EPPLER 333 AIRFOIL (e333-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 333 AIRFOIL (e333-il) Reynolds number: 50,000 Max Cl/Cd: 27.79 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e333-il-50000-n5.txt Download as CSV file: xf-e333-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 333 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3561 0.09963 0.09334 -0.0218 1.0000 0.1063
-8.250 -0.3721 0.09717 0.09104 -0.0262 1.0000 0.1106
-8.000 -0.4023 0.09564 0.08962 -0.0297 1.0000 0.1117
-7.750 -0.3812 0.09020 0.08427 -0.0278 1.0000 0.1137
-7.500 -0.3737 0.08670 0.08085 -0.0270 1.0000 0.1159
-7.250 -0.3730 0.08367 0.07791 -0.0269 1.0000 0.1182
-7.000 -0.3764 0.08074 0.07506 -0.0270 1.0000 0.1209
-6.250 -0.3855 0.06821 0.06219 -0.0277 1.0000 0.0527
-6.000 -0.3885 0.06573 0.05984 -0.0251 1.0000 0.0508
-5.750 -0.3623 0.06100 0.05492 -0.0292 0.9758 0.0476
-5.500 -0.3341 0.05612 0.04920 -0.0324 0.9481 0.0419
-5.250 -0.3054 0.05213 0.04486 -0.0348 0.9263 0.0419
-5.000 -0.2751 0.04839 0.04076 -0.0369 0.9065 0.0417
-4.750 -0.2443 0.04507 0.03701 -0.0384 0.8875 0.0417
-4.500 -0.2164 0.04205 0.03355 -0.0389 0.8671 0.0417
-4.250 -0.1886 0.03926 0.03032 -0.0391 0.8479 0.0415
-4.000 -0.1611 0.03677 0.02739 -0.0388 0.8295 0.0413
-3.750 -0.1336 0.03458 0.02473 -0.0382 0.8120 0.0413
-3.500 -0.1065 0.03270 0.02238 -0.0373 0.7943 0.0416
-3.250 -0.0795 0.03079 0.02018 -0.0367 0.7776 0.0434
-3.000 -0.0521 0.02944 0.01861 -0.0362 0.7613 0.0472
-2.750 -0.0217 0.02816 0.01699 -0.0357 0.7459 0.0506
-2.500 0.0134 0.02690 0.01536 -0.0357 0.7314 0.0539
-2.250 0.0471 0.02575 0.01409 -0.0362 0.7173 0.0629
-2.000 0.0760 0.02481 0.01295 -0.0356 0.7043 0.0730
-1.750 0.2446 0.02041 0.01112 -0.0576 0.6868 1.0000
-1.250 0.2894 0.02058 0.01052 -0.0556 0.6613 1.0000
-1.000 0.3117 0.02070 0.01033 -0.0547 0.6493 1.0000
-0.750 0.3342 0.02083 0.01018 -0.0538 0.6382 1.0000
-0.250 0.3793 0.02116 0.01004 -0.0520 0.6175 1.0000
0.000 0.4016 0.02135 0.01003 -0.0511 0.6077 1.0000
0.250 0.4245 0.02154 0.01001 -0.0502 0.5989 1.0000
0.500 0.4469 0.02181 0.01015 -0.0495 0.5891 1.0000
0.750 0.4699 0.02203 0.01019 -0.0486 0.5815 1.0000
1.000 0.4918 0.02234 0.01041 -0.0478 0.5722 1.0000
1.250 0.5142 0.02262 0.01056 -0.0469 0.5645 1.0000
1.500 0.5360 0.02295 0.01081 -0.0460 0.5564 1.0000
1.750 0.5580 0.02328 0.01104 -0.0451 0.5491 1.0000
2.000 0.5794 0.02364 0.01135 -0.0441 0.5413 1.0000
2.250 0.6011 0.02400 0.01164 -0.0432 0.5345 1.0000
2.500 0.6218 0.02443 0.01206 -0.0422 0.5270 1.0000
2.750 0.6438 0.02477 0.01231 -0.0411 0.5210 1.0000
3.000 0.6631 0.02531 0.01290 -0.0401 0.5132 1.0000
3.250 0.6853 0.02564 0.01315 -0.0390 0.5077 1.0000
3.500 0.7035 0.02628 0.01387 -0.0378 0.5002 1.0000
3.750 0.7246 0.02667 0.01425 -0.0367 0.4942 1.0000
4.000 0.7431 0.02729 0.01492 -0.0355 0.4877 1.0000
4.250 0.7622 0.02784 0.01551 -0.0342 0.4813 1.0000
4.500 0.7834 0.02824 0.01588 -0.0331 0.4761 1.0000
4.750 0.7984 0.02908 0.01689 -0.0315 0.4686 1.0000
5.000 0.8195 0.02949 0.01728 -0.0304 0.4635 1.0000
5.250 0.8338 0.03037 0.01829 -0.0287 0.4566 1.0000
5.500 0.8520 0.03095 0.01893 -0.0273 0.4506 1.0000
5.750 0.8708 0.03153 0.01958 -0.0260 0.4453 1.0000
6.000 0.8825 0.03253 0.02074 -0.0240 0.4380 1.0000
6.250 0.9047 0.03285 0.02107 -0.0229 0.4332 1.0000
6.500 0.9120 0.03415 0.02256 -0.0207 0.4258 1.0000
6.750 0.9305 0.03468 0.02317 -0.0192 0.4200 1.0000
7.000 0.9423 0.03567 0.02430 -0.0173 0.4137 1.0000
7.250 0.9534 0.03666 0.02541 -0.0153 0.4070 1.0000
7.500 0.9775 0.03685 0.02563 -0.0143 0.4021 1.0000
7.750 0.9739 0.03876 0.02777 -0.0113 0.3938 1.0000
8.000 1.0001 0.03878 0.02786 -0.0104 0.3887 1.0000
8.250 0.9916 0.04103 0.03032 -0.0072 0.3803 1.0000
8.500 1.0164 0.04109 0.03046 -0.0062 0.3747 1.0000
8.750 1.0045 0.04360 0.03315 -0.0030 0.3664 1.0000
9.000 1.0280 0.04371 0.03336 -0.0020 0.3605 1.0000
9.250 1.0070 0.04687 0.03668 0.0013 0.3519 1.0000
9.500 1.0336 0.04665 0.03659 0.0023 0.3459 1.0000
9.750 0.9808 0.05221 0.04218 0.0063 0.3363 1.0000
10.000 1.0221 0.05066 0.04079 0.0071 0.3311 1.0000
10.250 0.9552 0.05925 0.04935 0.0076 0.3190 1.0000
10.500 0.9787 0.05898 0.04921 0.0089 0.3137 1.0000
10.750 0.9537 0.06459 0.05486 0.0081 0.3028 1.0000
11.250 0.9500 0.07059 0.06103 0.0080 0.2861 1.0000
11.750 0.9053 0.08313 0.07361 0.0045 0.2633 1.0000
12.000 0.9382 0.08100 0.07168 0.0066 0.2596 1.0000
12.250 0.9115 0.08828 0.07896 0.0042 0.2479 1.0000
12.750 0.9205 0.09303 0.08396 0.0040 0.2329 1.0000
13.250 0.9318 0.09734 0.08849 0.0038 0.2182 1.0000
13.500 0.9032 0.10579 0.09693 0.0004 0.2072 1.0000
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Polar data table (+)
Polar graphs
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