GOE 147 (MVA H.6) AIRFOIL (goe147-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 147 (MVA H.6) AIRFOIL (goe147-il) Reynolds number: 100,000 Max Cl/Cd: 48.61 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe147-il-100000.txt Download as CSV file: xf-goe147-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4684 0.10687 0.10222 0.0139 1.0000 0.0870
-8.000 -0.4671 0.10436 0.09977 0.0106 1.0000 0.0899
-7.750 -0.4727 0.10327 0.09878 0.0012 1.0000 0.0912
-7.500 -0.4651 0.09900 0.09456 -0.0056 1.0000 0.0919
-7.250 -0.4523 0.09329 0.08887 0.0028 1.0000 0.0936
-7.000 -0.4403 0.08967 0.08526 0.0036 1.0000 0.0967
-6.750 -0.4296 0.08615 0.08177 0.0004 1.0000 0.1002
-6.500 -0.4097 0.08304 0.07857 -0.0168 1.0000 0.1047
-6.250 -0.3956 0.07772 0.07326 -0.0198 1.0000 0.1055
-6.000 -0.3841 0.07319 0.06878 -0.0178 1.0000 0.1065
-5.750 -0.3691 0.06924 0.06483 -0.0182 1.0000 0.1079
-5.500 -0.3511 0.06534 0.06091 -0.0203 1.0000 0.1097
-5.250 -0.3299 0.06129 0.05681 -0.0238 1.0000 0.1120
-5.000 -0.2880 0.04876 0.04370 -0.0387 1.0000 0.0802
-4.750 -0.2636 0.04423 0.03902 -0.0405 1.0000 0.0773
-4.500 -0.2362 0.03885 0.03337 -0.0434 1.0000 0.0753
-4.250 -0.2036 0.03075 0.02456 -0.0474 1.0000 0.0722
-4.000 -0.1732 0.02575 0.01885 -0.0489 1.0000 0.0754
-3.750 -0.1460 0.02410 0.01695 -0.0490 1.0000 0.0839
-3.500 -0.1177 0.02185 0.01422 -0.0490 1.0000 0.0948
-3.250 -0.0920 0.02123 0.01352 -0.0485 1.0000 0.1156
-3.000 -0.0675 0.02070 0.01292 -0.0479 1.0000 0.1489
-2.750 -0.0457 0.02094 0.01328 -0.0470 1.0000 0.1720
-2.500 -0.0240 0.02084 0.01304 -0.0463 1.0000 0.1904
-2.250 -0.0077 0.02079 0.01319 -0.0452 1.0000 0.2078
-2.000 0.0157 0.02064 0.01281 -0.0456 0.9973 0.2179
-1.750 0.0735 0.01938 0.01145 -0.0518 0.9796 0.2232
-1.500 0.1292 0.01838 0.01022 -0.0571 0.9594 0.2248
-1.250 0.1781 0.01761 0.00927 -0.0608 0.9333 0.2275
-1.000 0.2191 0.01711 0.00853 -0.0626 0.9033 0.2318
-0.750 0.2505 0.01661 0.00794 -0.0624 0.8718 0.2346
-0.500 0.2769 0.01629 0.00752 -0.0611 0.8412 0.2376
-0.250 0.3021 0.01606 0.00717 -0.0597 0.8124 0.2415
0.000 0.3273 0.01591 0.00686 -0.0583 0.7854 0.2462
0.250 0.3520 0.01564 0.00658 -0.0570 0.7600 0.2521
0.500 0.3768 0.01550 0.00633 -0.0556 0.7353 0.2607
0.750 0.4015 0.01530 0.00615 -0.0544 0.7098 0.2739
1.000 0.4268 0.01510 0.00595 -0.0532 0.6847 0.2945
1.250 0.4523 0.01474 0.00573 -0.0523 0.6602 0.3489
1.500 0.4758 0.01323 0.00545 -0.0502 0.6339 1.0000
1.750 0.5018 0.01353 0.00546 -0.0493 0.6058 1.0000
2.000 0.5277 0.01386 0.00554 -0.0484 0.5770 1.0000
2.250 0.5537 0.01421 0.00565 -0.0477 0.5480 1.0000
2.500 0.5797 0.01455 0.00577 -0.0470 0.5196 1.0000
2.750 0.6058 0.01486 0.00590 -0.0463 0.4924 1.0000
3.000 0.6319 0.01516 0.00600 -0.0457 0.4684 1.0000
