EPPLER 336 AIRFOIL (e336-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 336 AIRFOIL (e336-il) Reynolds number: 500,000 Max Cl/Cd: 78.63 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e336-il-500000-n5.txt Download as CSV file: xf-e336-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 336 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3445 0.09883 0.09626 -0.0129 0.7771 0.0110
-10.250 -0.3458 0.09449 0.09183 -0.0145 0.7542 0.0110
-9.750 -0.4518 0.08754 0.08539 -0.0192 1.0000 0.0105
-7.500 -0.5202 0.04826 0.04434 -0.0209 0.6561 0.0082
-7.000 -0.5278 0.03637 0.03171 -0.0120 0.6370 0.0057
-6.750 -0.5208 0.03326 0.02830 -0.0089 0.6251 0.0056
-6.500 -0.5137 0.02949 0.02413 -0.0055 0.6145 0.0055
-6.250 -0.5018 0.02633 0.02055 -0.0026 0.6038 0.0053
-6.000 -0.4866 0.02327 0.01703 0.0000 0.5932 0.0052
-5.750 -0.4663 0.02119 0.01455 0.0017 0.5823 0.0051
-5.500 -0.4434 0.01937 0.01237 0.0029 0.5710 0.0051
-5.250 -0.4188 0.01802 0.01074 0.0037 0.5597 0.0051
-5.000 -0.3933 0.01689 0.00938 0.0044 0.5497 0.0051
-4.750 -0.3680 0.01600 0.00830 0.0051 0.5402 0.0052
-4.500 -0.3429 0.01525 0.00741 0.0058 0.5311 0.0052
-4.250 -0.3183 0.01467 0.00672 0.0065 0.5225 0.0052
-4.000 -0.2940 0.01411 0.00605 0.0073 0.5139 0.0054
-3.750 -0.2699 0.01364 0.00550 0.0082 0.5059 0.0055
-3.500 -0.2457 0.01325 0.00502 0.0090 0.4978 0.0057
-3.250 -0.2219 0.01283 0.00454 0.0099 0.4903 0.0059
-3.000 -0.1976 0.01251 0.00417 0.0107 0.4824 0.0063
-2.750 -0.1730 0.01226 0.00385 0.0114 0.4752 0.0069
-2.500 -0.1481 0.01204 0.00358 0.0121 0.4677 0.0077
-2.250 -0.1236 0.01183 0.00330 0.0128 0.4607 0.0089
-2.000 -0.0986 0.01163 0.00308 0.0135 0.4536 0.0115
-1.750 -0.0740 0.01145 0.00288 0.0142 0.4465 0.0182
-1.500 -0.0503 0.01117 0.00273 0.0150 0.4397 0.0477
-1.250 -0.0273 0.01087 0.00260 0.0159 0.4322 0.1003
-1.000 -0.0091 0.01022 0.00244 0.0176 0.4259 0.2427
-0.750 -0.0249 0.00795 0.00255 0.0267 0.4218 0.8357
-0.250 0.0201 0.00859 0.00308 0.0301 0.4091 0.8971
0.000 0.0545 0.00904 0.00345 0.0293 0.4009 0.9066
0.250 0.0786 0.00931 0.00364 0.0305 0.3935 0.9160
0.500 0.1274 0.00986 0.00408 0.0267 0.3834 0.9202
0.750 0.1603 0.01001 0.00415 0.0257 0.3759 0.9225
1.000 0.1854 0.01005 0.00411 0.0263 0.3696 0.9245
1.250 0.2052 0.01004 0.00404 0.0280 0.3649 0.9275
1.500 0.2211 0.00999 0.00395 0.0304 0.3603 0.9309
1.750 0.2499 0.01004 0.00393 0.0301 0.3555 0.9315
2.000 0.2787 0.01011 0.00393 0.0299 0.3515 0.9322
2.250 0.3073 0.01015 0.00395 0.0296 0.3482 0.9329
2.500 0.3350 0.01020 0.00396 0.0296 0.3450 0.9336
2.750 0.3628 0.01027 0.00399 0.0295 0.3418 0.9345
3.000 0.3898 0.01036 0.00403 0.0296 0.3385 0.9354
3.250 0.4163 0.01041 0.00406 0.0297 0.3361 0.9364
3.500 0.4421 0.01045 0.00410 0.0300 0.3337 0.9374
3.750 0.4677 0.01051 0.00415 0.0304 0.3311 0.9387
4.000 0.4915 0.01056 0.00419 0.0311 0.3285 0.9402
4.250 0.5135 0.01062 0.00423 0.0321 0.3256 0.9418
