 0.00418 0.0186 0.3346 0.9488
5.250 0.6769 0.01059 0.00427 0.0185 0.3309 0.9496
5.500 0.7032 0.01071 0.00437 0.0186 0.3274 0.9503
5.750 0.7303 0.01078 0.00447 0.0186 0.3238 0.9510
6.000 0.7568 0.01087 0.00459 0.0186 0.3200 0.9518
6.250 0.7827 0.01098 0.00471 0.0188 0.3159 0.9527
6.500 0.8080 0.01111 0.00484 0.0190 0.3119 0.9536
6.750 0.8340 0.01120 0.00497 0.0191 0.3071 0.9546
7.000 0.8589 0.01132 0.00510 0.0194 0.3018 0.9557
7.250 0.8829 0.01147 0.00525 0.0199 0.2978 0.9570
7.500 0.9079 0.01157 0.00542 0.0202 0.2935 0.9582
7.750 0.9316 0.01169 0.00557 0.0207 0.2890 0.9598
8.000 0.9537 0.01185 0.00574 0.0215 0.2842 0.9615
8.250 0.9782 0.01198 0.00592 0.0219 0.2780 0.9626
8.500 1.0033 0.01218 0.00613 0.0220 0.2709 0.9635
8.750 1.0289 0.01236 0.00636 0.0220 0.2648 0.9645
9.000 1.0534 0.01259 0.00661 0.0222 0.2569 0.9656
9.250 1.0778 0.01281 0.00687 0.0224 0.2494 0.9669
9.500 1.1006 0.01310 0.00716 0.0228 0.2410 0.9684
9.750 1.1237 0.01336 0.00746 0.0232 0.2319 0.9701
10.000 1.1445 0.01369 0.00780 0.0239 0.2220 0.9721
10.250 1.1630 0.01405 0.00816 0.0250 0.2121 0.9746
10.750 1.2082 0.01505 0.00915 0.0252 0.1868 0.9776
11.000 1.2288 0.01563 0.00973 0.0255 0.1740 0.9799
11.250 1.2462 0.01628 0.01036 0.0263 0.1609 0.9829
11.500 1.2624 0.01700 0.01108 0.0271 0.1480 0.9860
11.750 1.2804 0.01794 0.01200 0.0270 0.1337 0.9883
12.000 1.2966 0.01897 0.01302 0.0271 0.1206 0.9912
12.250 1.3108 0.02006 0.01412 0.0272 0.1106 0.9952
12.500 1.3179 0.02129 0.01537 0.0283 0.1017 1.0000
13.000 1.3076 0.02413 0.01825 0.0339 0.0890 1.0000
13.250 1.3048 0.02613 0.02028 0.0351 0.0820 1.0000
13.500 1.3006 0.02852 0.02270 0.0359 0.0757 1.0000
13.750 1.3003 0.03076 0.02501 0.0363 0.0711 1.0000
14.000 1.2967 0.03344 0.02774 0.0364 0.0667 1.0000
14.250 1.2915 0.03638 0.03074 0.0364 0.0621 1.0000
14.500 1.2853 0.03950 0.03391 0.0363 0.0580 1.0000
14.750 1.2771 0.04291 0.03738 0.0360 0.0550 1.0000
15.000 1.2713 0.04612 0.04066 0.0356 0.0518 1.0000
15.250 1.2621 0.04976 0.04436 0.0351 0.0487 1.0000
15.500 1.2534 0.05341 0.04808 0.0344 0.0466 1.0000
15.750 1.2468 0.05699 0.05173 0.0337 0.0440 1.0000
16.000 1.2395 0.06071 0.05553 0.0328 0.0417 1.0000
16.250 1.2308 0.06471 0.05958 0.0318 0.0395 1.0000
16.500 1.2232 0.06869 0.06363 0.0307 0.0372 1.0000
16.750 1.2170 0.07252 0.06754 0.0295 0.0350 1.0000
17.000 1.2095 0.07663 0.07172 0.0282 0.0332 1.0000
17.250 1.2008 0.08099 0.07613 0.0268 0.0311 1.0000
17.500 1.1964 0.08477 0.07999 0.0255 0.0296 1.0000
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Polar data table (+)
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