MH 106 13.07% (mh106-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 106 13.07% (mh106-il) Reynolds number: 100,000 Max Cl/Cd: 42.08 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh106-il-100000.txt Download as CSV file: xf-mh106-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 106 13.07%
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5548 0.09658 0.09222 -0.0081 1.0000 0.0533
-11.250 -0.5632 0.09013 0.08578 -0.0103 1.0000 0.0517
-11.000 -0.6865 0.08269 0.07796 -0.0178 1.0000 0.0522
-10.750 -0.7096 0.07554 0.07077 -0.0229 1.0000 0.0513
-10.500 -0.7349 0.06960 0.06472 -0.0266 1.0000 0.0506
-10.250 -0.7590 0.06477 0.05975 -0.0279 1.0000 0.0496
-10.000 -0.7829 0.06070 0.05550 -0.0268 1.0000 0.0485
-9.750 -0.8084 0.05652 0.05098 -0.0242 1.0000 0.0468
-9.500 -0.8367 0.05312 0.04674 -0.0199 1.0000 0.0438
-9.250 -0.8277 0.05010 0.04346 -0.0184 1.0000 0.0427
-9.000 -0.8226 0.04594 0.03903 -0.0167 1.0000 0.0420
-8.750 -0.8147 0.04242 0.03518 -0.0149 1.0000 0.0415
-8.500 -0.8035 0.03927 0.03164 -0.0131 1.0000 0.0412
-8.250 -0.7887 0.03644 0.02846 -0.0114 1.0000 0.0411
-8.000 -0.7714 0.03422 0.02588 -0.0098 1.0000 0.0421
-7.750 -0.7522 0.03179 0.02317 -0.0084 1.0000 0.0439
-7.500 -0.7299 0.02924 0.02066 -0.0078 1.0000 0.0467
-7.250 -0.7071 0.02737 0.01873 -0.0067 1.0000 0.0493
-7.000 -0.6845 0.02564 0.01692 -0.0054 1.0000 0.0530
-6.750 -0.6672 0.02378 0.01518 -0.0037 1.0000 0.0588
-6.500 -0.6516 0.02227 0.01367 -0.0016 1.0000 0.0687
-6.250 -0.6396 0.02058 0.01213 0.0011 1.0000 0.0864
-6.000 -0.6393 0.01768 0.01035 0.0051 1.0000 0.2034
-5.750 -0.6290 0.01717 0.01023 0.0081 1.0000 0.3126
-5.500 -0.6139 0.01709 0.01017 0.0105 1.0000 0.3540
-5.250 -0.5987 0.01698 0.01009 0.0128 1.0000 0.3851
-5.000 -0.5852 0.01687 0.01003 0.0152 1.0000 0.4126
-4.750 -0.5765 0.01679 0.00995 0.0182 1.0000 0.4372
-4.500 -0.5553 0.01674 0.00997 0.0185 0.9937 0.4632
-4.250 -0.4998 0.01646 0.00965 0.0128 0.9722 0.4963
-4.000 -0.4453 0.01606 0.00925 0.0077 0.9514 0.5259
-3.750 -0.3961 0.01566 0.00884 0.0039 0.9279 0.5547
-3.500 -0.3548 0.01533 0.00852 0.0019 0.9009 0.5821
-3.250 -0.3225 0.01511 0.00829 0.0019 0.8727 0.6090
-3.000 -0.2962 0.01496 0.00810 0.0030 0.8454 0.6363
-2.750 -0.2718 0.01485 0.00797 0.0046 0.8209 0.6652
-2.500 -0.2477 0.01478 0.00790 0.0063 0.7970 0.6959
-2.250 -0.2232 0.01476 0.00784 0.0079 0.7763 0.7285
-2.000 -0.1981 0.01479 0.00787 0.0093 0.7561 0.7630
-1.750 -0.1695 0.01492 0.00796 0.0104 0.7380 0.7956
-1.500 -0.1377 0.01515 0.00810 0.0108 0.7211 0.8270
-1.250 -0.1020 0.01547 0.00830 0.0105 0.7052 0.8555
-1.000 -0.0637 0.01584 0.00852 0.0094 0.6902 0.8814
-0.750 -0.0151 0.01627 0.00879 0.0064 0.6752 0.9000
-0.500 0.0368 0.01667 0.00902 0.0024 0.6607 0.9168
-0.250 0.0891 0.01700 0.00920 -0.0019 0.6471 0.9333
0.000 0.1399 0.01724 0.00932 -0.0063 0.6342 0.9503
0.250 0.1910 0.01742 0.00940 -0.0110 0.6222 0.9673
0.500 0.2451 0.01747 0.00934 -0.0165 0.6114 0.9826
0.750 0.3012 0.01732 0.00906 -0.0226 0.6012 0.9969
1.000 0.3282 0.01731 0.00905 -0.0235 0.5917 1.0000
