E178 (8.69%) (e178-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: E178 (8.69%) (e178-il) Reynolds number: 50,000 Max Cl/Cd: 37.69 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e178-il-50000-n5.txt Download as CSV file: xf-e178-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: E178 (8.69%)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4465 0.10493 0.09849 -0.0107 1.0000 0.1057
-8.500 -0.4535 0.09670 0.09030 -0.0194 1.0000 0.0549
-8.250 -0.4497 0.09268 0.08635 -0.0211 1.0000 0.0546
-8.000 -0.4480 0.08865 0.08241 -0.0235 1.0000 0.0545
-7.750 -0.4451 0.08454 0.07836 -0.0261 1.0000 0.0542
-7.500 -0.4409 0.08013 0.07400 -0.0292 1.0000 0.0539
-7.250 -0.4356 0.07569 0.06959 -0.0321 1.0000 0.0533
-7.000 -0.4295 0.07122 0.06512 -0.0349 1.0000 0.0524
-6.750 -0.4228 0.06655 0.06044 -0.0377 1.0000 0.0512
-6.500 -0.4154 0.06179 0.05561 -0.0404 1.0000 0.0500
-6.250 -0.4071 0.05704 0.05073 -0.0427 1.0000 0.0490
-6.000 -0.3984 0.05245 0.04593 -0.0442 1.0000 0.0482
-5.750 -0.3900 0.04833 0.04155 -0.0448 1.0000 0.0476
-5.500 -0.3828 0.04482 0.03775 -0.0441 1.0000 0.0473
-5.250 -0.3762 0.04179 0.03439 -0.0428 1.0000 0.0472
-5.000 -0.3637 0.03878 0.03098 -0.0422 0.9971 0.0475
-4.750 -0.3279 0.03508 0.02661 -0.0454 0.9838 0.0495
-4.500 -0.2901 0.03218 0.02280 -0.0480 0.9718 0.0551
-4.250 -0.2539 0.02948 0.01967 -0.0503 0.9612 0.0577
-4.000 -0.2158 0.02735 0.01716 -0.0524 0.9516 0.0604
-3.750 -0.1778 0.02556 0.01500 -0.0541 0.9422 0.0642
-3.500 -0.1427 0.02414 0.01325 -0.0550 0.9316 0.0692
-3.250 -0.1080 0.02295 0.01192 -0.0563 0.9213 0.0790
-2.750 -0.0423 0.02050 0.00998 -0.0590 0.9015 0.1994
-2.500 -0.0186 0.01903 0.00949 -0.0588 0.8906 0.4085
-2.250 0.0012 0.01777 0.00943 -0.0557 0.8811 0.7017
-2.000 0.0909 0.01705 0.00850 -0.0659 0.8790 1.0000
-1.750 0.1172 0.01720 0.00820 -0.0658 0.8675 1.0000
-1.500 0.1433 0.01736 0.00801 -0.0656 0.8569 1.0000
-1.250 0.1688 0.01754 0.00788 -0.0653 0.8467 1.0000
-1.000 0.1927 0.01776 0.00785 -0.0647 0.8360 1.0000
-0.750 0.2171 0.01799 0.00784 -0.0642 0.8263 1.0000
-0.500 0.2426 0.01820 0.00780 -0.0637 0.8178 1.0000
-0.250 0.2663 0.01847 0.00790 -0.0631 0.8080 1.0000
0.000 0.2905 0.01875 0.00802 -0.0626 0.7990 1.0000
0.250 0.3159 0.01898 0.00810 -0.0620 0.7913 1.0000
0.500 0.3394 0.01932 0.00833 -0.0615 0.7819 1.0000
0.750 0.3640 0.01962 0.00852 -0.0610 0.7739 1.0000
1.000 0.3892 0.01992 0.00875 -0.0605 0.7658 1.0000
1.250 0.4135 0.02029 0.00908 -0.0601 0.7572 1.0000
