MH 116 9.84% (mh116-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 116 9.84% (mh116-il) Reynolds number: 100,000 Max Cl/Cd: 63.03 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh116-il-100000-n5.txt Download as CSV file: xf-mh116-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 116 9.84%
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3482 0.09225 0.08768 -0.0390 1.0000 0.0184
-8.000 -0.3596 0.09025 0.08578 -0.0371 1.0000 0.0182
-7.750 -0.3708 0.08801 0.08363 -0.0357 0.9993 0.0179
-7.500 -0.3601 0.08296 0.07861 -0.0416 0.9919 0.0174
-7.250 -0.3488 0.07740 0.07307 -0.0486 0.9833 0.0169
-7.000 -0.3353 0.07051 0.06618 -0.0578 0.9730 0.0165
-6.750 -0.3202 0.06163 0.05725 -0.0695 0.9628 0.0158
-6.500 -0.3047 0.04617 0.04127 -0.0857 0.9523 0.0147
-6.250 -0.2811 0.03867 0.03304 -0.0927 0.9451 0.0144
-6.000 -0.2560 0.03398 0.02773 -0.0961 0.9388 0.0146
-5.750 -0.2280 0.03062 0.02385 -0.0984 0.9332 0.0152
-5.500 -0.1939 0.02841 0.02123 -0.1010 0.9299 0.0169
-5.250 -0.1671 0.02648 0.01883 -0.1016 0.9233 0.0191
-5.000 -0.1343 0.02448 0.01635 -0.1028 0.9191 0.0212
-4.750 -0.0996 0.02253 0.01421 -0.1047 0.9161 0.0241
-4.500 -0.0724 0.02142 0.01286 -0.1047 0.9095 0.0289
-4.250 -0.0401 0.02021 0.01152 -0.1057 0.9050 0.0400
-4.000 -0.0048 0.01918 0.01048 -0.1075 0.9018 0.0638
-3.750 0.0210 0.01850 0.00978 -0.1073 0.8944 0.0887
-3.500 0.0541 0.01787 0.00914 -0.1084 0.8901 0.1214
-3.250 0.0851 0.01738 0.00870 -0.1093 0.8851 0.1572
-3.000 0.1134 0.01699 0.00835 -0.1095 0.8786 0.1944
-2.750 0.1470 0.01655 0.00796 -0.1106 0.8747 0.2399
-2.500 0.1731 0.01629 0.00775 -0.1104 0.8675 0.2858
-2.250 0.2042 0.01593 0.00750 -0.1111 0.8625 0.3433
-2.000 0.2329 0.01562 0.00733 -0.1113 0.8568 0.4069
-1.750 0.2598 0.01535 0.00723 -0.1110 0.8503 0.4793
-1.500 0.2910 0.01496 0.00704 -0.1113 0.8461 0.5688
-1.250 0.3121 0.01477 0.00709 -0.1097 0.8381 0.6575
-1.000 0.3373 0.01443 0.00698 -0.1083 0.8331 0.7619
-0.750 0.3604 0.01423 0.00693 -0.1065 0.8259 0.8820
-0.500 0.4038 0.01405 0.00663 -0.1094 0.8209 1.0000
-0.250 0.4319 0.01413 0.00656 -0.1095 0.8141 1.0000
0.000 0.4608 0.01419 0.00648 -0.1097 0.8074 1.0000
0.250 0.4891 0.01428 0.00644 -0.1098 0.8007 1.0000
0.500 0.5173 0.01435 0.00641 -0.1099 0.7936 1.0000
0.750 0.5451 0.01445 0.00642 -0.1098 0.7864 1.0000
1.000 0.5735 0.01452 0.00643 -0.1098 0.7792 1.0000
1.250 0.6002 0.01464 0.00648 -0.1096 0.7712 1.0000
1.500 0.6296 0.01468 0.00646 -0.1097 0.7641 1.0000
1.750 0.6550 0.01482 0.00658 -0.1093 0.7550 1.0000
2.000 0.6846 0.01485 0.00658 -0.1094 0.7477 1.0000
2.250 0.7101 0.01499 0.00671 -0.1089 0.7381 1.0000
2.500 0.7365 0.01511 0.00682 -0.1085 0.7289 1.0000
2.750 0.7659 0.01514 0.00682 -0.1086 0.7208 1.0000
3.000 0.7907 0.01529 0.00700 -0.1079 0.7100 1.0000
3.250 0.8164 0.01542 0.00719 -0.1074 0.6994 1.0000
3.500 0.8430 0.01552 0.00730 -0.1070 0.6889 1.0000
