GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 50,000 Max Cl/Cd: 36.1 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe147-il-50000-n5.txt Download as CSV file: xf-goe147-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 147 (MVA H.6) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4452 0.10188 0.09540 -0.0002 1.0000 0.0506
-7.750 -0.4377 0.09815 0.09171 -0.0011 1.0000 0.0500
-7.500 -0.4312 0.09437 0.08799 -0.0034 1.0000 0.0497
-7.250 -0.4232 0.09037 0.08405 -0.0065 1.0000 0.0496
-7.000 -0.4138 0.08621 0.07992 -0.0101 1.0000 0.0495
-6.750 -0.4027 0.08190 0.07564 -0.0139 1.0000 0.0494
-6.500 -0.3900 0.07745 0.07121 -0.0177 1.0000 0.0492
-6.250 -0.3755 0.07288 0.06664 -0.0217 1.0000 0.0487
-6.000 -0.3589 0.06810 0.06183 -0.0259 1.0000 0.0483
-5.750 -0.3400 0.06307 0.05674 -0.0304 1.0000 0.0481
-5.500 -0.3185 0.05771 0.05126 -0.0351 1.0000 0.0482
-5.250 -0.2932 0.05158 0.04492 -0.0406 1.0000 0.0495
-5.000 -0.2645 0.04442 0.03741 -0.0464 1.0000 0.0514
-4.750 -0.2419 0.04273 0.03561 -0.0469 1.0000 0.0545
-4.500 -0.2133 0.03794 0.03045 -0.0498 1.0000 0.0569
-4.250 -0.1803 0.03152 0.02319 -0.0535 1.0000 0.0628
-4.000 -0.1558 0.03102 0.02266 -0.0532 1.0000 0.0708
-3.750 -0.1277 0.02856 0.01980 -0.0538 1.0000 0.0805
-3.500 -0.1002 0.02692 0.01773 -0.0541 1.0000 0.1007
-3.250 -0.0744 0.02576 0.01620 -0.0539 1.0000 0.1264
-3.000 -0.0522 0.02557 0.01604 -0.0532 1.0000 0.1459
-2.750 -0.0306 0.02566 0.01605 -0.0526 1.0000 0.1703
-2.500 -0.0080 0.02510 0.01528 -0.0522 1.0000 0.1831
-2.250 0.0132 0.02453 0.01458 -0.0516 1.0000 0.1897
-2.000 0.0531 0.02376 0.01340 -0.0544 0.9870 0.1959
-1.750 0.1001 0.02292 0.01235 -0.0584 0.9664 0.1994
-1.500 0.1472 0.02223 0.01142 -0.0620 0.9407 0.2047
-1.250 0.1923 0.02165 0.01057 -0.0647 0.9114 0.2113
-1.000 0.2329 0.02112 0.00985 -0.0664 0.8809 0.2158
-0.750 0.2681 0.02072 0.00925 -0.0670 0.8511 0.2203
-0.500 0.2988 0.02043 0.00877 -0.0666 0.8225 0.2254
-0.250 0.3266 0.02017 0.00840 -0.0658 0.7947 0.2313
0.000 0.3532 0.02000 0.00809 -0.0648 0.7680 0.2395
0.250 0.3788 0.01983 0.00785 -0.0637 0.7427 0.2518
0.500 0.4043 0.01967 0.00765 -0.0626 0.7182 0.2687
0.750 0.4297 0.01945 0.00749 -0.0617 0.6939 0.2926
1.250 0.4776 0.01766 0.00718 -0.0589 0.6480 1.0000
1.500 0.5035 0.01795 0.00714 -0.0579 0.6257 1.0000
1.750 0.5294 0.01826 0.00720 -0.0570 0.6022 1.0000
2.000 0.5552 0.01858 0.00731 -0.0562 0.5795 1.0000
2.250 0.5810 0.01893 0.00748 -0.0555 0.5567 1.0000
2.500 0.6068 0.01929 0.00768 -0.0548 0.5342 1.0000
2.750 0.6326 0.01968 0.00795 -0.0541 0.5118 1.0000
3.000 0.6584 0.02008 0.00822 -0.0535 0.4907 1.0000
3.250 0.6846 0.02050 0.00857 -0.0531 0.4691 1.0000
3.500 0.7106 0.02093 0.00892 -0.0526 0.4498 1.0000
3.750 0.7365 0.02138 0.00931 -0.0521 0.4296 1.0000
4.000 0.7620 0.02181 0.00967 -0.0516 0.4095 1.0000
4.250 0.7872 0.02226 0.01003 -0.0510 0.3912 1.0000
4.500 0.8124 0.02277 0.01047 -0.0505 0.3733 1.0000
4.750 0.8376 0.02332 0.01099 -0.0500 0.3571 1.0000
5.000 0.8627 0.02393 0.01161 -0.0496 0.3429 1.0000
5.250 0.8878 0.02459 0.01225 -0.0491 0.3302 1.0000
5.500 0.9128 0.02529 0.01297 -0.0487 0.3182 1.0000
5.750 0.9378 0.02605 0.01384 -0.0483 0.3063 1.0000
6.000 0.9627 0.02687 0.01480 -0.0479 0.2960 1.0000
6.500 1.0122 0.02867 0.01686 -0.0471 0.2785 1.0000
6.750 1.0369 0.02961 0.01786 -0.0467 0.2717 1.0000
7.000 1.0610 0.03074 0.01934 -0.0463 0.2641 1.0000
7.250 1.0856 0.03175 0.02044 -0.0459 0.2587 1.0000
7.500 1.1086 0.03309 0.02213 -0.0455 0.2524 1.0000
7.750 1.1319 0.03431 0.02361 -0.0451 0.2470 1.0000
8.000 1.1563 0.03540 0.02482 -0.0446 0.2430 1.0000
8.250 1.1765 0.03716 0.02716 -0.0442 0.2378 1.0000
8.500 1.1975 0.03881 0.02921 -0.0438 0.2340 1.0000
8.750 1.2203 0.03991 0.03056 -0.0431 0.2296 1.0000
9.000 1.2360 0.03924 0.03008 -0.0417 0.2095 1.0000
9.250 1.2490 0.03829 0.02923 -0.0402 0.1852 1.0000
9.500 1.2610 0.03883 0.03020 -0.0392 0.1639 1.0000
9.750 1.2715 0.03961 0.03119 -0.0382 0.1345 1.0000
10.250 1.2684 0.04524 0.03644 -0.0363 0.0603 1.0000
10.500 1.2556 0.04915 0.04027 -0.0354 0.0551 1.0000
10.750 1.2434 0.05349 0.04478 -0.0358 0.0524 1.0000
11.000 1.2303 0.05864 0.05012 -0.0376 0.0507 1.0000
11.250 1.2165 0.06443 0.05611 -0.0403 0.0495 1.0000
11.500 1.2023 0.07058 0.06243 -0.0433 0.0486 1.0000
11.750 1.1880 0.07685 0.06885 -0.0462 0.0478 1.0000
12.000 1.1741 0.08307 0.07518 -0.0489 0.0470 1.0000
12.250 1.1612 0.08911 0.08131 -0.0514 0.0461 1.0000
12.500 1.1494 0.09488 0.08712 -0.0536 0.0451 1.0000
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Polar data table (+)
Polar graphs
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