1.500 0.4394 0.02056 0.00929 -0.0596 0.7503 1.0000
1.750 0.4630 0.02099 0.00971 -0.0592 0.7412 1.0000
2.000 0.4883 0.02132 0.01001 -0.0587 0.7340 1.0000
2.250 0.5125 0.02173 0.01047 -0.0582 0.7255 1.0000
2.500 0.5366 0.02215 0.01092 -0.0577 0.7172 1.0000
2.750 0.5620 0.02247 0.01128 -0.0572 0.7098 1.0000
3.000 0.5852 0.02297 0.01184 -0.0566 0.7004 1.0000
3.250 0.6103 0.02330 0.01224 -0.0560 0.6926 1.0000
3.500 0.6343 0.02370 0.01279 -0.0553 0.6832 1.0000
3.750 0.6574 0.02415 0.01335 -0.0546 0.6729 1.0000
4.000 0.6817 0.02448 0.01379 -0.0538 0.6630 1.0000
4.250 0.7074 0.02465 0.01407 -0.0528 0.6537 1.0000
4.500 0.7303 0.02503 0.01460 -0.0519 0.6415 1.0000
4.750 0.7536 0.02532 0.01514 -0.0508 0.6289 1.0000
5.000 0.7773 0.02550 0.01549 -0.0496 0.6154 1.0000
5.250 0.8013 0.02557 0.01574 -0.0483 0.6010 1.0000
5.500 0.8257 0.02551 0.01586 -0.0468 0.5855 1.0000
5.750 0.8473 0.02563 0.01621 -0.0453 0.5661 1.0000
6.000 0.8709 0.02544 0.01622 -0.0435 0.5459 1.0000
6.250 0.8924 0.02536 0.01648 -0.0417 0.5213 1.0000
6.500 0.9138 0.02518 0.01651 -0.0397 0.4921 1.0000
6.750 0.9332 0.02516 0.01668 -0.0376 0.4544 1.0000
7.000 0.9513 0.02524 0.01681 -0.0353 0.4049 1.0000
7.250 0.9658 0.02574 0.01711 -0.0328 0.3371 1.0000
7.500 0.9743 0.02709 0.01799 -0.0303 0.2661 1.0000
7.750 0.9791 0.02904 0.01956 -0.0281 0.2089 1.0000
8.000 0.9819 0.03124 0.02143 -0.0260 0.1650 1.0000
8.250 0.9845 0.03349 0.02347 -0.0240 0.1297 1.0000
8.500 0.9858 0.03583 0.02563 -0.0220 0.1023 1.0000
8.750 0.9861 0.03816 0.02783 -0.0199 0.0826 1.0000
9.000 0.9886 0.04054 0.03017 -0.0181 0.0662 1.0000
9.250 0.9937 0.04290 0.03269 -0.0165 0.0550 1.0000
9.500 1.0009 0.04530 0.03506 -0.0151 0.0478 1.0000
9.750 1.0110 0.04750 0.03749 -0.0139 0.0404 1.0000
10.000 1.0246 0.04991 0.04001 -0.0125 0.0361 1.0000
10.250 1.0465 0.05272 0.04325 -0.0110 0.0333 1.0000
10.500 1.0593 0.05596 0.04686 -0.0099 0.0316 1.0000
10.750 1.0645 0.05948 0.05071 -0.0090 0.0306 1.0000
11.000 1.0640 0.06314 0.05468 -0.0084 0.0299 1.0000
11.250 1.0586 0.06707 0.05887 -0.0082 0.0292 1.0000
11.500 1.0504 0.07130 0.06336 -0.0087 0.0289 1.0000
11.750 1.0392 0.07597 0.06828 -0.0097 0.0287 1.0000
12.000 1.0252 0.08120 0.07375 -0.0115 0.0286 1.0000
12.250 1.0071 0.08750 0.08030 -0.0143 0.0290 1.0000
12.500 0.9861 0.09481 0.08783 -0.0183 0.0296 1.0000
12.750 0.9620 0.10350 0.09670 -0.0236 0.0304 1.0000
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Polar data table (+)
Polar graphs
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