MH 117 9.8% (mh117-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 117 9.8% (mh117-il) Reynolds number: 500,000 Max Cl/Cd: 90.42 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh117-il-500000-n5.txt Download as CSV file: xf-mh117-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5846 0.08378 0.08132 -0.0322 1.0000 0.0033
-11.250 -0.6203 0.07305 0.07059 -0.0380 1.0000 0.0032
-11.000 -0.6506 0.06375 0.06126 -0.0434 1.0000 0.0030
-10.750 -0.6889 0.05261 0.05006 -0.0506 1.0000 0.0030
-10.500 -0.7197 0.04076 0.03803 -0.0623 1.0000 0.0028
-10.250 -0.7342 0.03574 0.03273 -0.0642 1.0000 0.0028
-10.000 -0.7391 0.03206 0.02875 -0.0639 1.0000 0.0028
-9.750 -0.7363 0.02926 0.02568 -0.0628 1.0000 0.0029
-9.500 -0.7296 0.02692 0.02306 -0.0615 1.0000 0.0030
-9.250 -0.7081 0.02458 0.02041 -0.0626 0.9973 0.0031
-9.000 -0.6800 0.02251 0.01804 -0.0646 0.9932 0.0032
-8.750 -0.6519 0.02102 0.01628 -0.0659 0.9883 0.0034
-8.500 -0.6221 0.01959 0.01463 -0.0674 0.9839 0.0035
-8.250 -0.5942 0.01809 0.01293 -0.0684 0.9781 0.0036
-8.000 -0.5650 0.01682 0.01149 -0.0696 0.9719 0.0039
-7.750 -0.5348 0.01589 0.01043 -0.0706 0.9655 0.0041
-7.500 -0.5039 0.01511 0.00954 -0.0716 0.9580 0.0043
-7.250 -0.4729 0.01438 0.00868 -0.0726 0.9498 0.0045
-7.000 -0.4407 0.01374 0.00792 -0.0738 0.9413 0.0049
-6.750 -0.4105 0.01322 0.00729 -0.0744 0.9301 0.0054
-6.500 -0.3816 0.01257 0.00652 -0.0748 0.9180 0.0061
-6.250 -0.3539 0.01204 0.00587 -0.0749 0.9050 0.0068
-6.000 -0.3268 0.01160 0.00531 -0.0747 0.8919 0.0076
-5.750 -0.3002 0.01117 0.00474 -0.0743 0.8788 0.0092
-5.500 -0.2739 0.01075 0.00425 -0.0740 0.8664 0.0130
-5.250 -0.2478 0.01034 0.00382 -0.0737 0.8542 0.0225
-5.000 -0.2215 0.00999 0.00350 -0.0734 0.8425 0.0372
-4.750 -0.1950 0.00971 0.00324 -0.0732 0.8312 0.0529
-4.500 -0.1681 0.00949 0.00302 -0.0729 0.8204 0.0665
-4.250 -0.1412 0.00930 0.00280 -0.0727 0.8101 0.0802
-4.000 -0.1142 0.00913 0.00261 -0.0725 0.7998 0.0935
-3.750 -0.0869 0.00897 0.00242 -0.0724 0.7897 0.1048
-3.500 -0.0596 0.00882 0.00226 -0.0722 0.7802 0.1189
-3.000 -0.0049 0.00855 0.00196 -0.0719 0.7613 0.1510
-2.750 0.0224 0.00842 0.00184 -0.0718 0.7523 0.1706
-2.500 0.0498 0.00831 0.00174 -0.0716 0.7433 0.1897
-2.250 0.0774 0.00819 0.00164 -0.0715 0.7342 0.2124
-2.000 0.1048 0.00807 0.00156 -0.0714 0.7257 0.2388
-1.750 0.1323 0.00797 0.00149 -0.0713 0.7165 0.2641
-1.500 0.1597 0.00786 0.00143 -0.0712 0.7075 0.2948
-1.250 0.1871 0.00777 0.00138 -0.0711 0.6982 0.3250
-1.000 0.2144 0.00766 0.00134 -0.0709 0.6882 0.3607
-0.750 0.2417 0.00755 0.00132 -0.0708 0.6783 0.4015
-0.500 0.2689 0.00745 0.00130 -0.0707 0.6685 0.4443
-0.250 0.2960 0.00735 0.00130 -0.0705 0.6584 0.4908
0.000 0.3230 0.00723 0.00131 -0.0703 0.6481 0.5425
0.250 0.3498 0.00712 0.00134 -0.0701 0.6380 0.5961
0.500 0.3763 0.00702 0.00137 -0.0697 0.6277 0.6529
1.000 0.4277 0.00680 0.00148 -0.0685 0.6055 0.7719
1.250 0.4520 0.00671 0.00154 -0.0675 0.5941 0.8324
1.500 0.4753 0.00666 0.00160 -0.0662 0.5823 0.8925
1.750 0.5060 0.00666 0.00163 -0.0665 0.5691 0.9491
2.000 0.5452 0.00673 0.00166 -0.0689 0.5532 0.9932
2.250 0.5734 0.00685 0.00171 -0.0690 0.5378 1.0000
2.500 0.5996 0.00698 0.00178 -0.0686 0.5211 1.0000