3.250 0.6586 0.01547 0.00621 -0.0453 0.4450 1.0000
3.500 0.6852 0.01582 0.00642 -0.0449 0.4263 1.0000
3.750 0.7118 0.01622 0.00672 -0.0446 0.4093 1.0000
4.000 0.7386 0.01665 0.00708 -0.0442 0.3929 1.0000
4.250 0.7652 0.01712 0.00748 -0.0439 0.3777 1.0000
4.500 0.7917 0.01764 0.00793 -0.0436 0.3633 1.0000
4.750 0.8181 0.01823 0.00847 -0.0433 0.3495 1.0000
5.000 0.8444 0.01886 0.00904 -0.0430 0.3359 1.0000
5.250 0.8705 0.01955 0.00966 -0.0427 0.3227 1.0000
5.500 0.8967 0.02025 0.01038 -0.0424 0.3097 1.0000
5.750 0.9227 0.02099 0.01120 -0.0421 0.2972 1.0000
6.000 0.9487 0.02185 0.01214 -0.0418 0.2866 1.0000
6.250 0.9750 0.02277 0.01301 -0.0415 0.2786 1.0000
6.500 1.0007 0.02368 0.01418 -0.0413 0.2703 1.0000
6.750 1.0271 0.02472 0.01516 -0.0411 0.2650 1.0000
7.000 1.0522 0.02583 0.01665 -0.0408 0.2592 1.0000
7.250 1.0778 0.02693 0.01794 -0.0405 0.2548 1.0000
7.500 1.1038 0.02801 0.01901 -0.0403 0.2507 1.0000
7.750 1.1270 0.02816 0.01944 -0.0397 0.2394 1.0000
8.000 1.1504 0.02764 0.01889 -0.0391 0.2245 1.0000
8.250 1.1734 0.02769 0.01915 -0.0385 0.2132 1.0000
8.500 1.1960 0.02730 0.01892 -0.0378 0.1997 1.0000
8.750 1.2180 0.02649 0.01834 -0.0369 0.1825 1.0000
9.000 1.2400 0.02551 0.01764 -0.0363 0.1419 1.0000
9.250 1.2572 0.02711 0.01892 -0.0354 0.0756 1.0000
9.500 1.2686 0.02960 0.02118 -0.0341 0.0608 1.0000
9.750 1.2773 0.03211 0.02375 -0.0326 0.0552 1.0000
10.000 1.2864 0.03433 0.02619 -0.0311 0.0511 1.0000
10.250 1.2907 0.03683 0.02881 -0.0294 0.0481 1.0000
10.500 1.2923 0.03951 0.03153 -0.0273 0.0463 1.0000
10.750 1.2984 0.04194 0.03406 -0.0254 0.0451 1.0000
11.000 1.3054 0.04416 0.03645 -0.0234 0.0443 1.0000
11.250 1.3127 0.04659 0.03906 -0.0217 0.0435 1.0000
11.500 1.3183 0.04927 0.04193 -0.0201 0.0427 1.0000
11.750 1.3207 0.05220 0.04508 -0.0189 0.0417 1.0000
12.000 1.3205 0.05539 0.04847 -0.0182 0.0407 1.0000
12.250 1.3183 0.05888 0.05217 -0.0179 0.0398 1.0000
12.500 1.3130 0.06281 0.05631 -0.0182 0.0393 1.0000
12.750 1.3051 0.06722 0.06096 -0.0191 0.0391 1.0000
13.000 1.2940 0.07223 0.06624 -0.0209 0.0391 1.0000
13.250 1.2789 0.07800 0.07226 -0.0236 0.0393 1.0000
13.500 1.2596 0.08470 0.07923 -0.0275 0.0396 1.0000
13.750 1.2371 0.09231 0.08709 -0.0323 0.0400 1.0000
14.000 1.2112 0.10106 0.09607 -0.0382 0.0406 1.0000
14.250 1.1809 0.11138 0.10660 -0.0454 0.0415 1.0000
14.500 1.1474 0.12333 0.11872 -0.0533 0.0430 1.0000
14.750 1.1171 0.13548 0.13096 -0.0608 0.0445 1.0000
15.000 1.0951 0.14614 0.14165 -0.0666 0.0455 1.0000
15.250 1.0236 0.17915 0.17451 -0.0860 0.0551 1.0000
15.500 1.0288 0.18398 0.17937 -0.0873 0.0565 1.0000
15.750 1.0226 0.19650 0.19181 -0.0924 0.0664 1.0000
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Polar data table (+)
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