MH 61 10.26% (mh61-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 61 10.26% (mh61-il) Reynolds number: 100,000 Max Cl/Cd: 47.62 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh61-il-100000.txt Download as CSV file: xf-mh61-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 61 10.26%
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5672 0.12556 0.12116 0.0205 1.0000 0.0860
-10.250 -0.5784 0.12197 0.11765 0.0148 1.0000 0.0894
-10.000 -0.5995 0.11816 0.11401 0.0066 1.0000 0.0902
-9.750 -0.5603 0.11295 0.10868 0.0138 1.0000 0.0942
-9.500 -0.5549 0.10919 0.10494 0.0123 1.0000 0.0983
-9.250 -0.5775 0.10505 0.10092 0.0037 1.0000 0.1030
-9.000 -0.5666 0.10000 0.09591 0.0041 1.0000 0.1052
-8.750 -0.5513 0.09653 0.09244 0.0052 1.0000 0.1092
-8.250 -0.4817 0.08065 0.07702 -0.0077 1.0000 0.1292
-6.750 -0.5741 0.04469 0.03910 -0.0282 1.0000 0.0495
-6.500 -0.5619 0.03999 0.03413 -0.0278 1.0000 0.0450
-6.250 -0.5538 0.03783 0.03104 -0.0244 1.0000 0.0391
-6.000 -0.5503 0.03481 0.02787 -0.0215 1.0000 0.0378
-5.750 -0.5463 0.03236 0.02513 -0.0183 1.0000 0.0370
-5.500 -0.5384 0.03025 0.02273 -0.0155 1.0000 0.0363
-5.250 -0.5275 0.02862 0.02074 -0.0129 1.0000 0.0372
-5.000 -0.4951 0.02643 0.01807 -0.0139 0.9945 0.0395
-4.750 -0.4585 0.02358 0.01510 -0.0159 0.9880 0.0423
-4.500 -0.4174 0.02156 0.01298 -0.0181 0.9822 0.0466
-4.250 -0.3829 0.01990 0.01126 -0.0193 0.9744 0.0534
-4.000 -0.3496 0.01766 0.00937 -0.0206 0.9675 0.1065
-3.750 -0.3299 0.01551 0.00902 -0.0200 0.9586 0.4472
-3.500 -0.3005 0.01530 0.00905 -0.0201 0.9500 0.5431
-3.250 -0.2651 0.01506 0.00898 -0.0210 0.9430 0.6196
-3.000 -0.2370 0.01486 0.00892 -0.0205 0.9339 0.6835
-2.750 -0.2001 0.01470 0.00887 -0.0212 0.9272 0.7538
-2.500 -0.1590 0.01467 0.00885 -0.0226 0.9199 0.8236
-2.250 -0.0980 0.01482 0.00887 -0.0274 0.9158 0.8841
-2.000 -0.0352 0.01507 0.00890 -0.0331 0.9096 0.9236
-1.750 0.0327 0.01520 0.00875 -0.0400 0.9041 0.9519
-1.500 0.0980 0.01517 0.00852 -0.0471 0.8968 0.9784
-1.250 0.1571 0.01487 0.00805 -0.0536 0.8890 1.0000
-1.000 0.1700 0.01494 0.00799 -0.0518 0.8759 1.0000
-0.750 0.1850 0.01506 0.00801 -0.0501 0.8634 1.0000
-0.500 0.2014 0.01521 0.00806 -0.0484 0.8513 1.0000
-0.250 0.2185 0.01539 0.00816 -0.0468 0.8397 1.0000
0.000 0.2363 0.01557 0.00827 -0.0450 0.8284 1.0000
0.250 0.2542 0.01575 0.00837 -0.0431 0.8178 1.0000
0.500 0.2721 0.01590 0.00844 -0.0410 0.8076 1.0000
0.750 0.2923 0.01611 0.00860 -0.0397 0.7958 1.0000
1.000 0.3127 0.01631 0.00876 -0.0383 0.7844 1.0000
1.250 0.3331 0.01649 0.00893 -0.0367 0.7733 1.0000
