MH 83 13.29% (mh83-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 83 13.29% (mh83-il) Reynolds number: 100,000 Max Cl/Cd: 34.06 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh83-il-100000.txt Download as CSV file: xf-mh83-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2550 0.11849 0.11442 -0.0068 1.0000 0.0805
-9.500 -0.2600 0.11720 0.11323 -0.0120 1.0000 0.0828
-9.250 -0.2693 0.11623 0.11240 -0.0189 1.0000 0.0834
-9.000 -0.2284 0.10865 0.10486 -0.0146 1.0000 0.0864
-8.750 -0.2127 0.10544 0.10174 -0.0170 1.0000 0.0898
-8.500 -0.2003 0.10257 0.09891 -0.0245 0.9526 0.0943
-8.250 -0.2056 0.10059 0.09690 -0.0357 0.9083 0.0961
-8.000 -0.1758 0.09534 0.09152 -0.0300 0.8815 0.0983
-7.750 -0.1662 0.09293 0.08903 -0.0285 0.8562 0.1008
-7.500 -0.1616 0.09071 0.08675 -0.0284 0.8343 0.1041
-7.250 -0.1699 0.08930 0.08533 -0.0316 0.8153 0.1084
-7.000 -0.1904 0.08801 0.08406 -0.0414 0.7992 0.1099
-6.750 -0.1646 0.08347 0.07945 -0.0324 0.7838 0.1120
-6.500 -0.1508 0.08085 0.07677 -0.0306 0.7689 0.1152
-6.250 -0.1461 0.07863 0.07448 -0.0314 0.7560 0.1192
-6.000 -0.1508 0.07499 0.07082 -0.0454 0.7437 0.1255
-5.750 -0.1350 0.07225 0.06806 -0.0397 0.7303 0.1275
-5.500 -0.1210 0.06988 0.06562 -0.0383 0.7187 0.1315
-5.250 -0.1102 0.06551 0.06112 -0.0503 0.7076 0.1418
-5.000 -0.0948 0.06313 0.05875 -0.0466 0.6953 0.1445
-4.750 -0.0784 0.06067 0.05616 -0.0472 0.6853 0.1515
-4.500 -0.0604 0.05719 0.05262 -0.0511 0.6732 0.1615
-4.250 -0.0344 0.04111 0.03675 -0.0472 0.6442 0.1767
-4.000 0.0066 0.03722 0.03100 -0.0716 0.6587 0.0859
-3.750 0.0349 0.03286 0.02593 -0.0726 0.6502 0.0768
-3.500 0.0666 0.02949 0.02157 -0.0734 0.6387 0.0720
-3.250 0.0945 0.02753 0.01915 -0.0730 0.6294 0.0719
-3.000 0.1233 0.02586 0.01712 -0.0729 0.6179 0.0730
-2.750 0.1506 0.02481 0.01603 -0.0726 0.6072 0.0775
-2.500 0.1791 0.02385 0.01471 -0.0720 0.5978 0.0825
-2.250 0.2073 0.02278 0.01365 -0.0717 0.5867 0.0880
-2.000 0.2349 0.02192 0.01263 -0.0709 0.5787 0.0992
-1.750 0.2632 0.02119 0.01200 -0.0707 0.5673 0.1233
-1.500 0.2903 0.02020 0.01130 -0.0702 0.5595 0.1957
-1.250 0.3176 0.01981 0.01128 -0.0702 0.5492 0.2876
-1.000 0.3439 0.01942 0.01114 -0.0696 0.5417 0.3845
-0.750 0.3691 0.01903 0.01119 -0.0688 0.5319 0.4958
-0.500 0.3914 0.01848 0.01107 -0.0667 0.5255 0.6536
-0.250 0.4212 0.01780 0.01098 -0.0656 0.5154 1.0000
0.000 0.4508 0.01804 0.01075 -0.0656 0.5092 1.0000
0.250 0.4796 0.01850 0.01105 -0.0660 0.5001 1.0000
0.500 0.5083 0.01875 0.01099 -0.0658 0.4936 1.0000
0.750 0.5364 0.01922 0.01129 -0.0660 0.4858 1.0000
1.000 0.5646 0.01955 0.01141 -0.0659 0.4788 1.0000
1.250 0.5928 0.01992 0.01152 -0.0657 0.4734 1.0000
1.500 0.6202 0.02051 0.01209 -0.0659 0.4659 1.0000
1.750 0.6482 0.02086 0.01225 -0.0658 0.4604 1.0000
2.000 0.6757 0.02137 0.01262 -0.0657 0.4549 1.0000
2.250 0.7026 0.02197 0.01320 -0.0658 0.4480 1.0000
2.500 0.7304 0.02232 0.01337 -0.0656 0.4431 1.0000
2.750 0.7575 0.02294 0.01390 -0.0656 0.4384 1.0000
3.000 0.7833 0.02376 0.01477 -0.0657 0.4324 1.0000
3.250 0.8104 0.02423 0.01514 -0.0656 0.4276 1.0000
3.500 0.8385 0.02462 0.01533 -0.0653 0.4240 1.0000
3.750 0.8620 0.02573 0.01660 -0.0655 0.4178 1.0000
4.000 0.8878 0.02644 0.01730 -0.0655 0.4130 1.0000
4.250 0.9150 0.02695 0.01770 -0.0653 0.4094 1.0000
4.500 0.9415 0.02765 0.01831 -0.0652 0.4060 1.0000
4.750 0.9617 0.02916 0.02006 -0.0653 0.4001 1.0000
5.000 0.9868 0.02988 0.02077 -0.0652 0.3957 1.0000
5.250 1.0140 0.03032 0.02112 -0.0649 0.3924 1.0000
5.500 1.0391 0.03124 0.02198 -0.0648 0.3893 1.0000
5.750 1.0521 0.03364 0.02474 -0.0649 0.3836 1.0000
6.000 1.0742 0.03470 0.02584 -0.0647 0.3794 1.0000
6.250 1.1020 0.03502 0.02606 -0.0644 0.3764 1.0000
6.500 1.1312 0.03535 0.02625 -0.0641 0.3738 1.0000
6.750 1.1224 0.04026 0.03171 -0.0642 0.3675 1.0000
7.000 1.1321 0.04268 0.03428 -0.0640 0.3631 1.0000
7.250 1.1620 0.04268 0.03420 -0.0635 0.3604 1.0000
7.500 1.1977 0.04216 0.03355 -0.0631 0.3582 1.0000
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Polar data table (+)
Polar graphs
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