MH 70 11.08% (mh70-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 70 11.08% (mh70-il) Reynolds number: 100,000 Max Cl/Cd: 50.65 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh70-il-100000.txt Download as CSV file: xf-mh70-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 70 11.08%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3556 0.09508 0.09051 -0.0257 1.0000 0.1069
-8.250 -0.3825 0.09280 0.08841 -0.0331 1.0000 0.1105
-8.000 -0.3726 0.08818 0.08384 -0.0323 1.0000 0.1126
-7.750 -0.3525 0.08516 0.08083 -0.0296 1.0000 0.1169
-7.500 -0.3568 0.08237 0.07815 -0.0310 1.0000 0.1216
-7.250 -0.3968 0.08006 0.07603 -0.0380 1.0000 0.1250
-7.000 -0.4379 0.07938 0.07535 -0.0374 1.0000 0.1255
-6.750 -0.4209 0.07578 0.07195 -0.0310 1.0000 0.1276
-6.500 -0.4266 0.07445 0.07070 -0.0266 1.0000 0.1293
-6.250 -0.4363 0.07295 0.06925 -0.0236 1.0000 0.1320
-6.000 -0.4488 0.07090 0.06721 -0.0231 1.0000 0.1362
-5.750 -0.4255 0.06559 0.06182 -0.0299 0.9928 0.1456
-5.500 -0.3966 0.06046 0.05653 -0.0375 0.9845 0.1594
-5.250 -0.3655 0.04156 0.03594 -0.0515 0.9746 0.0730
-5.000 -0.3310 0.03522 0.02865 -0.0537 0.9682 0.0570
-4.750 -0.2970 0.03146 0.02432 -0.0556 0.9610 0.0538
-4.500 -0.2582 0.02855 0.02080 -0.0577 0.9550 0.0534
-4.250 -0.2226 0.02679 0.01863 -0.0590 0.9470 0.0570
-4.000 -0.1760 0.02485 0.01623 -0.0618 0.9423 0.0595
-3.750 -0.1461 0.02310 0.01454 -0.0622 0.9334 0.0654
-3.500 -0.1009 0.02157 0.01303 -0.0652 0.9284 0.0792
-3.250 -0.0708 0.02034 0.01195 -0.0655 0.9194 0.1066
-3.000 -0.0360 0.01810 0.01086 -0.0670 0.9132 0.2948
-2.750 -0.0118 0.01750 0.01081 -0.0663 0.9031 0.4413
-2.500 0.0223 0.01684 0.01071 -0.0666 0.8967 0.5871
-2.250 0.0419 0.01652 0.01085 -0.0638 0.8861 0.7143
-2.000 0.0819 0.01623 0.01081 -0.0633 0.8809 0.8617
-1.750 0.1598 0.01613 0.01048 -0.0711 0.8752 0.9591
-1.500 0.2580 0.01562 0.00957 -0.0841 0.8709 1.0000
-1.250 0.2741 0.01570 0.00947 -0.0824 0.8582 1.0000
-1.000 0.2940 0.01575 0.00933 -0.0808 0.8471 1.0000
-0.750 0.3128 0.01585 0.00928 -0.0791 0.8352 1.0000
-0.500 0.3308 0.01603 0.00932 -0.0772 0.8224 1.0000
-0.250 0.3507 0.01618 0.00933 -0.0755 0.8107 1.0000
0.000 0.3740 0.01619 0.00917 -0.0740 0.8012 1.0000
0.250 0.3939 0.01635 0.00924 -0.0723 0.7884 1.0000
0.500 0.4147 0.01652 0.00930 -0.0707 0.7761 1.0000
0.750 0.4372 0.01660 0.00927 -0.0692 0.7649 1.0000
1.000 0.4613 0.01658 0.00912 -0.0677 0.7546 1.0000
1.250 0.4833 0.01672 0.00920 -0.0664 0.7414 1.0000
1.500 0.5062 0.01683 0.00923 -0.0650 0.7289 1.0000
1.750 0.5304 0.01686 0.00917 -0.0638 0.7172 1.0000
2.000 0.5561 0.01678 0.00899 -0.0625 0.7066 1.0000
2.250 0.5796 0.01687 0.00903 -0.0613 0.6927 1.0000
2.500 0.6037 0.01694 0.00905 -0.0602 0.6791 1.0000
2.750 0.6283 0.01698 0.00904 -0.0591 0.6655 1.0000
3.000 0.6534 0.01701 0.00902 -0.0581 0.6518 1.0000