2.750 0.6257 0.00714 0.00186 -0.0683 0.5029 1.0000
3.000 0.6518 0.00731 0.00197 -0.0679 0.4827 1.0000
3.250 0.6774 0.00752 0.00208 -0.0675 0.4584 1.0000
3.750 0.7279 0.00805 0.00239 -0.0666 0.4012 1.0000
4.000 0.7525 0.00838 0.00258 -0.0660 0.3668 1.0000
4.250 0.7769 0.00875 0.00279 -0.0655 0.3339 1.0000
4.500 0.8014 0.00912 0.00303 -0.0650 0.3030 1.0000
4.750 0.8257 0.00951 0.00329 -0.0644 0.2714 1.0000
5.000 0.8501 0.00989 0.00356 -0.0639 0.2431 1.0000
5.500 0.8990 0.01062 0.00411 -0.0629 0.1977 1.0000
5.750 0.9230 0.01103 0.00443 -0.0624 0.1745 1.0000
6.000 0.9473 0.01141 0.00475 -0.0619 0.1563 1.0000
6.250 0.9710 0.01183 0.00510 -0.0613 0.1379 1.0000
6.500 0.9947 0.01225 0.00545 -0.0607 0.1203 1.0000
6.750 1.0183 0.01267 0.00582 -0.0601 0.1056 1.0000
7.000 1.0415 0.01311 0.00622 -0.0594 0.0915 1.0000
7.250 1.0645 0.01356 0.00665 -0.0588 0.0795 1.0000
7.500 1.0873 0.01402 0.00708 -0.0580 0.0695 1.0000
7.750 1.1096 0.01451 0.00754 -0.0573 0.0603 1.0000
8.000 1.1325 0.01493 0.00799 -0.0566 0.0543 1.0000
8.250 1.1543 0.01544 0.00850 -0.0557 0.0482 1.0000
8.500 1.1763 0.01591 0.00899 -0.0549 0.0427 1.0000
8.750 1.1971 0.01646 0.00956 -0.0540 0.0368 1.0000
9.000 1.2179 0.01699 0.01010 -0.0530 0.0316 1.0000
9.250 1.2377 0.01757 0.01068 -0.0519 0.0267 1.0000
9.500 1.2569 0.01818 0.01129 -0.0508 0.0221 1.0000
9.750 1.2755 0.01881 0.01194 -0.0496 0.0183 1.0000
10.000 1.2926 0.01952 0.01265 -0.0482 0.0146 1.0000
10.250 1.3095 0.02019 0.01338 -0.0467 0.0120 1.0000
10.500 1.3233 0.02099 0.01419 -0.0449 0.0095 1.0000
10.750 1.3354 0.02175 0.01502 -0.0427 0.0072 1.0000
11.000 1.3456 0.02265 0.01597 -0.0403 0.0057 1.0000
11.250 1.3551 0.02359 0.01697 -0.0380 0.0045 1.0000
11.500 1.3637 0.02463 0.01807 -0.0357 0.0037 1.0000
11.750 1.3728 0.02567 0.01922 -0.0337 0.0032 1.0000
12.000 1.3807 0.02684 0.02047 -0.0318 0.0028 1.0000
12.250 1.3858 0.02828 0.02202 -0.0298 0.0025 1.0000
12.500 1.3910 0.02977 0.02362 -0.0280 0.0023 1.0000
12.750 1.3969 0.03128 0.02524 -0.0265 0.0022 1.0000
13.000 1.4018 0.03295 0.02703 -0.0252 0.0021 1.0000
13.250 1.4049 0.03488 0.02909 -0.0239 0.0019 1.0000
13.500 1.4076 0.03692 0.03128 -0.0230 0.0019 1.0000
13.750 1.4088 0.03923 0.03373 -0.0222 0.0018 1.0000
14.000 1.4099 0.04164 0.03626 -0.0217 0.0017 1.0000
14.250 1.4086 0.04446 0.03921 -0.0214 0.0017 1.0000
14.500 1.4061 0.04751 0.04241 -0.0214 0.0016 1.0000
14.750 1.4021 0.05093 0.04597 -0.0217 0.0015 1.0000
15.000 1.3982 0.05447 0.04964 -0.0223 0.0015 1.0000
15.250 1.3902 0.05875 0.05407 -0.0234 0.0015 1.0000
15.500 1.3823 0.06327 0.05875 -0.0248 0.0015 1.0000
15.750 1.3721 0.06838 0.06401 -0.0268 0.0014 1.0000
16.000 1.3611 0.07393 0.06970 -0.0291 0.0014 1.0000
16.250 1.3459 0.08053 0.07647 -0.0322 0.0014 1.0000
16.500 1.3316 0.08729 0.08340 -0.0356 0.0014 1.0000
16.750 1.3121 0.09546 0.09174 -0.0400 0.0013 1.0000
17.000 1.2944 0.10358 0.10002 -0.0444 0.0014 1.0000
17.250 1.2742 0.11254 0.10914 -0.0494 0.0014 1.0000
17.500 1.2546 0.12160 0.11836 -0.0545 0.0014 1.0000
17.750 1.2308 0.13189 0.12880 -0.0604 0.0014 1.0000
18.000 1.2089 0.14203 0.13909 -0.0663 0.0015 1.0000
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Polar data table (+)
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