MH 45 9.85% (mh45-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: MH 45 9.85% (mh45-il) Reynolds number: 500,000 Max Cl/Cd: 75.25 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh45-il-500000-n5.txt Download as CSV file: xf-mh45-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 45 9.85%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6248 0.08456 0.08255 0.0105 1.0000 0.0042
-9.250 -0.6341 0.07794 0.07597 0.0064 1.0000 0.0041
-9.000 -0.6558 0.06815 0.06624 -0.0005 1.0000 0.0041
-8.750 -0.6916 0.05296 0.05089 -0.0135 1.0000 0.0040
-8.500 -0.7096 0.04620 0.04372 -0.0152 0.8996 0.0039
-8.250 -0.7230 0.03961 0.03663 -0.0148 0.8736 0.0038
-7.750 -0.7190 0.02837 0.02416 -0.0126 0.8462 0.0036
-7.500 -0.7047 0.02470 0.01994 -0.0114 0.8363 0.0035
-7.250 -0.6858 0.02219 0.01699 -0.0103 0.8275 0.0035
-7.000 -0.6643 0.02029 0.01475 -0.0095 0.8189 0.0035
-6.750 -0.6413 0.01879 0.01297 -0.0088 0.8110 0.0035
-6.500 -0.6176 0.01754 0.01149 -0.0081 0.8031 0.0036
-6.250 -0.5931 0.01646 0.01021 -0.0075 0.7957 0.0036
-6.000 -0.5683 0.01554 0.00911 -0.0069 0.7882 0.0037
-5.750 -0.5430 0.01472 0.00815 -0.0064 0.7809 0.0038
-5.500 -0.5174 0.01400 0.00730 -0.0059 0.7736 0.0040
-5.250 -0.4913 0.01337 0.00655 -0.0055 0.7664 0.0042
-5.000 -0.4649 0.01284 0.00589 -0.0052 0.7591 0.0044
-4.750 -0.4384 0.01227 0.00522 -0.0048 0.7519 0.0048
-4.500 -0.4117 0.01182 0.00468 -0.0045 0.7446 0.0053
-4.250 -0.3845 0.01146 0.00426 -0.0043 0.7372 0.0061
-4.000 -0.3572 0.01115 0.00385 -0.0040 0.7299 0.0071
-3.750 -0.3298 0.01081 0.00347 -0.0038 0.7222 0.0096
-3.500 -0.3027 0.01046 0.00313 -0.0036 0.7146 0.0181
-3.250 -0.2754 0.01011 0.00282 -0.0034 0.7066 0.0348
-3.000 -0.2491 0.00958 0.00250 -0.0032 0.6990 0.0874
-2.750 -0.2228 0.00904 0.00226 -0.0030 0.6906 0.1617
-2.500 -0.1954 0.00879 0.00209 -0.0029 0.6826 0.1992
-2.250 -0.1679 0.00856 0.00194 -0.0028 0.6738 0.2366
-2.000 -0.1407 0.00829 0.00182 -0.0026 0.6652 0.2869
-1.500 -0.0857 0.00790 0.00160 -0.0024 0.6467 0.3677
-1.250 -0.0580 0.00776 0.00151 -0.0023 0.6371 0.4002
-1.000 -0.0304 0.00763 0.00143 -0.0021 0.6269 0.4352
-0.750 -0.0028 0.00750 0.00136 -0.0020 0.6159 0.4710
-0.500 0.0247 0.00736 0.00131 -0.0018 0.6046 0.5101
-0.250 0.0519 0.00723 0.00127 -0.0016 0.5927 0.5523
0.000 0.0789 0.00710 0.00124 -0.0014 0.5804 0.5987
0.250 0.1056 0.00696 0.00122 -0.0010 0.5674 0.6501
0.500 0.1314 0.00679 0.00121 -0.0004 0.5535 0.7106
0.750 0.1565 0.00660 0.00121 0.0004 0.5394 0.7804
1.000 0.1820 0.00641 0.00124 0.0012 0.5246 0.8597
1.250 0.2246 0.00639 0.00130 -0.0016 0.5062 0.9353
1.500 0.2716 0.00650 0.00133 -0.0057 0.4860 0.9694
1.750 0.3103 0.00663 0.00137 -0.0080 0.4674 0.9862
2.000 0.3463 0.00677 0.00142 -0.0098 0.4482 0.9976
2.250 0.3769 0.00691 0.00148 -0.0104 0.4299 1.0000
2.500 0.4036 0.00706 0.00154 -0.0102 0.4126 1.0000
2.750 0.4303 0.00721 0.00161 -0.0099 0.3948 1.0000
3.000 0.4570 0.00737 0.00170 -0.0097 0.3771 1.0000
3.250 0.4837 0.00754 0.00182 -0.0095 0.3600 1.0000