3.250 0.6787 0.01702 0.00897 -0.0571 0.6380 1.0000
3.500 0.7041 0.01704 0.00893 -0.0561 0.6238 1.0000
3.750 0.7295 0.01708 0.00890 -0.0551 0.6088 1.0000
4.000 0.7546 0.01714 0.00893 -0.0542 0.5931 1.0000
4.250 0.7797 0.01723 0.00898 -0.0533 0.5767 1.0000
4.500 0.8045 0.01734 0.00905 -0.0524 0.5596 1.0000
4.750 0.8294 0.01748 0.00916 -0.0515 0.5422 1.0000
5.000 0.8542 0.01765 0.00926 -0.0506 0.5244 1.0000
5.250 0.8791 0.01786 0.00938 -0.0497 0.5066 1.0000
5.500 0.9039 0.01811 0.00953 -0.0489 0.4886 1.0000
5.750 0.9270 0.01847 0.00992 -0.0480 0.4688 1.0000
6.000 0.9505 0.01884 0.01025 -0.0471 0.4495 1.0000
6.250 0.9742 0.01925 0.01059 -0.0463 0.4309 1.0000
6.500 0.9978 0.01970 0.01096 -0.0455 0.4129 1.0000
6.750 1.0205 0.02021 0.01144 -0.0446 0.3946 1.0000
7.000 1.0427 0.02078 0.01201 -0.0437 0.3764 1.0000
7.250 1.0648 0.02136 0.01260 -0.0428 0.3591 1.0000
7.500 1.0869 0.02200 0.01321 -0.0420 0.3426 1.0000
7.750 1.1087 0.02266 0.01386 -0.0411 0.3267 1.0000
8.000 1.1302 0.02338 0.01458 -0.0402 0.3115 1.0000
8.250 1.1515 0.02414 0.01535 -0.0394 0.2970 1.0000
8.500 1.1724 0.02493 0.01615 -0.0385 0.2830 1.0000
8.750 1.1932 0.02577 0.01700 -0.0376 0.2699 1.0000
9.000 1.2142 0.02663 0.01785 -0.0368 0.2573 1.0000
9.250 1.2357 0.02752 0.01868 -0.0360 0.2452 1.0000
9.500 1.2530 0.02842 0.01975 -0.0348 0.2331 1.0000
9.750 1.2706 0.02946 0.02092 -0.0336 0.2217 1.0000
10.000 1.2893 0.03052 0.02202 -0.0326 0.2111 1.0000
10.250 1.3106 0.03155 0.02293 -0.0320 0.2006 1.0000
10.500 1.3230 0.03264 0.02429 -0.0302 0.1906 1.0000
10.750 1.3380 0.03390 0.02566 -0.0289 0.1811 1.0000
11.000 1.3585 0.03505 0.02670 -0.0283 0.1717 1.0000
11.250 1.3655 0.03632 0.02829 -0.0260 0.1631 1.0000
11.500 1.3795 0.03775 0.02977 -0.0247 0.1549 1.0000
11.750 1.3914 0.03894 0.03101 -0.0232 0.1469 1.0000
12.000 1.3972 0.04067 0.03297 -0.0212 0.1399 1.0000
12.250 1.4125 0.04190 0.03413 -0.0201 0.1323 1.0000
12.500 1.4084 0.04382 0.03635 -0.0171 0.1270 1.0000
12.750 1.4110 0.04530 0.03793 -0.0149 0.1213 1.0000
13.000 1.4168 0.04734 0.04005 -0.0133 0.1157 1.0000
13.250 1.4066 0.04962 0.04262 -0.0108 0.1118 1.0000
13.500 1.4271 0.05117 0.04397 -0.0105 0.1050 1.0000
13.750 1.4081 0.05417 0.04736 -0.0083 0.1028 1.0000
14.000 1.3935 0.05739 0.05088 -0.0069 0.1000 1.0000
14.250 1.3899 0.05994 0.05354 -0.0062 0.0963 1.0000
14.500 1.3961 0.06260 0.05622 -0.0058 0.0921 1.0000
14.750 1.3718 0.06729 0.06125 -0.0058 0.0910 1.0000
15.000 1.3459 0.07274 0.06699 -0.0067 0.0900 1.0000
15.250 1.3164 0.07918 0.07371 -0.0086 0.0895 1.0000
15.500 1.2803 0.08721 0.08201 -0.0120 0.0898 1.0000
15.750 1.2367 0.09737 0.09240 -0.0173 0.0910 1.0000
16.000 1.1892 0.10974 0.10494 -0.0243 0.0924 1.0000
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Polar data table (+)
Polar graphs
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