MH 64 8.59% (mh64-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 64 8.59% (mh64-il) Reynolds number: 1,000,000 Max Cl/Cd: 84 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh64-il-1000000-n5.txt Download as CSV file: xf-mh64-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 64 8.59%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5012 0.09569 0.09432 0.0159 1.0000 0.0055
-9.250 -0.5023 0.09026 0.08890 0.0138 1.0000 0.0055
-7.000 -0.6314 0.03023 0.02727 -0.0178 0.8602 0.0028
-6.750 -0.6196 0.02517 0.02167 -0.0170 0.8484 0.0026
-6.500 -0.6014 0.02170 0.01773 -0.0162 0.8378 0.0025
-6.250 -0.5801 0.01906 0.01470 -0.0154 0.8283 0.0025
-6.000 -0.5570 0.01699 0.01228 -0.0147 0.8190 0.0024
-5.750 -0.5327 0.01535 0.01035 -0.0141 0.8096 0.0024
-5.500 -0.5076 0.01402 0.00879 -0.0135 0.8008 0.0023
-5.250 -0.4822 0.01292 0.00749 -0.0129 0.7919 0.0023
-5.000 -0.4563 0.01198 0.00638 -0.0125 0.7827 0.0023
-4.750 -0.4301 0.01121 0.00547 -0.0120 0.7740 0.0022
-4.250 -0.3766 0.01003 0.00404 -0.0114 0.7562 0.0023
-4.000 -0.3494 0.00960 0.00350 -0.0111 0.7475 0.0023
-3.500 -0.2943 0.00893 0.00261 -0.0107 0.7288 0.0024
-3.250 -0.2665 0.00869 0.00229 -0.0106 0.7195 0.0025
-3.000 -0.2386 0.00850 0.00201 -0.0104 0.7100 0.0027
-2.750 -0.2106 0.00832 0.00177 -0.0103 0.7000 0.0036
-2.500 -0.1830 0.00804 0.00154 -0.0102 0.6902 0.0205
-2.250 -0.1557 0.00771 0.00133 -0.0101 0.6800 0.0600
-2.000 -0.1282 0.00747 0.00117 -0.0100 0.6690 0.0973
-1.750 -0.1017 0.00697 0.00102 -0.0100 0.6574 0.1963
-1.500 -0.0746 0.00667 0.00092 -0.0099 0.6451 0.2670
-1.250 -0.0470 0.00649 0.00085 -0.0099 0.6322 0.3115
-1.000 -0.0191 0.00639 0.00078 -0.0099 0.6183 0.3443
-0.750 0.0087 0.00630 0.00074 -0.0098 0.6037 0.3764
-0.500 0.0366 0.00623 0.00070 -0.0098 0.5881 0.4076
-0.250 0.0644 0.00617 0.00067 -0.0098 0.5712 0.4399
0.000 0.0922 0.00612 0.00065 -0.0097 0.5528 0.4743
0.500 0.1474 0.00603 0.00065 -0.0097 0.5129 0.5492
0.750 0.1748 0.00600 0.00067 -0.0096 0.4917 0.5921
1.000 0.2020 0.00595 0.00069 -0.0095 0.4705 0.6400
1.250 0.2288 0.00589 0.00073 -0.0092 0.4491 0.6937
1.500 0.2550 0.00582 0.00078 -0.0089 0.4275 0.7539
1.750 0.2802 0.00573 0.00084 -0.0083 0.4069 0.8208
2.000 0.3046 0.00562 0.00091 -0.0073 0.3851 0.8994
2.250 0.3486 0.00569 0.00100 -0.0108 0.3603 0.9689
2.500 0.3884 0.00585 0.00107 -0.0135 0.3374 0.9921
2.750 0.4218 0.00603 0.00115 -0.0148 0.3160 1.0000
3.000 0.4486 0.00619 0.00126 -0.0146 0.2969 1.0000
3.250 0.4753 0.00636 0.00136 -0.0144 0.2783 1.0000
3.500 0.5021 0.00655 0.00147 -0.0142 0.2587 1.0000
