MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 100,000 Max Cl/Cd: 46.58 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh83-il-100000-n5.txt Download as CSV file: xf-mh83-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 83 13.29%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2235 0.10190 0.09722 -0.0142 0.7647 0.0611
-8.250 -0.2252 0.09903 0.09433 -0.0174 0.7509 0.0628
-7.750 -0.2249 0.09261 0.08788 -0.0231 0.7248 0.0634
-7.250 -0.2165 0.08028 0.07544 -0.0262 0.7046 0.0358
-7.000 -0.2085 0.07779 0.07292 -0.0267 0.6920 0.0352
-6.750 -0.2036 0.07468 0.06979 -0.0284 0.6814 0.0343
-6.250 -0.1969 0.06116 0.05614 -0.0431 0.6653 0.0308
-6.000 -0.1833 0.05621 0.05108 -0.0481 0.6549 0.0304
-5.750 -0.1688 0.04949 0.04410 -0.0543 0.6470 0.0297
-5.500 -0.1515 0.04211 0.03625 -0.0606 0.6383 0.0291
-5.250 -0.1304 0.03630 0.02975 -0.0644 0.6302 0.0288
-5.000 -0.1056 0.03254 0.02539 -0.0663 0.6194 0.0293
-4.750 -0.0794 0.02960 0.02177 -0.0673 0.6097 0.0304
-4.500 -0.0524 0.02749 0.01915 -0.0677 0.5992 0.0315
-4.250 -0.0254 0.02616 0.01758 -0.0678 0.5884 0.0324
-4.000 0.0019 0.02477 0.01584 -0.0677 0.5788 0.0331
-3.750 0.0300 0.02352 0.01434 -0.0676 0.5679 0.0340
-3.500 0.0578 0.02245 0.01296 -0.0673 0.5587 0.0352
-3.250 0.0857 0.02154 0.01188 -0.0671 0.5482 0.0365
-3.000 0.1133 0.02091 0.01116 -0.0669 0.5388 0.0388
-2.750 0.1412 0.02031 0.01042 -0.0667 0.5292 0.0423
-2.500 0.1692 0.01979 0.00980 -0.0665 0.5199 0.0463
-2.250 0.1972 0.01926 0.00918 -0.0663 0.5111 0.0509
-2.000 0.2255 0.01879 0.00865 -0.0662 0.5022 0.0608
-1.750 0.2537 0.01829 0.00818 -0.0661 0.4939 0.0852
-1.500 0.2817 0.01785 0.00790 -0.0661 0.4854 0.1330
-1.250 0.3092 0.01751 0.00779 -0.0661 0.4772 0.2034
-1.000 0.3370 0.01728 0.00771 -0.0660 0.4693 0.2713
-0.750 0.3645 0.01710 0.00762 -0.0658 0.4617 0.3333
-0.500 0.3918 0.01694 0.00754 -0.0655 0.4550 0.4006
-0.250 0.4191 0.01676 0.00756 -0.0652 0.4471 0.4828
0.000 0.4447 0.01653 0.00752 -0.0644 0.4410 0.5885
0.250 0.4673 0.01620 0.00758 -0.0626 0.4339 0.7283
0.500 0.5001 0.01586 0.00740 -0.0627 0.4270 1.0000
0.750 0.5286 0.01610 0.00739 -0.0626 0.4214 1.0000
1.000 0.5570 0.01635 0.00748 -0.0627 0.4148 1.0000
1.250 0.5852 0.01659 0.00750 -0.0626 0.4092 1.0000
1.500 0.6132 0.01686 0.00759 -0.0626 0.4036 1.0000
1.750 0.6413 0.01714 0.00775 -0.0626 0.3975 1.0000
2.000 0.6691 0.01741 0.00785 -0.0625 0.3925 1.0000
2.250 0.6969 0.01773 0.00801 -0.0624 0.3880 1.0000