1.250 0.3471 0.01737 0.00902 -0.0225 0.5852 1.0000
1.500 0.3670 0.01749 0.00917 -0.0219 0.5766 1.0000
1.750 0.3871 0.01762 0.00922 -0.0209 0.5703 1.0000
2.000 0.4078 0.01782 0.00948 -0.0203 0.5621 1.0000
2.250 0.4285 0.01800 0.00956 -0.0192 0.5562 1.0000
2.500 0.4494 0.01830 0.00996 -0.0185 0.5479 1.0000
2.750 0.4706 0.01851 0.01010 -0.0174 0.5419 1.0000
3.000 0.4915 0.01889 0.01058 -0.0167 0.5337 1.0000
3.250 0.5132 0.01912 0.01075 -0.0156 0.5275 1.0000
3.500 0.5341 0.01956 0.01131 -0.0149 0.5193 1.0000
3.750 0.5561 0.01980 0.01150 -0.0138 0.5129 1.0000
4.000 0.5769 0.02028 0.01210 -0.0129 0.5043 1.0000
4.250 0.5994 0.02049 0.01225 -0.0118 0.4978 1.0000
4.500 0.6199 0.02099 0.01291 -0.0109 0.4885 1.0000
4.750 0.6425 0.02123 0.01311 -0.0097 0.4813 1.0000
5.000 0.6634 0.02163 0.01362 -0.0087 0.4717 1.0000
5.250 0.6848 0.02200 0.01406 -0.0076 0.4628 1.0000
5.500 0.7081 0.02213 0.01417 -0.0064 0.4543 1.0000
5.750 0.7285 0.02255 0.01472 -0.0053 0.4436 1.0000
6.000 0.7505 0.02280 0.01502 -0.0041 0.4337 1.0000
6.250 0.7747 0.02281 0.01497 -0.0030 0.4244 1.0000
6.500 0.7952 0.02310 0.01542 -0.0017 0.4123 1.0000
6.750 0.8165 0.02332 0.01574 -0.0004 0.4003 1.0000
7.000 0.8386 0.02342 0.01589 0.0008 0.3881 1.0000
7.250 0.8610 0.02344 0.01594 0.0021 0.3754 1.0000
7.500 0.8832 0.02342 0.01598 0.0034 0.3616 1.0000
7.750 0.9046 0.02341 0.01603 0.0048 0.3465 1.0000
8.000 0.9252 0.02337 0.01606 0.0063 0.3298 1.0000
8.250 0.9456 0.02329 0.01603 0.0078 0.3121 1.0000
8.500 0.9662 0.02317 0.01585 0.0093 0.2937 1.0000
8.750 0.9824 0.02345 0.01624 0.0112 0.2715 1.0000
9.000 0.9993 0.02375 0.01646 0.0129 0.2505 1.0000
9.250 1.0128 0.02447 0.01718 0.0149 0.2277 1.0000
9.500 1.0262 0.02540 0.01797 0.0168 0.2079 1.0000
9.750 1.0371 0.02653 0.01911 0.0188 0.1885 1.0000
10.000 1.0479 0.02775 0.02028 0.0208 0.1717 1.0000
10.250 1.0576 0.02905 0.02152 0.0228 0.1567 1.0000
10.500 1.0665 0.03046 0.02291 0.0248 0.1432 1.0000
10.750 1.0737 0.03197 0.02445 0.0269 0.1311 1.0000
11.000 1.0799 0.03358 0.02613 0.0289 0.1204 1.0000
11.250 1.0871 0.03527 0.02777 0.0308 0.1107 1.0000
11.500 1.0884 0.03675 0.02928 0.0332 0.1024 1.0000
11.750 1.0879 0.03871 0.03138 0.0356 0.0954 1.0000
12.000 1.0968 0.04063 0.03311 0.0368 0.0869 1.0000
12.250 1.0870 0.04283 0.03565 0.0387 0.0828 1.0000
12.500 1.0890 0.04485 0.03766 0.0397 0.0770 1.0000
12.750 1.0866 0.04767 0.04061 0.0404 0.0721 1.0000
13.000 1.0788 0.05067 0.04384 0.0407 0.0685 1.0000
13.250 1.0895 0.05314 0.04612 0.0414 0.0625 1.0000
13.500 1.0746 0.05681 0.05011 0.0408 0.0610 1.0000
13.750 1.0606 0.06089 0.05446 0.0397 0.0590 1.0000
14.000 1.0482 0.06513 0.05892 0.0383 0.0572 1.0000
14.250 1.0363 0.06952 0.06348 0.0366 0.0556 1.0000
14.500 1.0454 0.07240 0.06620 0.0373 0.0516 1.0000
14.750 1.0264 0.07796 0.07197 0.0348 0.0513 1.0000
15.000 1.0042 0.08424 0.07848 0.0315 0.0512 1.0000
15.250 0.9807 0.09100 0.08544 0.0277 0.0513 1.0000
15.500 0.7941 0.13608 0.13103 -0.0010 0.0747 1.0000
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Polar data table (+)
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