3.750 0.5288 0.00675 0.00161 -0.0141 0.2393 1.0000
4.000 0.5555 0.00697 0.00175 -0.0139 0.2198 1.0000
4.250 0.5822 0.00717 0.00190 -0.0137 0.2026 1.0000
4.500 0.6088 0.00743 0.00207 -0.0136 0.1817 1.0000
4.750 0.6354 0.00767 0.00225 -0.0134 0.1639 1.0000
5.000 0.6620 0.00793 0.00246 -0.0133 0.1451 1.0000
5.250 0.6883 0.00823 0.00268 -0.0131 0.1265 1.0000
5.500 0.7148 0.00851 0.00291 -0.0130 0.1116 1.0000
5.750 0.7408 0.00886 0.00317 -0.0128 0.0910 1.0000
6.000 0.7669 0.00922 0.00345 -0.0126 0.0742 1.0000
6.250 0.7928 0.00958 0.00375 -0.0124 0.0587 1.0000
6.500 0.8181 0.01007 0.00413 -0.0122 0.0384 1.0000
6.750 0.8434 0.01052 0.00453 -0.0120 0.0250 1.0000
7.000 0.8688 0.01095 0.00493 -0.0118 0.0163 1.0000
7.250 0.8940 0.01140 0.00535 -0.0115 0.0100 1.0000
7.500 0.9192 0.01185 0.00579 -0.0112 0.0062 1.0000
7.750 0.9440 0.01234 0.00628 -0.0109 0.0033 1.0000
8.000 0.9689 0.01280 0.00677 -0.0106 0.0022 1.0000
8.250 0.9932 0.01338 0.00740 -0.0102 0.0015 1.0000
8.500 1.0171 0.01399 0.00811 -0.0098 0.0013 1.0000
8.750 1.0410 0.01456 0.00875 -0.0094 0.0013 1.0000
9.000 1.0643 0.01521 0.00953 -0.0089 0.0013 1.0000
9.250 1.0869 0.01591 0.01033 -0.0083 0.0012 1.0000
9.500 1.1091 0.01664 0.01115 -0.0078 0.0012 1.0000
9.750 1.1305 0.01744 0.01205 -0.0071 0.0012 1.0000
10.000 1.1516 0.01819 0.01290 -0.0065 0.0011 1.0000
10.250 1.1713 0.01910 0.01392 -0.0057 0.0010 1.0000
10.500 1.1907 0.01997 0.01489 -0.0049 0.0010 1.0000
10.750 1.2098 0.02079 0.01580 -0.0041 0.0009 1.0000
11.000 1.2265 0.02184 0.01696 -0.0031 0.0009 1.0000
11.250 1.2426 0.02284 0.01809 -0.0021 0.0008 1.0000
11.500 1.2536 0.02426 0.01967 -0.0005 0.0008 1.0000
11.750 1.2669 0.02528 0.02078 0.0007 0.0008 1.0000
12.000 1.2701 0.02681 0.02247 0.0031 0.0008 1.0000
12.250 1.2701 0.02824 0.02402 0.0056 0.0008 1.0000
12.500 1.2711 0.02988 0.02578 0.0072 0.0008 1.0000
12.750 1.2686 0.03211 0.02815 0.0084 0.0008 1.0000
13.000 1.2659 0.03464 0.03082 0.0088 0.0007 1.0000
13.250 1.2631 0.03745 0.03376 0.0087 0.0007 1.0000
13.500 1.2537 0.04135 0.03784 0.0078 0.0007 1.0000
13.750 1.2471 0.04528 0.04191 0.0064 0.0007 1.0000
14.000 1.2383 0.04988 0.04664 0.0043 0.0007 1.0000
14.250 1.2285 0.05496 0.05186 0.0016 0.0007 1.0000
14.500 1.2069 0.06242 0.05951 -0.0027 0.0007 1.0000
14.750 1.1879 0.06986 0.06710 -0.0069 0.0007 1.0000
15.000 1.1691 0.07754 0.07492 -0.0113 0.0007 1.0000
15.250 1.1514 0.08527 0.08276 -0.0156 0.0007 1.0000
15.500 1.1315 0.09362 0.09122 -0.0201 0.0007 1.0000
15.750 1.1039 0.10390 0.10163 -0.0257 0.0008 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 64 8.59% (mh64-il)