EPPLER 337 AIRFOIL (e337-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 337 AIRFOIL (e337-il) Reynolds number: 50,000 Max Cl/Cd: 25.75 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e337-il-50000-n5.txt Download as CSV file: xf-e337-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3837 0.11471 0.10812 -0.0156 1.0000 0.1058
-9.750 -0.4044 0.11225 0.10580 -0.0209 1.0000 0.1102
-9.500 -0.4215 0.10897 0.10263 -0.0259 1.0000 0.1108
-9.250 -0.3967 0.10391 0.09762 -0.0227 1.0000 0.1126
-9.000 -0.3841 0.10027 0.09402 -0.0218 1.0000 0.1154
-8.750 -0.3915 0.09177 0.08547 -0.0297 1.0000 0.0647
-8.500 -0.3914 0.08768 0.08145 -0.0306 1.0000 0.0607
-8.000 -0.4136 0.07957 0.07340 -0.0319 1.0000 0.0516
-7.500 -0.4461 0.07209 0.06567 -0.0293 1.0000 0.0445
-7.250 -0.4455 0.06912 0.06274 -0.0276 1.0000 0.0441
-7.000 -0.4506 0.06628 0.05985 -0.0251 1.0000 0.0441
-6.750 -0.4525 0.06374 0.05733 -0.0226 1.0000 0.0436
-6.500 -0.4579 0.06154 0.05513 -0.0194 1.0000 0.0433
-6.250 -0.4388 0.05757 0.05091 -0.0213 0.9727 0.0430
-6.000 -0.4144 0.05351 0.04652 -0.0233 0.9420 0.0424
-5.750 -0.3866 0.04949 0.04207 -0.0252 0.9175 0.0417
-5.500 -0.3587 0.04596 0.03808 -0.0263 0.8935 0.0410
-5.250 -0.3306 0.04268 0.03428 -0.0269 0.8714 0.0405
-5.000 -0.3034 0.03978 0.03083 -0.0267 0.8500 0.0404
-4.750 -0.2772 0.03731 0.02785 -0.0260 0.8285 0.0406
-4.500 -0.2501 0.03520 0.02524 -0.0253 0.8088 0.0415
-4.250 -0.2219 0.03337 0.02282 -0.0243 0.7903 0.0440
-4.000 -0.1932 0.03164 0.02080 -0.0240 0.7726 0.0465
-3.750 -0.1619 0.03014 0.01905 -0.0239 0.7558 0.0491
-3.500 -0.1251 0.02871 0.01727 -0.0244 0.7395 0.0533
-3.250 -0.0851 0.02743 0.01582 -0.0258 0.7237 0.0612
-3.000 -0.0508 0.02636 0.01457 -0.0262 0.7087 0.0715
-2.750 -0.0239 0.02551 0.01359 -0.0257 0.6946 0.0861
-2.500 0.1965 0.02284 0.01325 -0.0536 0.6726 1.0000
-2.250 0.2178 0.02280 0.01286 -0.0527 0.6596 1.0000
-2.000 0.2394 0.02279 0.01256 -0.0520 0.6472 1.0000
-1.750 0.2612 0.02281 0.01230 -0.0512 0.6359 1.0000
-1.250 0.3050 0.02291 0.01190 -0.0496 0.6148 1.0000
-1.000 0.3271 0.02300 0.01177 -0.0488 0.6052 1.0000
-0.750 0.3493 0.02309 0.01168 -0.0481 0.5963 1.0000
-0.500 0.3714 0.02324 0.01167 -0.0473 0.5870 1.0000
-0.250 0.3935 0.02336 0.01160 -0.0465 0.5791 1.0000
0.000 0.4159 0.02357 0.01170 -0.0459 0.5704 1.0000
0.250 0.4385 0.02373 0.01170 -0.0451 0.5631 1.0000
0.500 0.4608 0.02398 0.01188 -0.0445 0.5550 1.0000
