E. Bambino (ebambino7-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E. Bambino (ebambino7-il) Reynolds number: 50,000 Max Cl/Cd: 27.95 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ebambino7-il-50000-n5.txt Download as CSV file: xf-ebambino7-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E. Bambino
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
------ -------- --------- --------- -------- -------- --------
-6.500 -0.5579 0.10260 0.09674 0.0133 1.0000 0.0791
-6.250 -0.5559 0.09919 0.09338 0.0089 1.0000 0.0817
-6.000 -0.5534 0.09682 0.09097 0.0008 1.0000 0.0838
-5.750 -0.5447 0.09183 0.08603 -0.0005 1.0000 0.0849
-5.500 -0.5342 0.08678 0.08104 0.0009 1.0000 0.0873
-5.250 -0.5237 0.08272 0.07697 -0.0004 1.0000 0.0904
-5.000 -0.4433 0.06415 0.05891 -0.0079 1.0000 0.1021
-4.750 -0.4365 0.05988 0.05457 -0.0091 1.0000 0.1078
-4.500 -0.4304 0.05526 0.04992 -0.0110 1.0000 0.1152
-4.250 -0.4219 0.05107 0.04561 -0.0130 1.0000 0.1274
-4.000 -0.4121 0.04667 0.04121 -0.0129 1.0000 0.1422
-3.750 -0.4017 0.04249 0.03708 -0.0120 1.0000 0.1600
-3.500 -0.3922 0.03858 0.03320 -0.0112 1.0000 0.1905
-3.250 -0.3649 0.05196 0.04449 -0.0154 1.0000 0.0574
-3.000 -0.3406 0.04723 0.03958 -0.0153 1.0000 0.0450
-2.750 -0.3192 0.04342 0.03567 -0.0152 1.0000 0.0420
-2.500 -0.2947 0.04005 0.03201 -0.0152 1.0000 0.0395
-2.250 -0.2668 0.03694 0.02842 -0.0147 1.0000 0.0362
-2.000 -0.2391 0.03433 0.02531 -0.0141 1.0000 0.0340
-1.750 -0.2128 0.03169 0.02237 -0.0136 1.0000 0.0330
-1.500 -0.1856 0.02932 0.01965 -0.0129 1.0000 0.0322
-1.250 -0.1579 0.02717 0.01716 -0.0121 1.0000 0.0317
-1.000 -0.1303 0.02526 0.01495 -0.0112 1.0000 0.0318
-0.750 -0.1026 0.02366 0.01305 -0.0102 1.0000 0.0338
-0.500 -0.0745 0.02223 0.01146 -0.0095 1.0000 0.0376
-0.250 -0.0484 0.02106 0.01010 -0.0085 1.0000 0.0409
0.000 -0.0246 0.02006 0.00891 -0.0072 1.0000 0.0455
0.250 -0.0020 0.01918 0.00797 -0.0062 1.0000 0.0609
0.500 0.0226 0.01523 0.00720 -0.0048 1.0000 0.8797
1.000 0.1435 0.01524 0.00576 -0.0164 0.8957 1.0000
1.250 0.1732 0.01531 0.00541 -0.0161 0.8331 1.0000
1.500 0.1966 0.01546 0.00508 -0.0140 0.7571 1.0000
1.750 0.2168 0.01571 0.00482 -0.0115 0.6898 1.0000
2.000 0.2389 0.01596 0.00468 -0.0099 0.6415 1.0000
2.250 0.2627 0.01617 0.00466 -0.0089 0.6052 1.0000
2.500 0.2861 0.01643 0.00466 -0.0078 0.5357 1.0000
2.750 0.3036 0.01770 0.00454 -0.0060 0.3122 1.0000
3.000 0.3286 0.01811 0.00480 -0.0057 0.2551 1.0000
3.250 0.3523 0.01900 0.00512 -0.0056 0.1771 1.0000
3.500 0.3771 0.01958 0.00553 -0.0054 0.1583 1.0000
3.750 0.4023 0.02002 0.00598 -0.0052 0.1337 1.0000
4.000 0.4278 0.02040 0.00648 -0.0049 0.1129 1.0000
4.250 0.4528 0.02089 0.00697 -0.0046 0.1021 1.0000
4.500 0.4780 0.02140 0.00750 -0.0044 0.0978 1.0000
4.750 0.5033 0.02192 0.00811 -0.0042 0.0952 1.0000
5.000 0.5285 0.02244 0.00884 -0.0040 0.0935 1.0000
5.250 0.5536 0.02295 0.00951 -0.0037 0.0924 1.0000
5.500 0.5775 0.02360 0.00995 -0.0038 0.0784 1.0000
5.750 0.6006 0.02449 0.01079 -0.0038 0.0676 1.0000
6.000 0.6239 0.02532 0.01178 -0.0037 0.0598 1.0000
6.250 0.6489 0.02566 0.01226 -0.0035 0.0546 1.0000
6.500 0.6737 0.02608 0.01274 -0.0035 0.0441 1.0000
6.750 0.6995 0.02630 0.01308 -0.0032 0.0399 1.0000
7.000 0.7261 0.02641 0.01349 -0.0028 0.0352 1.0000
7.250 0.7499 0.02736 0.01427 -0.0024 0.0216 1.0000
7.500 0.7755 0.02780 0.01518 -0.0020 0.0207 1.0000
7.750 0.8000 0.02862 0.01634 -0.0014 0.0202 1.0000
8.000 0.8238 0.02967 0.01770 -0.0009 0.0199 1.0000
8.250 0.8468 0.03097 0.01931 -0.0002 0.0196 1.0000
8.500 0.8681 0.03267 0.02154 0.0005 0.0192 1.0000
8.750 0.8877 0.03471 0.02403 0.0012 0.0186 1.0000
9.000 0.9055 0.03696 0.02676 0.0020 0.0182 1.0000
9.250 0.9218 0.03938 0.02964 0.0029 0.0181 1.0000
9.500 0.9363 0.04200 0.03275 0.0038 0.0183 1.0000
9.750 0.9481 0.04500 0.03624 0.0047 0.0185 1.0000
10.000 0.9564 0.04844 0.04017 0.0055 0.0187 1.0000
10.250 0.9601 0.05233 0.04453 0.0062 0.0189 1.0000
10.500 0.9584 0.05659 0.04921 0.0065 0.0191 1.0000
10.750 0.9507 0.06116 0.05413 0.0063 0.0192 1.0000
11.000 0.9366 0.06586 0.05907 0.0053 0.0193 1.0000
11.250 0.9211 0.07169 0.06509 0.0019 0.0193 1.0000
11.500 0.9054 0.07888 0.07244 -0.0036 0.0193 1.0000
11.750 0.8907 0.08717 0.08083 -0.0098 0.0193 1.0000
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Polar data table (+)
Polar graphs
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