EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 50,000 Max Cl/Cd: 26.48 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2510-il-50000.txt Download as CSV file: xf-eh2510-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.5/10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4987 0.10797 0.10179 0.0051 1.0000 0.2200
-8.500 -0.4894 0.10390 0.09777 0.0056 1.0000 0.2340
-8.250 -0.4807 0.09998 0.09387 0.0061 1.0000 0.2479
-8.000 -0.4742 0.09625 0.09019 0.0064 1.0000 0.2618
-7.750 -0.4726 0.09293 0.08695 0.0064 1.0000 0.2764
-7.500 -0.4780 0.09005 0.08418 0.0062 1.0000 0.2919
-7.250 -0.4563 0.08566 0.07981 0.0084 1.0000 0.3138
-7.000 -0.4689 0.08345 0.07774 0.0089 1.0000 0.3352
-6.750 -0.4629 0.08040 0.07476 0.0111 1.0000 0.3643
-6.500 -0.4408 0.07702 0.07139 0.0149 1.0000 0.4066
-6.250 -0.3967 0.07368 0.06796 0.0214 1.0000 0.4899
-6.000 -0.3567 0.07056 0.06478 0.0266 1.0000 0.5784
-5.750 -0.3001 0.06642 0.06055 0.0290 1.0000 0.6785
-5.000 -0.3336 0.04537 0.04071 0.0172 1.0000 0.5232
-4.750 -0.4156 0.04487 0.03782 -0.0132 1.0000 0.1721
-4.500 -0.4024 0.04154 0.03408 -0.0117 1.0000 0.1547
-4.250 -0.3929 0.03904 0.03113 -0.0093 1.0000 0.1439
-4.000 -0.3868 0.03695 0.02877 -0.0066 1.0000 0.1389
-3.750 -0.3792 0.03555 0.02663 -0.0037 1.0000 0.1333
-3.500 -0.3696 0.03381 0.02468 -0.0018 1.0000 0.1327
-3.250 -0.3576 0.03241 0.02288 0.0000 1.0000 0.1333
-3.000 -0.3450 0.03091 0.02147 0.0010 1.0000 0.1393
-2.750 -0.2988 0.02901 0.01905 -0.0027 0.9880 0.1495
-2.500 -0.2386 0.02694 0.01678 -0.0085 0.9716 0.1749
-2.250 -0.0697 0.02025 0.01354 -0.0256 0.9898 1.0000
-2.000 0.0118 0.02045 0.01266 -0.0362 0.9663 1.0000
-1.750 0.0908 0.02039 0.01203 -0.0465 0.9442 1.0000
-1.500 0.1591 0.02026 0.01148 -0.0545 0.9215 1.0000
-1.250 0.2106 0.02023 0.01115 -0.0591 0.8983 1.0000
-1.000 0.2430 0.02045 0.01114 -0.0601 0.8746 1.0000
-0.750 0.2710 0.02069 0.01117 -0.0600 0.8542 1.0000
-0.500 0.2909 0.02113 0.01146 -0.0588 0.8335 1.0000
-0.250 0.3110 0.02155 0.01174 -0.0574 0.8152 1.0000
0.000 0.3311 0.02199 0.01205 -0.0560 0.7985 1.0000
0.250 0.3511 0.02246 0.01239 -0.0545 0.7828 1.0000
0.500 0.3698 0.02298 0.01281 -0.0530 0.7675 1.0000
0.750 0.3883 0.02354 0.01329 -0.0514 0.7530 1.0000
1.000 0.4069 0.02411 0.01377 -0.0498 0.7393 1.0000
1.250 0.4250 0.02476 0.01437 -0.0484 0.7256 1.0000
1.500 0.4429 0.02547 0.01503 -0.0470 0.7122 1.0000
1.750 0.4605 0.02622 0.01575 -0.0456 0.6991 1.0000
2.000 0.4780 0.02704 0.01655 -0.0443 0.6866 1.0000
2.250 0.4955 0.02787 0.01736 -0.0429 0.6745 1.0000
2.500 0.5134 0.02868 0.01817 -0.0415 0.6632 1.0000
2.750 0.5336 0.02929 0.01874 -0.0398 0.6531 1.0000
3.000 0.5492 0.03041 0.01989 -0.0387 0.6409 1.0000
3.250 0.5643 0.03162 0.02114 -0.0376 0.6294 1.0000
3.500 0.5804 0.03275 0.02232 -0.0363 0.6187 1.0000
3.750 0.6025 0.03330 0.02285 -0.0346 0.6096 1.0000
4.000 0.6144 0.03490 0.02453 -0.0337 0.5980 1.0000
4.250 0.6259 0.03655 0.02624 -0.0326 0.5870 1.0000
4.500 0.6419 0.03781 0.02755 -0.0314 0.5774 1.0000
4.750 0.6607 0.03885 0.02867 -0.0300 0.5679 1.0000
5.000 0.6658 0.04117 0.03108 -0.0292 0.5569 1.0000
5.250 0.6753 0.04316 0.03314 -0.0282 0.5472 1.0000
5.500 0.7007 0.04372 0.03377 -0.0267 0.5385 1.0000
5.750 0.6935 0.04727 0.03739 -0.0263 0.5278 1.0000
6.000 0.6967 0.04994 0.04012 -0.0256 0.5187 1.0000
6.250 0.7278 0.05017 0.04051 -0.0241 0.5097 1.0000
6.500 0.6952 0.05595 0.04621 -0.0245 0.5012 1.0000
6.750 0.7102 0.05777 0.04817 -0.0236 0.4926 1.0000
7.000 0.6854 0.06231 0.05265 -0.0230 0.4864 1.0000
7.250 0.6980 0.06449 0.05491 -0.0223 0.4783 1.0000
7.500 0.6769 0.06884 0.05922 -0.0221 0.4741 1.0000
7.750 0.6970 0.07071 0.06122 -0.0216 0.4648 1.0000
8.000 0.6795 0.07518 0.06566 -0.0220 0.4629 1.0000
8.250 0.6704 0.07921 0.06972 -0.0226 0.4614 1.0000
8.500 0.6663 0.08330 0.07385 -0.0235 0.4628 1.0000
8.750 0.6731 0.08739 0.07803 -0.0247 0.4657 1.0000
10.000 1.0929 0.04128 0.03431 0.0093 0.2696 1.0000
10.250 1.0183 0.05780 0.05109 0.0064 0.2964 1.0000
10.500 1.0006 0.06047 0.05383 0.0084 0.2808 1.0000
10.750 1.0509 0.04401 0.03585 0.0215 0.1475 1.0000
11.000 1.0403 0.04723 0.03887 0.0228 0.1301 1.0000
11.250 1.0386 0.05038 0.04191 0.0241 0.1160 1.0000
11.500 1.0416 0.05337 0.04480 0.0253 0.1041 1.0000
11.750 1.0524 0.05594 0.04722 0.0266 0.0938 1.0000
12.000 1.0487 0.05974 0.05138 0.0267 0.0898 1.0000
12.250 1.0539 0.06322 0.05502 0.0273 0.0852 1.0000
12.500 1.0660 0.06700 0.05885 0.0283 0.0813 1.0000
12.750 1.0500 0.07196 0.06411 0.0269 0.0808 1.0000
13.000 1.0355 0.07724 0.06963 0.0251 0.0809 1.0000
13.250 1.0169 0.08328 0.07589 0.0225 0.0812 1.0000
13.500 0.9978 0.08982 0.08259 0.0193 0.0816 1.0000
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Polar data table (+)
Polar graphs
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