MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 100,000 Max Cl/Cd: 56.43 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh117-il-100000.txt Download as CSV file: xf-mh117-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 117 9.8%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3200 0.09837 0.09375 -0.0287 1.0000 0.1061
-9.250 -0.3311 0.09506 0.09050 -0.0313 1.0000 0.1097
-9.000 -0.3498 0.09175 0.08730 -0.0350 1.0000 0.1107
-8.750 -0.3291 0.08660 0.08215 -0.0322 1.0000 0.1138
-8.500 -0.3235 0.08301 0.07859 -0.0318 1.0000 0.1168
-8.250 -0.3257 0.07934 0.07498 -0.0325 1.0000 0.1196
-8.000 -0.3493 0.07607 0.07184 -0.0357 1.0000 0.1239
-7.750 -0.4713 0.06603 0.06148 -0.0520 1.0000 0.0574
-7.500 -0.4656 0.06326 0.05881 -0.0498 1.0000 0.0559
-7.250 -0.4699 0.05884 0.05438 -0.0503 1.0000 0.0541
-7.000 -0.4975 0.04754 0.04227 -0.0541 1.0000 0.0454
-6.750 -0.4965 0.04332 0.03781 -0.0530 1.0000 0.0450
-6.500 -0.4928 0.03945 0.03351 -0.0518 1.0000 0.0452
-6.250 -0.4858 0.03576 0.02932 -0.0506 1.0000 0.0460
-6.000 -0.4753 0.03285 0.02630 -0.0496 1.0000 0.0485
-5.750 -0.4609 0.03068 0.02389 -0.0483 1.0000 0.0509
-5.500 -0.4437 0.02786 0.02053 -0.0471 1.0000 0.0535
-5.250 -0.4239 0.02558 0.01762 -0.0459 1.0000 0.0582
-5.000 -0.4054 0.02424 0.01620 -0.0450 1.0000 0.0682
-4.750 -0.3846 0.02290 0.01456 -0.0440 1.0000 0.0837
-4.500 -0.3649 0.02184 0.01362 -0.0433 1.0000 0.1041
-4.250 -0.3446 0.02114 0.01279 -0.0425 1.0000 0.1267
-4.000 -0.3250 0.02065 0.01233 -0.0418 1.0000 0.1469
-3.750 -0.2950 0.02003 0.01162 -0.0428 0.9970 0.1693
-3.500 -0.2539 0.01947 0.01102 -0.0458 0.9900 0.1968
-3.250 -0.2126 0.01898 0.01064 -0.0489 0.9832 0.2293
-3.000 -0.1748 0.01849 0.01023 -0.0512 0.9752 0.2679
-2.750 -0.1322 0.01805 0.01001 -0.0545 0.9689 0.3219
-2.500 -0.0985 0.01759 0.00981 -0.0560 0.9597 0.3829
-2.250 -0.0609 0.01715 0.00973 -0.0582 0.9525 0.4665
-2.000 -0.0273 0.01672 0.00973 -0.0592 0.9442 0.5683
-1.750 0.0021 0.01633 0.00984 -0.0589 0.9359 0.6933
-1.500 0.0345 0.01598 0.00992 -0.0580 0.9292 0.8566
-1.250 0.1143 0.01580 0.00956 -0.0680 0.9272 1.0000
-1.000 0.1479 0.01592 0.00944 -0.0697 0.9166 1.0000
-0.750 0.1883 0.01600 0.00934 -0.0724 0.9084 1.0000
-0.500 0.2321 0.01601 0.00919 -0.0756 0.9010 1.0000
-0.250 0.2656 0.01613 0.00917 -0.0768 0.8912 1.0000
0.000 0.3109 0.01604 0.00897 -0.0799 0.8850 1.0000
0.250 0.3395 0.01618 0.00902 -0.0800 0.8737 1.0000
0.500 0.3710 0.01626 0.00903 -0.0806 0.8636 1.0000
0.750 0.4104 0.01614 0.00885 -0.0822 0.8562 1.0000
1.000 0.4365 0.01628 0.00895 -0.0817 0.8444 1.0000
1.250 0.4638 0.01640 0.00904 -0.0813 0.8330 1.0000
1.500 0.4927 0.01646 0.00906 -0.0810 0.8223 1.0000
1.750 0.5255 0.01635 0.00891 -0.0811 0.8134 1.0000
2.000 0.5505 0.01647 0.00902 -0.0802 0.8008 1.0000
