EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 337 AIRFOIL (e337-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.9 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e337-il-1000000-n5.txt Download as CSV file: xf-e337-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3577 0.10955 0.10713 -0.0270 0.7749 0.0043
-11.000 -0.3568 0.10603 0.10348 -0.0281 0.7422 0.0043
-10.750 -0.3635 0.09995 0.09735 -0.0303 0.7239 0.0045
-10.500 -0.2973 0.09112 0.08844 -0.0253 0.6395 0.0044
-10.250 -0.3083 0.08402 0.08134 -0.0279 0.6355 0.0048
-10.000 -0.3129 0.07867 0.07597 -0.0299 0.6278 0.0047
-9.750 -0.3186 0.07378 0.07108 -0.0321 0.6204 0.0049
-9.500 -0.3317 0.06699 0.06429 -0.0351 0.6152 0.0048
-9.250 -0.3342 0.06337 0.06064 -0.0373 0.6065 0.0049
-9.000 -0.3755 0.05327 0.05053 -0.0446 0.6083 0.0048
-8.750 -0.4005 0.04853 0.04573 -0.0449 0.6032 0.0048
-8.500 -0.4202 0.04502 0.04214 -0.0427 0.5962 0.0049
-8.250 -0.4727 0.05327 0.05008 -0.0405 0.6069 0.0047
-8.000 -0.4875 0.04784 0.04445 -0.0372 0.6004 0.0048
-7.750 -0.4879 0.04354 0.03995 -0.0343 0.5920 0.0047
-7.500 -0.4874 0.03910 0.03529 -0.0312 0.5837 0.0047
-7.250 -0.4919 0.03306 0.02888 -0.0267 0.5771 0.0046
-7.000 -0.5104 0.02278 0.01766 -0.0190 0.5743 0.0046
-6.750 -0.4892 0.02183 0.01650 -0.0178 0.5630 0.0047
-6.500 -0.4705 0.02020 0.01459 -0.0162 0.5534 0.0047
-6.250 -0.4524 0.01811 0.01212 -0.0144 0.5442 0.0048
-6.000 -0.4297 0.01706 0.01086 -0.0134 0.5352 0.0048
-5.750 -0.4062 0.01609 0.00970 -0.0125 0.5268 0.0047
-5.500 -0.3818 0.01534 0.00880 -0.0118 0.5178 0.0047
-5.250 -0.3571 0.01466 0.00798 -0.0111 0.5092 0.0047
-5.000 -0.3325 0.01395 0.00714 -0.0104 0.4995 0.0047
-4.750 -0.3077 0.01335 0.00643 -0.0097 0.4918 0.0047
-4.500 -0.2831 0.01282 0.00579 -0.0090 0.4841 0.0048
-4.250 -0.2585 0.01232 0.00522 -0.0082 0.4773 0.0048
-4.000 -0.2338 0.01194 0.00476 -0.0075 0.4695 0.0048
-3.750 -0.2094 0.01155 0.00430 -0.0068 0.4628 0.0048
-3.500 -0.1849 0.01120 0.00389 -0.0060 0.4550 0.0049
-3.250 -0.1600 0.01092 0.00355 -0.0053 0.4485 0.0050
-3.000 -0.1347 0.01068 0.00327 -0.0047 0.4425 0.0051
-2.750 -0.1093 0.01049 0.00303 -0.0042 0.4362 0.0052
-2.500 -0.0838 0.01031 0.00281 -0.0036 0.4306 0.0054
-2.250 -0.0580 0.01016 0.00263 -0.0031 0.4241 0.0055
-2.000 -0.0322 0.01004 0.00246 -0.0026 0.4184 0.0060
-1.750 -0.0060 0.00992 0.00231 -0.0022 0.4136 0.0063
-1.500 0.0199 0.00979 0.00216 -0.0017 0.4085 0.0080
-1.250 0.0458 0.00970 0.00205 -0.0013 0.4034 0.0118
-1.000 0.0717 0.00957 0.00196 -0.0009 0.3988 0.0236
-0.750 0.0976 0.00946 0.00189 -0.0004 0.3938 0.0384
-0.500 0.1224 0.00928 0.00183 0.0002 0.3890 0.0795
-0.250 0.1447 0.00888 0.00176 0.0011 0.3856 0.1893
0.250 0.1497 0.00656 0.00176 0.0115 0.3794 0.8758
0.500 0.1758 0.00669 0.00184 0.0121 0.3747 0.8887
0.750 0.2019 0.00688 0.00200 0.0127 0.3710 0.8996
1.000 0.2285 0.00700 0.00210 0.0132 0.3675 0.9059
1.250 0.2552 0.00718 0.00226 0.0137 0.3636 0.9122
1.500 0.2817 0.00730 0.00232 0.0141 0.3593 0.9159
1.750 0.3094 0.00734 0.00232 0.0141 0.3559 0.9169
2.000 0.3374 0.00737 0.00232 0.0140 0.3527 0.9176
2.250 0.3652 0.00742 0.00232 0.0139 0.3491 0.9182