3.750 0.8701 0.01561 0.00740 -0.1067 0.6781 1.0000
4.000 0.8961 0.01572 0.00758 -0.1061 0.6660 1.0000
4.250 0.9210 0.01586 0.00777 -0.1054 0.6527 1.0000
4.500 0.9461 0.01599 0.00794 -0.1047 0.6385 1.0000
4.750 0.9709 0.01612 0.00813 -0.1040 0.6232 1.0000
5.000 0.9943 0.01631 0.00837 -0.1030 0.6057 1.0000
5.250 1.0179 0.01648 0.00864 -0.1020 0.5870 1.0000
5.500 1.0414 0.01667 0.00886 -0.1009 0.5668 1.0000
5.750 1.0633 0.01692 0.00915 -0.0997 0.5438 1.0000
6.000 1.0847 0.01721 0.00946 -0.0984 0.5182 1.0000
6.250 1.1053 0.01755 0.00979 -0.0969 0.4895 1.0000
6.500 1.1245 0.01798 0.01021 -0.0953 0.4573 1.0000
6.750 1.1422 0.01851 0.01068 -0.0934 0.4217 1.0000
7.000 1.1580 0.01917 0.01121 -0.0914 0.3844 1.0000
7.250 1.1724 0.01993 0.01186 -0.0892 0.3475 1.0000
7.500 1.1856 0.02078 0.01260 -0.0869 0.3113 1.0000
7.750 1.1976 0.02171 0.01342 -0.0845 0.2774 1.0000
8.000 1.2085 0.02270 0.01431 -0.0821 0.2447 1.0000
8.250 1.2180 0.02371 0.01530 -0.0795 0.2157 1.0000
8.500 1.2263 0.02480 0.01632 -0.0768 0.1887 1.0000
8.750 1.2342 0.02597 0.01742 -0.0741 0.1647 1.0000
9.000 1.2418 0.02722 0.01861 -0.0716 0.1413 1.0000
9.250 1.2494 0.02852 0.01988 -0.0693 0.1201 1.0000
9.500 1.2553 0.02998 0.02127 -0.0669 0.1008 1.0000
9.750 1.2623 0.03145 0.02274 -0.0647 0.0838 1.0000
10.000 1.2680 0.03306 0.02438 -0.0626 0.0691 1.0000
10.250 1.2721 0.03487 0.02619 -0.0604 0.0558 1.0000
10.500 1.2744 0.03691 0.02826 -0.0583 0.0461 1.0000
10.750 1.2749 0.03918 0.03054 -0.0562 0.0383 1.0000
11.000 1.2767 0.04142 0.03293 -0.0545 0.0313 1.0000
11.250 1.2762 0.04397 0.03560 -0.0527 0.0270 1.0000
11.500 1.2773 0.04643 0.03819 -0.0513 0.0229 1.0000
11.750 1.2717 0.04970 0.04153 -0.0499 0.0207 1.0000
12.000 1.2723 0.05250 0.04457 -0.0488 0.0184 1.0000
12.250 1.2721 0.05539 0.04763 -0.0480 0.0165 1.0000
12.500 1.2689 0.05868 0.05104 -0.0476 0.0149 1.0000
12.750 1.2616 0.06265 0.05512 -0.0472 0.0139 1.0000
13.000 1.2604 0.06613 0.05886 -0.0469 0.0131 1.0000
13.250 1.2575 0.06994 0.06291 -0.0467 0.0125 1.0000
13.500 1.2536 0.07403 0.06723 -0.0469 0.0119 1.0000
13.750 1.2483 0.07843 0.07187 -0.0473 0.0115 1.0000
14.000 1.2422 0.08308 0.07675 -0.0482 0.0112 1.0000
14.250 1.2345 0.08814 0.08204 -0.0496 0.0109 1.0000
14.500 1.2258 0.09355 0.08767 -0.0514 0.0106 1.0000
14.750 1.2157 0.09939 0.09373 -0.0538 0.0104 1.0000
15.000 1.2045 0.10572 0.10027 -0.0567 0.0103 1.0000
15.250 1.1926 0.11246 0.10721 -0.0602 0.0101 1.0000
15.500 1.1792 0.11997 0.11495 -0.0643 0.0102 1.0000
15.750 1.1642 0.12828 0.12348 -0.0692 0.0103 1.0000
16.000 1.1471 0.13772 0.13314 -0.0750 0.0105 1.0000
16.250 1.1283 0.14836 0.14398 -0.0818 0.0109 1.0000
16.500 1.1086 0.16016 0.15593 -0.0893 0.0113 1.0000
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Polar data table (+)
Polar graphs
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