4.500 0.5336 0.01069 0.00427 0.0336 0.3231 0.9436
4.750 0.5530 0.01070 0.00430 0.0352 0.3211 0.9456
5.000 0.5810 0.01076 0.00439 0.0350 0.3184 0.9462
5.250 0.6083 0.01084 0.00448 0.0349 0.3156 0.9467
5.500 0.6352 0.01094 0.00459 0.0349 0.3124 0.9473
5.750 0.6615 0.01106 0.00471 0.0350 0.3092 0.9480
6.000 0.6877 0.01119 0.00484 0.0350 0.3060 0.9487
6.250 0.7147 0.01124 0.00496 0.0350 0.3030 0.9494
6.500 0.7410 0.01133 0.00508 0.0351 0.2996 0.9502
6.750 0.7666 0.01143 0.00521 0.0353 0.2956 0.9511
7.000 0.7914 0.01157 0.00536 0.0356 0.2921 0.9522
7.250 0.8173 0.01164 0.00549 0.0358 0.2881 0.9534
7.500 0.8420 0.01172 0.00562 0.0362 0.2834 0.9547
7.750 0.8651 0.01182 0.00575 0.0368 0.2776 0.9560
8.000 0.8883 0.01189 0.00587 0.0375 0.2711 0.9574
8.250 0.9096 0.01200 0.00599 0.0385 0.2643 0.9589
8.500 0.9326 0.01212 0.00615 0.0391 0.2564 0.9601
8.750 0.9579 0.01232 0.00636 0.0392 0.2481 0.9609
9.000 0.9830 0.01255 0.00660 0.0393 0.2392 0.9617
9.250 1.0073 0.01281 0.00689 0.0394 0.2304 0.9627
9.500 1.0303 0.01313 0.00721 0.0398 0.2207 0.9639
9.750 1.0530 0.01346 0.00755 0.0402 0.2095 0.9652
10.000 1.0749 0.01381 0.00792 0.0407 0.1985 0.9668
10.250 1.0944 0.01422 0.00832 0.0416 0.1860 0.9690
10.500 1.1111 0.01465 0.00875 0.0430 0.1742 0.9714
10.750 1.1280 0.01518 0.00926 0.0442 0.1601 0.9734
11.000 1.1486 0.01581 0.00988 0.0444 0.1464 0.9748
11.250 1.1675 0.01650 0.01056 0.0448 0.1332 0.9765
11.500 1.1834 0.01725 0.01130 0.0457 0.1206 0.9790
11.750 1.1962 0.01808 0.01212 0.0469 0.1087 0.9823
12.000 1.2099 0.01904 0.01309 0.0475 0.0977 0.9850
12.250 1.2264 0.02021 0.01427 0.0470 0.0871 0.9868
12.500 1.2399 0.02159 0.01567 0.0464 0.0783 0.9892
12.750 1.2510 0.02320 0.01732 0.0458 0.0699 0.9925
13.000 1.2615 0.02505 0.01923 0.0446 0.0634 0.9966
13.250 1.2698 0.02745 0.02167 0.0429 0.0568 1.0000
13.500 1.2569 0.02946 0.02375 0.0457 0.0536 1.0000
13.750 1.2479 0.03198 0.02630 0.0469 0.0502 1.0000
14.000 1.2421 0.03459 0.02898 0.0474 0.0474 1.0000
14.250 1.2339 0.03764 0.03209 0.0476 0.0437 1.0000
14.750 1.2184 0.04404 0.03863 0.0473 0.0392 1.0000
15.000 1.2083 0.04762 0.04226 0.0469 0.0362 1.0000
15.250 1.1987 0.05123 0.04594 0.0464 0.0348 1.0000
15.500 1.1902 0.05481 0.04960 0.0458 0.0334 1.0000
15.750 1.1819 0.05851 0.05337 0.0450 0.0313 1.0000
16.000 1.1742 0.06227 0.05721 0.0441 0.0299 1.0000
16.250 1.1630 0.06656 0.06154 0.0429 0.0278 1.0000
16.500 1.1573 0.07024 0.06531 0.0419 0.0269 1.0000
16.750 1.1502 0.07423 0.06937 0.0407 0.0253 1.0000
17.000 1.1409 0.07852 0.07372 0.0393 0.0235 1.0000
17.250 1.1339 0.08260 0.07787 0.0379 0.0225 1.0000
17.500 1.1288 0.08649 0.08185 0.0366 0.0217 1.0000
17.750 1.1228 0.09053 0.08596 0.0351 0.0204 1.0000
18.000 1.1149 0.09492 0.09040 0.0335 0.0192 1.0000
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Polar data table (+)
Polar graphs
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