1.500 0.3534 0.01663 0.00903 -0.0350 0.7628 1.0000
1.750 0.3734 0.01671 0.00906 -0.0329 0.7530 1.0000
2.000 0.3952 0.01687 0.00922 -0.0317 0.7409 1.0000
2.250 0.4172 0.01702 0.00937 -0.0304 0.7290 1.0000
2.500 0.4392 0.01715 0.00954 -0.0290 0.7171 1.0000
2.750 0.4613 0.01724 0.00964 -0.0275 0.7055 1.0000
3.000 0.4835 0.01728 0.00970 -0.0259 0.6941 1.0000
3.250 0.5057 0.01725 0.00967 -0.0241 0.6832 1.0000
3.500 0.5285 0.01724 0.00972 -0.0226 0.6711 1.0000
3.750 0.5518 0.01727 0.00979 -0.0213 0.6579 1.0000
4.000 0.5752 0.01726 0.00983 -0.0199 0.6444 1.0000
4.250 0.5987 0.01723 0.00983 -0.0185 0.6305 1.0000
4.500 0.6225 0.01720 0.00986 -0.0171 0.6152 1.0000
4.750 0.6464 0.01721 0.01001 -0.0160 0.5978 1.0000
5.000 0.6704 0.01713 0.00998 -0.0146 0.5804 1.0000
5.250 0.6944 0.01699 0.00985 -0.0130 0.5628 1.0000
5.500 0.7184 0.01701 0.00996 -0.0119 0.5409 1.0000
5.750 0.7425 0.01696 0.00993 -0.0105 0.5191 1.0000
6.000 0.7663 0.01697 0.00996 -0.0092 0.4942 1.0000
6.250 0.7897 0.01707 0.01012 -0.0081 0.4652 1.0000
6.500 0.8125 0.01725 0.01043 -0.0070 0.4311 1.0000
6.750 0.8343 0.01752 0.01071 -0.0058 0.3912 1.0000
7.000 0.8544 0.01798 0.01111 -0.0046 0.3417 1.0000
7.250 0.8715 0.01885 0.01179 -0.0034 0.2745 1.0000
7.500 0.8811 0.02072 0.01307 -0.0019 0.1794 1.0000
7.750 0.8862 0.02335 0.01507 0.0003 0.1162 1.0000
8.000 0.8949 0.02555 0.01705 0.0024 0.0834 1.0000
8.250 0.9058 0.02774 0.01907 0.0044 0.0664 1.0000
8.500 0.9193 0.02991 0.02116 0.0061 0.0536 1.0000
8.750 0.9390 0.03246 0.02386 0.0077 0.0460 1.0000
9.000 0.9556 0.03538 0.02677 0.0088 0.0391 1.0000
9.250 0.9745 0.03826 0.03003 0.0103 0.0368 1.0000
9.500 0.9891 0.04158 0.03384 0.0118 0.0356 1.0000
9.750 0.9974 0.04502 0.03769 0.0135 0.0345 1.0000
10.000 1.0020 0.04810 0.04109 0.0152 0.0333 1.0000
10.250 1.0061 0.05087 0.04403 0.0165 0.0316 1.0000
10.500 1.0035 0.05410 0.04751 0.0180 0.0311 1.0000
10.750 0.9943 0.05729 0.05095 0.0199 0.0308 1.0000
11.000 0.9828 0.06105 0.05484 0.0210 0.0299 1.0000
11.250 0.9676 0.06435 0.05842 0.0217 0.0304 1.0000
11.500 0.9462 0.06863 0.06301 0.0211 0.0312 1.0000
11.750 0.8992 0.07712 0.07196 0.0170 0.0354 1.0000
12.000 0.8769 0.08364 0.07863 0.0134 0.0365 1.0000
12.250 0.8545 0.09090 0.08600 0.0087 0.0371 1.0000
12.500 0.8342 0.09880 0.09396 0.0036 0.0380 1.0000
12.750 0.8173 0.10692 0.10202 -0.0011 0.0390 1.0000
13.000 0.8060 0.11439 0.10949 -0.0047 0.0398 1.0000
13.250 0.7666 0.13473 0.12980 -0.0177 0.0496 1.0000
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Polar data table (+)
Polar graphs
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