2.500 0.7246 0.01806 0.00828 -0.0624 0.3826 1.0000
2.750 0.7521 0.01836 0.00846 -0.0623 0.3778 1.0000
3.000 0.7796 0.01867 0.00860 -0.0621 0.3739 1.0000
3.250 0.8068 0.01905 0.00896 -0.0621 0.3688 1.0000
3.500 0.8340 0.01941 0.00927 -0.0620 0.3641 1.0000
3.750 0.8612 0.01976 0.00952 -0.0619 0.3604 1.0000
4.000 0.8883 0.02013 0.00975 -0.0618 0.3572 1.0000
4.250 0.9149 0.02058 0.01024 -0.0617 0.3527 1.0000
4.500 0.9414 0.02100 0.01065 -0.0616 0.3484 1.0000
4.750 0.9680 0.02138 0.01098 -0.0615 0.3446 1.0000
5.000 0.9948 0.02176 0.01126 -0.0614 0.3416 1.0000
5.250 1.0207 0.02228 0.01181 -0.0613 0.3381 1.0000
5.500 1.0463 0.02281 0.01239 -0.0612 0.3343 1.0000
5.750 1.0720 0.02329 0.01288 -0.0610 0.3307 1.0000
6.000 1.0981 0.02371 0.01325 -0.0608 0.3275 1.0000
6.250 1.1244 0.02414 0.01358 -0.0607 0.3249 1.0000
6.500 1.1482 0.02481 0.01441 -0.0605 0.3212 1.0000
6.750 1.1724 0.02545 0.01514 -0.0603 0.3178 1.0000
7.000 1.1969 0.02601 0.01573 -0.0601 0.3146 1.0000
7.250 1.2221 0.02649 0.01621 -0.0599 0.3117 1.0000
7.500 1.2479 0.02695 0.01659 -0.0597 0.3093 1.0000
7.750 1.2695 0.02777 0.01758 -0.0594 0.3059 1.0000
8.000 1.2910 0.02860 0.01856 -0.0590 0.3027 1.0000
8.250 1.3132 0.02931 0.01935 -0.0587 0.2996 1.0000
8.500 1.3367 0.02989 0.01996 -0.0584 0.2968 1.0000
8.750 1.3615 0.03038 0.02042 -0.0581 0.2944 1.0000
9.000 1.3825 0.03120 0.02134 -0.0577 0.2917 1.0000
9.250 1.3982 0.03239 0.02276 -0.0571 0.2884 1.0000
9.500 1.4155 0.03341 0.02392 -0.0565 0.2853 1.0000
9.750 1.4350 0.03420 0.02481 -0.0559 0.2825 1.0000
10.000 1.4573 0.03478 0.02540 -0.0555 0.2800 1.0000
10.250 1.4824 0.03525 0.02584 -0.0553 0.2779 1.0000
10.500 1.4876 0.03702 0.02790 -0.0540 0.2747 1.0000
10.750 1.4916 0.03877 0.02989 -0.0527 0.2715 1.0000
11.000 1.4987 0.04020 0.03147 -0.0515 0.2686 1.0000
11.250 1.5115 0.04115 0.03248 -0.0505 0.2660 1.0000
11.500 1.5330 0.04166 0.03301 -0.0500 0.2639 1.0000
11.750 1.5443 0.04282 0.03424 -0.0490 0.2617 1.0000
12.000 1.4837 0.04912 0.04093 -0.0469 0.2580 1.0000
12.250 1.3832 0.06255 0.05468 -0.0504 0.2516 1.0000
12.500 1.4090 0.06225 0.05441 -0.0495 0.2498 1.0000
12.750 1.4516 0.06000 0.05217 -0.0479 0.2486 1.0000
16.250 1.1252 0.17061 0.16392 -0.0978 0.1616 1.0000
16.500 1.1298 0.17397 0.16734 -0.0995 0.1577 1.0000
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Polar data table (+)
Polar graphs
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