2.500 0.3928 0.00747 0.00233 0.0139 0.3451 0.9190
2.750 0.4205 0.00753 0.00236 0.0139 0.3416 0.9197
3.000 0.4485 0.00757 0.00238 0.0138 0.3387 0.9203
3.250 0.4763 0.00762 0.00242 0.0137 0.3353 0.9208
3.500 0.5039 0.00769 0.00246 0.0137 0.3314 0.9214
3.750 0.5313 0.00777 0.00251 0.0137 0.3278 0.9220
4.000 0.5591 0.00783 0.00257 0.0136 0.3251 0.9226
4.250 0.5867 0.00790 0.00263 0.0135 0.3216 0.9234
4.500 0.6141 0.00797 0.00269 0.0135 0.3180 0.9242
4.750 0.6412 0.00807 0.00277 0.0135 0.3141 0.9249
5.000 0.6685 0.00815 0.00285 0.0135 0.3111 0.9255
5.250 0.6960 0.00822 0.00293 0.0134 0.3080 0.9262
5.500 0.7232 0.00831 0.00301 0.0133 0.3039 0.9269
5.750 0.7500 0.00843 0.00312 0.0134 0.2990 0.9276
6.000 0.7771 0.00852 0.00321 0.0133 0.2945 0.9283
6.250 0.8040 0.00862 0.00331 0.0133 0.2893 0.9290
6.500 0.8304 0.00875 0.00343 0.0133 0.2847 0.9298
6.750 0.8572 0.00886 0.00355 0.0133 0.2810 0.9305
7.000 0.8840 0.00897 0.00367 0.0133 0.2770 0.9312
7.250 0.9101 0.00911 0.00382 0.0134 0.2715 0.9319
7.500 0.9362 0.00926 0.00396 0.0134 0.2650 0.9327
7.750 0.9617 0.00944 0.00412 0.0136 0.2573 0.9335
8.000 0.9873 0.00960 0.00429 0.0137 0.2512 0.9343
8.250 1.0121 0.00979 0.00448 0.0140 0.2430 0.9352
8.500 1.0369 0.00998 0.00467 0.0142 0.2356 0.9360
8.750 1.0606 0.01023 0.00490 0.0147 0.2264 0.9370
9.000 1.0839 0.01049 0.00515 0.0152 0.2155 0.9380
9.250 1.1071 0.01075 0.00540 0.0156 0.2064 0.9390
9.500 1.1292 0.01106 0.00570 0.0163 0.1960 0.9402
9.750 1.1503 0.01142 0.00603 0.0171 0.1843 0.9415
10.000 1.1706 0.01181 0.00638 0.0180 0.1727 0.9429
10.250 1.1896 0.01225 0.00678 0.0190 0.1593 0.9444
10.500 1.2076 0.01271 0.00720 0.0203 0.1468 0.9461
10.750 1.2245 0.01320 0.00765 0.0216 0.1346 0.9477
11.250 1.2500 0.01426 0.00866 0.0258 0.1115 0.9530
11.500 1.2599 0.01476 0.00916 0.0285 0.1033 0.9565
11.750 1.2684 0.01535 0.00975 0.0312 0.0948 0.9605
12.000 1.2764 0.01604 0.01043 0.0337 0.0858 0.9651
12.250 1.2852 0.01687 0.01126 0.0356 0.0759 0.9712
12.500 1.3001 0.01769 0.01211 0.0362 0.0689 0.9766
12.750 1.3162 0.01885 0.01327 0.0358 0.0606 0.9822
13.000 1.3325 0.02022 0.01466 0.0347 0.0538 0.9878
13.500 1.3514 0.02334 0.01784 0.0344 0.0446 1.0000
13.750 1.3489 0.02547 0.02000 0.0354 0.0396 1.0000
14.000 1.3393 0.02849 0.02300 0.0360 0.0318 1.0000
14.250 1.3519 0.02963 0.02427 0.0361 0.0349 1.0000
14.500 1.3366 0.03350 0.02813 0.0362 0.0272 1.0000
14.750 1.3460 0.03504 0.02979 0.0361 0.0302 1.0000
15.000 1.3398 0.03818 0.03298 0.0360 0.0275 1.0000
15.250 1.3317 0.04159 0.03644 0.0356 0.0253 1.0000
15.500 1.3210 0.04530 0.04021 0.0352 0.0221 1.0000
16.000 1.3011 0.05286 0.04789 0.0340 0.0182 1.0000
16.250 1.2886 0.05712 0.05220 0.0331 0.0160 1.0000
16.500 1.2882 0.06004 0.05521 0.0324 0.0169 1.0000
16.750 1.2839 0.06347 0.05872 0.0316 0.0170 1.0000
17.000 1.2730 0.06779 0.06310 0.0304 0.0148 1.0000
17.250 1.2657 0.07174 0.06712 0.0292 0.0139 1.0000
17.500 1.2553 0.07616 0.07159 0.0279 0.0125 1.0000
17.750 1.2507 0.07990 0.07541 0.0267 0.0123 1.0000
18.000 1.2468 0.08357 0.07916 0.0254 0.0121 1.0000
18.250 1.2365 0.08819 0.08382 0.0238 0.0106 1.0000
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