GOE 133 (MVA H.11) AIRFOIL (goe133-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 133 (MVA H.11) AIRFOIL (goe133-il) Reynolds number: 50,000 Max Cl/Cd: 33.62 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe133-il-50000.txt Download as CSV file: xf-goe133-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 133 (MVA H.11) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3975 0.10657 0.09991 -0.0184 1.0000 0.1502
-7.750 -0.3759 0.10041 0.09374 -0.0158 1.0000 0.1581
-7.500 -0.3827 0.09902 0.09248 -0.0180 1.0000 0.1639
-7.250 -0.3771 0.09524 0.08875 -0.0182 1.0000 0.1685
-7.000 -0.3717 0.09234 0.08591 -0.0185 1.0000 0.1771
-6.750 -0.3720 0.08958 0.08326 -0.0211 1.0000 0.1824
-6.500 -0.3654 0.08656 0.08030 -0.0205 1.0000 0.1926
-6.000 -0.3614 0.08122 0.07510 -0.0244 1.0000 0.2111
-5.750 -0.3558 0.07849 0.07242 -0.0243 1.0000 0.2248
-5.500 -0.3492 0.07503 0.06904 -0.0217 1.0000 0.2385
-5.250 -0.3455 0.07233 0.06640 -0.0226 1.0000 0.2563
-5.000 -0.3398 0.06907 0.06324 -0.0180 1.0000 0.2760
-4.750 -0.3365 0.06653 0.06075 -0.0169 1.0000 0.3035
-4.500 0.0149 0.04104 0.03429 -0.0221 1.0000 1.0000
-4.250 0.0264 0.03905 0.03235 -0.0231 1.0000 1.0000
-4.000 0.0376 0.03715 0.03050 -0.0241 1.0000 1.0000
-3.750 0.0160 0.03733 0.03084 -0.0174 1.0000 0.9853
-3.500 -0.0396 0.03922 0.03300 -0.0036 1.0000 0.9445
-3.250 -0.0897 0.04037 0.03443 0.0075 1.0000 0.9039
-3.000 -0.1392 0.04108 0.03543 0.0177 1.0000 0.8702
-2.750 -0.1908 0.04160 0.03624 0.0279 1.0000 0.8423
-2.500 -0.2620 0.04267 0.03763 0.0411 1.0000 0.8150
-2.250 -0.0678 0.03442 0.02590 -0.0503 1.0000 0.1966
-2.000 -0.0382 0.03228 0.02342 -0.0512 1.0000 0.1868
-1.750 -0.0081 0.03069 0.02138 -0.0521 1.0000 0.1846
-1.500 0.0223 0.02967 0.01975 -0.0527 1.0000 0.1804
-1.250 0.0468 0.02846 0.01851 -0.0532 1.0000 0.1876
-1.000 0.0716 0.02783 0.01760 -0.0535 1.0000 0.1909
-0.750 0.0947 0.02753 0.01702 -0.0537 1.0000 0.1949
-0.500 0.1152 0.02726 0.01675 -0.0539 1.0000 0.2054
-0.250 0.1639 0.02691 0.01620 -0.0584 0.9903 0.2192
0.000 0.2248 0.02640 0.01569 -0.0649 0.9746 0.2541
0.250 0.2828 0.02435 0.01528 -0.0713 0.9616 0.5097
0.500 0.3328 0.02413 0.01491 -0.0741 0.9416 1.0000
0.750 0.3766 0.02476 0.01520 -0.0777 0.9202 1.0000
1.000 0.4234 0.02529 0.01549 -0.0817 0.9014 1.0000
1.250 0.4700 0.02570 0.01575 -0.0853 0.8841 1.0000
1.500 0.5156 0.02601 0.01595 -0.0884 0.8677 1.0000
1.750 0.5508 0.02640 0.01627 -0.0897 0.8499 1.0000
2.000 0.5855 0.02662 0.01643 -0.0904 0.8306 1.0000
2.250 0.6264 0.02631 0.01608 -0.0911 0.8111 1.0000
2.500 0.6630 0.02596 0.01569 -0.0907 0.7912 1.0000
2.750 0.6922 0.02594 0.01565 -0.0896 0.7704 1.0000
3.000 0.7236 0.02583 0.01554 -0.0887 0.7521 1.0000
3.250 0.7543 0.02577 0.01546 -0.0877 0.7347 1.0000
3.500 0.7801 0.02605 0.01575 -0.0864 0.7156 1.0000
3.750 0.8054 0.02637 0.01612 -0.0850 0.6957 1.0000
4.000 0.8327 0.02651 0.01625 -0.0836 0.6765 1.0000
4.250 0.8590 0.02675 0.01650 -0.0821 0.6566 1.0000
4.500 0.8825 0.02721 0.01700 -0.0805 0.6341 1.0000
4.750 0.9101 0.02735 0.01712 -0.0789 0.6136 1.0000
5.000 0.9320 0.02809 0.01794 -0.0774 0.5894 1.0000
5.250 0.9589 0.02852 0.01831 -0.0760 0.5688 1.0000
5.500 0.9801 0.02956 0.01945 -0.0747 0.5453 1.0000
5.750 1.0054 0.03031 0.02022 -0.0735 0.5258 1.0000
6.000 1.0283 0.03142 0.02140 -0.0724 0.5074 1.0000
6.250 1.0497 0.03282 0.02294 -0.0715 0.4908 1.0000
6.500 1.0711 0.03412 0.02438 -0.0706 0.4750 1.0000
6.750 1.0921 0.03520 0.02562 -0.0693 0.4581 1.0000
7.000 1.1144 0.03582 0.02633 -0.0679 0.4398 1.0000
7.250 1.1381 0.03622 0.02678 -0.0664 0.4219 1.0000
7.500 1.1622 0.03641 0.02702 -0.0648 0.4031 1.0000
7.750 1.1801 0.03719 0.02803 -0.0631 0.3834 1.0000
8.000 1.2036 0.03721 0.02809 -0.0614 0.3624 1.0000
8.250 1.2225 0.03757 0.02859 -0.0594 0.3384 1.0000
8.500 1.2423 0.03751 0.02851 -0.0570 0.3085 1.0000
8.750 1.2636 0.03766 0.02832 -0.0547 0.2736 1.0000
9.000 1.2768 0.03941 0.03001 -0.0523 0.2421 1.0000
9.250 1.2926 0.04162 0.03220 -0.0504 0.2181 1.0000
9.500 1.3068 0.04398 0.03460 -0.0486 0.1991 1.0000
9.750 1.3198 0.04671 0.03752 -0.0468 0.1844 1.0000
10.000 1.3323 0.04923 0.04020 -0.0451 0.1709 1.0000
10.250 1.3464 0.05164 0.04266 -0.0435 0.1583 1.0000
10.500 1.3394 0.05537 0.04705 -0.0405 0.1513 1.0000
10.750 1.3464 0.05811 0.04990 -0.0387 0.1420 1.0000
11.000 1.3366 0.06207 0.05431 -0.0360 0.1372 1.0000
11.250 1.3420 0.06486 0.05714 -0.0343 0.1297 1.0000
11.500 1.3186 0.06959 0.06228 -0.0317 0.1287 1.0000
11.750 1.2912 0.07450 0.06745 -0.0296 0.1288 1.0000
12.000 1.2618 0.08023 0.07339 -0.0292 0.1296 1.0000
12.250 1.2324 0.08692 0.08022 -0.0305 0.1306 1.0000
12.500 1.2045 0.09452 0.08791 -0.0332 0.1315 1.0000
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Polar data table (+)
Polar graphs
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