2.250 0.5760 0.01658 0.00914 -0.0793 0.7882 1.0000
2.500 0.6019 0.01665 0.00921 -0.0783 0.7755 1.0000
2.750 0.6280 0.01670 0.00926 -0.0774 0.7626 1.0000
3.000 0.6543 0.01673 0.00932 -0.0764 0.7494 1.0000
3.250 0.6804 0.01674 0.00934 -0.0754 0.7356 1.0000
3.500 0.7064 0.01675 0.00936 -0.0744 0.7211 1.0000
3.750 0.7323 0.01674 0.00937 -0.0733 0.7059 1.0000
4.000 0.7583 0.01671 0.00938 -0.0721 0.6900 1.0000
4.250 0.7847 0.01665 0.00932 -0.0710 0.6734 1.0000
4.500 0.8097 0.01664 0.00934 -0.0698 0.6549 1.0000
4.750 0.8342 0.01664 0.00938 -0.0685 0.6341 1.0000
5.000 0.8594 0.01660 0.00935 -0.0672 0.6128 1.0000
5.250 0.8834 0.01659 0.00936 -0.0658 0.5882 1.0000
5.500 0.9065 0.01662 0.00940 -0.0642 0.5605 1.0000
5.750 0.9291 0.01669 0.00943 -0.0627 0.5300 1.0000
6.000 0.9499 0.01688 0.00965 -0.0609 0.4932 1.0000
6.250 0.9701 0.01719 0.00986 -0.0591 0.4529 1.0000
6.500 0.9887 0.01768 0.01020 -0.0573 0.4087 1.0000
6.750 1.0060 0.01840 0.01069 -0.0553 0.3638 1.0000
7.000 1.0221 0.01932 0.01137 -0.0534 0.3202 1.0000
7.250 1.0379 0.02037 0.01222 -0.0515 0.2796 1.0000
7.500 1.0532 0.02153 0.01323 -0.0497 0.2430 1.0000
7.750 1.0684 0.02276 0.01428 -0.0479 0.2111 1.0000
8.000 1.0844 0.02410 0.01548 -0.0462 0.1848 1.0000
8.250 1.1009 0.02551 0.01674 -0.0447 0.1633 1.0000
8.500 1.1182 0.02688 0.01811 -0.0433 0.1449 1.0000
8.750 1.1368 0.02839 0.01960 -0.0420 0.1301 1.0000
9.000 1.1546 0.02989 0.02112 -0.0408 0.1170 1.0000
9.250 1.1745 0.03170 0.02302 -0.0398 0.1062 1.0000
9.500 1.1936 0.03353 0.02485 -0.0388 0.0960 1.0000
9.750 1.2115 0.03528 0.02667 -0.0376 0.0871 1.0000
10.000 1.2269 0.03752 0.02923 -0.0361 0.0793 1.0000
10.250 1.2434 0.03999 0.03169 -0.0351 0.0715 1.0000
10.500 1.2510 0.04183 0.03391 -0.0327 0.0652 1.0000
10.750 1.2621 0.04481 0.03697 -0.0313 0.0592 1.0000
11.000 1.2627 0.04708 0.03967 -0.0283 0.0545 1.0000
11.500 1.2626 0.05309 0.04605 -0.0238 0.0475 1.0000
11.750 1.2483 0.05611 0.04948 -0.0202 0.0462 1.0000
12.000 1.2330 0.05950 0.05322 -0.0176 0.0451 1.0000
12.250 1.2165 0.06302 0.05703 -0.0158 0.0438 1.0000
12.500 1.1988 0.06718 0.06147 -0.0151 0.0433 1.0000
12.750 1.1785 0.07194 0.06650 -0.0153 0.0432 1.0000
13.000 1.1525 0.07805 0.07289 -0.0167 0.0442 1.0000
13.250 1.1261 0.08468 0.07975 -0.0194 0.0447 1.0000
13.500 1.1001 0.09211 0.08737 -0.0231 0.0459 1.0000
13.750 1.0755 0.10010 0.09550 -0.0276 0.0469 1.0000
14.000 1.0527 0.10859 0.10408 -0.0327 0.0478 1.0000
14.250 1.0312 0.11776 0.11331 -0.0381 0.0485 1.0000
14.500 0.9338 0.15811 0.15356 -0.0636 0.0740 1.0000
14.750 0.9424 0.16238 0.15788 -0.0633 0.0727 1.0000
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Polar data table (+)
Polar graphs
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