MH 122 9.32% (mh122-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 122 9.32% (mh122-il) Reynolds number: 100,000 Max Cl/Cd: 61.08 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh122-il-100000.txt Download as CSV file: xf-mh122-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 122 9.32%
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4660 0.10446 0.10014 -0.0328 1.0000 0.0727
-7.750 -0.4847 0.10303 0.09880 -0.0315 1.0000 0.0728
-7.500 -0.5037 0.10072 0.09658 -0.0329 1.0000 0.0730
-7.250 -0.4795 0.09584 0.09161 -0.0261 1.0000 0.0760
-7.000 -0.4862 0.09382 0.08964 -0.0237 1.0000 0.0777
-6.750 -0.4948 0.09153 0.08740 -0.0226 1.0000 0.0793
-6.500 -0.5029 0.08851 0.08444 -0.0234 1.0000 0.0819
-6.000 -0.5144 0.07723 0.07302 -0.0407 1.0000 0.0871
-5.750 -0.5085 0.07558 0.07155 -0.0332 1.0000 0.0899
-5.500 -0.5023 0.07215 0.06809 -0.0342 1.0000 0.0948
-5.250 -0.4922 0.06597 0.06170 -0.0418 1.0000 0.1022
-5.000 -0.4816 0.06327 0.05902 -0.0409 1.0000 0.1077
-4.750 -0.4658 0.05866 0.05426 -0.0447 1.0000 0.1183
-4.500 -0.4478 0.05481 0.05026 -0.0473 1.0000 0.1319
-3.750 -0.3210 0.03550 0.02832 -0.0611 1.0000 0.0447
-3.500 -0.2898 0.03194 0.02431 -0.0623 1.0000 0.0397
-3.250 -0.2594 0.02962 0.02148 -0.0628 1.0000 0.0395
-3.000 -0.2313 0.02812 0.01959 -0.0629 1.0000 0.0431
-2.750 -0.2032 0.02664 0.01777 -0.0628 1.0000 0.0444
-2.500 -0.1749 0.02526 0.01612 -0.0623 1.0000 0.0462
-2.250 -0.1463 0.02355 0.01442 -0.0624 1.0000 0.0506
-2.000 -0.1176 0.02260 0.01350 -0.0627 1.0000 0.0722
-1.750 -0.0815 0.01983 0.01322 -0.0640 1.0000 0.6215
-1.500 -0.0661 0.02010 0.01354 -0.0610 1.0000 0.6887
-1.250 -0.0507 0.02031 0.01375 -0.0582 1.0000 0.7383
-1.000 -0.0393 0.02043 0.01395 -0.0543 1.0000 0.7911
-0.750 -0.0287 0.02043 0.01401 -0.0504 1.0000 0.8409
-0.500 -0.0140 0.02033 0.01394 -0.0479 1.0000 0.8902
-0.250 0.0093 0.01994 0.01347 -0.0487 1.0000 1.0000
0.000 0.0443 0.02043 0.01367 -0.0521 1.0000 1.0000
0.250 0.0825 0.02113 0.01410 -0.0557 0.9966 1.0000
0.500 0.1257 0.02198 0.01472 -0.0600 0.9892 1.0000
0.750 0.1694 0.02297 0.01548 -0.0641 0.9829 1.0000
1.000 0.2040 0.02351 0.01590 -0.0665 0.9747 1.0000
1.250 0.2426 0.02427 0.01655 -0.0695 0.9674 1.0000
1.500 0.2787 0.02489 0.01709 -0.0720 0.9596 1.0000
1.750 0.3116 0.02544 0.01758 -0.0738 0.9508 1.0000
2.000 0.3515 0.02614 0.01825 -0.0768 0.9433 1.0000
2.250 0.3853 0.02664 0.01873 -0.0787 0.9339 1.0000
2.500 0.4176 0.02712 0.01925 -0.0802 0.9240 1.0000
2.750 0.4550 0.02763 0.01978 -0.0825 0.9145 1.0000
3.000 0.4981 0.02810 0.02030 -0.0857 0.9059 1.0000
3.250 0.5310 0.02841 0.02068 -0.0870 0.8942 1.0000
3.500 0.5669 0.02866 0.02102 -0.0887 0.8823 1.0000
3.750 0.6053 0.02877 0.02132 -0.0906 0.8699 1.0000
4.000 0.6473 0.02865 0.02136 -0.0927 0.8569 1.0000
4.250 0.6958 0.02806 0.02096 -0.0954 0.8426 1.0000
4.500 0.7560 0.02659 0.01982 -0.0989 0.8273 1.0000
4.750 0.8204 0.02445 0.01801 -0.1025 0.8125 1.0000
5.000 0.8612 0.02291 0.01676 -0.1025 0.7930 1.0000
5.250 0.9233 0.01992 0.01426 -0.1046 0.7702 1.0000
5.500 0.9540 0.01822 0.01282 -0.1021 0.7313 1.0000
5.750 1.0029 0.01642 0.01026 -0.1010 0.5105 1.0000
6.000 0.9939 0.01901 0.01122 -0.0943 0.2852 1.0000
6.250 0.9939 0.02141 0.01269 -0.0898 0.1832 1.0000
6.500 1.0031 0.02331 0.01417 -0.0868 0.1395 1.0000
6.750 1.0205 0.02541 0.01601 -0.0851 0.1119 1.0000
7.000 1.0415 0.02713 0.01768 -0.0840 0.0888 1.0000
7.250 1.0779 0.03018 0.02067 -0.0852 0.0715 1.0000
7.500 1.1067 0.03277 0.02344 -0.0851 0.0572 1.0000
7.750 1.1317 0.03565 0.02663 -0.0845 0.0460 1.0000
8.000 1.1579 0.03899 0.03034 -0.0835 0.0401 1.0000
8.250 1.1766 0.04407 0.03576 -0.0824 0.0363 1.0000
8.500 1.1856 0.04642 0.03878 -0.0788 0.0334 1.0000
8.750 1.1928 0.05043 0.04333 -0.0755 0.0325 1.0000
9.000 1.1944 0.05488 0.04829 -0.0719 0.0329 1.0000
9.250 1.1914 0.05936 0.05320 -0.0681 0.0336 1.0000
9.500 1.1844 0.06380 0.05800 -0.0643 0.0343 1.0000
9.750 1.1743 0.06809 0.06256 -0.0607 0.0350 1.0000
10.000 1.1614 0.07242 0.06709 -0.0572 0.0357 1.0000
10.250 1.0612 0.07048 0.06573 -0.0454 0.0356 1.0000
10.500 1.0528 0.07842 0.07373 -0.0448 0.0369 1.0000
10.750 1.0336 0.08115 0.07669 -0.0424 0.0373 1.0000
11.000 1.0062 0.08508 0.08090 -0.0412 0.0379 1.0000
11.250 0.9724 0.09070 0.08676 -0.0417 0.0383 1.0000
11.500 0.9335 0.09762 0.09391 -0.0446 0.0388 1.0000
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Polar data table (+)
Polar graphs
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