0.750 0.4832 0.02419 0.01196 -0.0437 0.5480 1.0000
1.000 0.5052 0.02448 0.01218 -0.0430 0.5408 1.0000
1.250 0.5272 0.02476 0.01239 -0.0422 0.5338 1.0000
1.500 0.5494 0.02502 0.01254 -0.0414 0.5280 1.0000
1.750 0.5705 0.02542 0.01296 -0.0407 0.5205 1.0000
2.000 0.5926 0.02569 0.01314 -0.0398 0.5151 1.0000
2.250 0.6133 0.02615 0.01363 -0.0390 0.5085 1.0000
2.500 0.6342 0.02656 0.01402 -0.0381 0.5023 1.0000
2.750 0.6564 0.02683 0.01420 -0.0371 0.4977 1.0000
3.000 0.6750 0.02750 0.01498 -0.0362 0.4905 1.0000
3.250 0.6957 0.02793 0.01541 -0.0352 0.4852 1.0000
3.500 0.7167 0.02834 0.01579 -0.0342 0.4804 1.0000
3.750 0.7340 0.02910 0.01667 -0.0331 0.4736 1.0000
4.000 0.7544 0.02954 0.01710 -0.0320 0.4687 1.0000
4.250 0.7737 0.03011 0.01773 -0.0308 0.4639 1.0000
4.500 0.7892 0.03097 0.01873 -0.0295 0.4574 1.0000
4.750 0.8092 0.03142 0.01919 -0.0283 0.4527 1.0000
5.000 0.8263 0.03215 0.01999 -0.0270 0.4476 1.0000
5.250 0.8394 0.03317 0.02118 -0.0254 0.4414 1.0000
5.500 0.8591 0.03362 0.02166 -0.0241 0.4368 1.0000
5.750 0.8731 0.03454 0.02268 -0.0225 0.4316 1.0000
6.000 0.8829 0.03572 0.02402 -0.0205 0.4254 1.0000
6.250 0.9024 0.03615 0.02451 -0.0192 0.4210 1.0000
6.500 0.9108 0.03739 0.02589 -0.0170 0.4152 1.0000
6.750 0.9171 0.03872 0.02737 -0.0147 0.4092 1.0000
7.000 0.9376 0.03902 0.02771 -0.0134 0.4050 1.0000
7.250 0.9337 0.04095 0.02983 -0.0102 0.3984 1.0000
7.500 0.9383 0.04224 0.03125 -0.0076 0.3926 1.0000
7.750 0.9626 0.04225 0.03130 -0.0065 0.3888 1.0000
8.000 0.9310 0.04569 0.03493 -0.0011 0.3808 1.0000
8.250 0.9408 0.04650 0.03581 0.0011 0.3758 1.0000
8.750 0.8855 0.05245 0.04186 0.0106 0.3620 1.0000
9.000 0.9224 0.05158 0.04112 0.0111 0.3586 1.0000
9.250 0.8223 0.06073 0.05012 0.0161 0.3457 1.0000
9.500 0.8545 0.05946 0.04895 0.0180 0.3431 1.0000
10.000 0.8245 0.06708 0.05661 0.0194 0.3266 1.0000
11.000 0.7696 0.08385 0.07353 0.0188 0.2915 1.0000
11.250 0.7813 0.08515 0.07492 0.0194 0.2859 1.0000
11.750 0.7818 0.09071 0.08062 0.0194 0.2716 1.0000
12.000 0.7715 0.09500 0.08495 0.0185 0.2631 1.0000
12.250 0.7840 0.09623 0.08629 0.0190 0.2573 1.0000
12.500 0.7737 0.10068 0.09078 0.0180 0.2488 1.0000
12.750 0.7869 0.10183 0.09208 0.0185 0.2432 1.0000
13.000 0.7762 0.10654 0.09682 0.0171 0.2349 1.0000
13.250 0.7904 0.10748 0.09789 0.0177 0.2292 1.0000
13.500 0.7787 0.11260 0.10305 0.0160 0.2212 1.0000
13.750 0.7918 0.11376 0.10433 0.0163 0.2155 1.0000
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