3.500 0.5104 0.00773 0.00193 -0.0093 0.3433 1.0000
3.750 0.5371 0.00792 0.00206 -0.0091 0.3263 1.0000
4.000 0.5637 0.00812 0.00220 -0.0089 0.3096 1.0000
4.250 0.5903 0.00833 0.00235 -0.0087 0.2915 1.0000
4.500 0.6167 0.00856 0.00252 -0.0085 0.2739 1.0000
4.750 0.6431 0.00882 0.00271 -0.0084 0.2553 1.0000
5.000 0.6694 0.00907 0.00292 -0.0082 0.2377 1.0000
5.250 0.6956 0.00935 0.00313 -0.0080 0.2190 1.0000
5.500 0.7216 0.00967 0.00337 -0.0078 0.2006 1.0000
5.750 0.7476 0.00997 0.00363 -0.0076 0.1848 1.0000
6.000 0.7734 0.01029 0.00391 -0.0074 0.1676 1.0000
6.250 0.7992 0.01062 0.00420 -0.0072 0.1530 1.0000
6.500 0.8248 0.01097 0.00450 -0.0069 0.1392 1.0000
6.750 0.8503 0.01133 0.00483 -0.0067 0.1254 1.0000
7.000 0.8756 0.01170 0.00519 -0.0064 0.1145 1.0000
7.250 0.9007 0.01210 0.00555 -0.0062 0.1030 1.0000
7.500 0.9257 0.01249 0.00593 -0.0059 0.0931 1.0000
7.750 0.9507 0.01287 0.00632 -0.0056 0.0843 1.0000
8.000 0.9752 0.01331 0.00676 -0.0053 0.0751 1.0000
8.250 0.9992 0.01380 0.00722 -0.0050 0.0655 1.0000
8.500 1.0233 0.01426 0.00768 -0.0047 0.0580 1.0000
8.750 1.0471 0.01473 0.00817 -0.0043 0.0523 1.0000
9.000 1.0704 0.01525 0.00870 -0.0039 0.0461 1.0000
9.250 1.0936 0.01576 0.00924 -0.0034 0.0409 1.0000
9.500 1.1158 0.01636 0.00986 -0.0030 0.0353 1.0000
9.750 1.1381 0.01691 0.01046 -0.0024 0.0315 1.0000
10.000 1.1593 0.01757 0.01114 -0.0019 0.0272 1.0000
10.250 1.1802 0.01821 0.01184 -0.0012 0.0239 1.0000
10.500 1.2000 0.01894 0.01259 -0.0005 0.0205 1.0000
10.750 1.2187 0.01972 0.01343 0.0003 0.0180 1.0000
11.000 1.2372 0.02046 0.01423 0.0011 0.0158 1.0000
11.250 1.2526 0.02143 0.01523 0.0021 0.0132 1.0000
11.500 1.2693 0.02219 0.01608 0.0031 0.0118 1.0000
11.750 1.2830 0.02313 0.01707 0.0042 0.0104 1.0000
12.000 1.2918 0.02422 0.01823 0.0060 0.0093 1.0000
12.250 1.2991 0.02524 0.01934 0.0078 0.0085 1.0000
12.500 1.3057 0.02647 0.02068 0.0091 0.0079 1.0000
12.750 1.3116 0.02794 0.02223 0.0102 0.0074 1.0000
13.000 1.3164 0.02962 0.02400 0.0110 0.0068 1.0000
13.250 1.3197 0.03156 0.02603 0.0115 0.0062 1.0000
13.500 1.3240 0.03352 0.02811 0.0118 0.0058 1.0000
13.750 1.3266 0.03578 0.03051 0.0118 0.0054 1.0000
14.000 1.3278 0.03827 0.03313 0.0116 0.0051 1.0000
14.250 1.3274 0.04106 0.03601 0.0111 0.0045 1.0000
14.500 1.3231 0.04448 0.03952 0.0103 0.0040 1.0000
14.750 1.3179 0.04818 0.04337 0.0091 0.0041 1.0000
15.000 1.3127 0.05203 0.04735 0.0077 0.0040 1.0000
15.250 1.3064 0.05620 0.05166 0.0060 0.0036 1.0000
15.500 1.2959 0.06114 0.05672 0.0038 0.0031 1.0000
15.750 1.2837 0.06655 0.06229 0.0013 0.0035 1.0000
16.000 1.2706 0.07236 0.06824 -0.0016 0.0033 1.0000
16.250 1.2567 0.07849 0.07450 -0.0046 0.0031 1.0000
16.500 1.2389 0.08553 0.08169 -0.0082 0.0033 1.0000
16.750 1.2205 0.09286 0.08916 -0.0120 0.0032 1.0000
17.000 1.2016 0.10047 0.09689 -0.0159 0.0030 1.0000
17.250 1.1818 0.10852 0.10509 -0.0201 0.0033 1.0000
17.500 1.1609 0.11698 0.11368 -0.0245 0.0032 1.0000
|
Polar data table (+)
Polar graphs
<< Back to MH 45 9.85% (mh45-il)