MH 24 9.01% (mh24-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 24 9.01% (mh24-il) Reynolds number: 50,000 Max Cl/Cd: 34.16 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh24-il-50000.txt Download as CSV file: xf-mh24-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 24 9.01%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4881 0.12894 0.12183 -0.0195 1.0000 0.1816
-10.500 -0.4755 0.12438 0.11728 -0.0186 1.0000 0.1909
-10.250 -0.4949 0.12354 0.11657 -0.0210 1.0000 0.1960
-10.000 -0.4761 0.11851 0.11153 -0.0193 1.0000 0.2072
-9.750 -0.4704 0.11485 0.10791 -0.0188 1.0000 0.2174
-9.500 -0.4796 0.11236 0.10554 -0.0196 1.0000 0.2252
-9.250 -0.4853 0.11013 0.10339 -0.0195 1.0000 0.2363
-9.000 -0.4790 0.10650 0.09980 -0.0184 1.0000 0.2491
-8.750 -0.4738 0.10297 0.09622 -0.0173 1.0000 0.2615
-8.500 -0.4717 0.09980 0.09313 -0.0162 1.0000 0.2742
-8.250 -0.4754 0.09700 0.09042 -0.0150 1.0000 0.2886
-8.000 -0.4795 0.09444 0.08795 -0.0136 1.0000 0.3029
-7.750 -0.4925 0.09237 0.08599 -0.0118 1.0000 0.3178
-7.500 -0.4760 0.08819 0.08184 -0.0095 1.0000 0.3362
-7.250 -0.4787 0.08578 0.07951 -0.0070 1.0000 0.3559
-5.250 -0.5609 0.05078 0.04321 -0.0145 1.0000 0.1259
-5.000 -0.5474 0.04637 0.03820 -0.0125 1.0000 0.1086
-4.750 -0.5321 0.04276 0.03399 -0.0102 1.0000 0.0976
-4.500 -0.5150 0.03986 0.03006 -0.0073 1.0000 0.0883
-4.250 -0.4954 0.03652 0.02651 -0.0057 1.0000 0.0862
-4.000 -0.4740 0.03381 0.02342 -0.0039 1.0000 0.0845
-3.750 -0.4502 0.03134 0.02049 -0.0023 1.0000 0.0844
-3.500 -0.1702 0.02135 0.01332 -0.0360 1.0000 1.0000
-3.250 -0.1631 0.02100 0.01259 -0.0333 1.0000 1.0000
-3.000 -0.1547 0.02072 0.01188 -0.0306 1.0000 1.0000
-2.750 -0.1453 0.02050 0.01135 -0.0279 1.0000 1.0000
-2.500 -0.1351 0.02033 0.01089 -0.0253 1.0000 1.0000
-2.250 -0.1244 0.02020 0.01049 -0.0227 1.0000 1.0000
-2.000 -0.1133 0.02010 0.01016 -0.0201 1.0000 1.0000
-1.750 -0.1019 0.02003 0.00987 -0.0176 1.0000 1.0000
-1.500 -0.0901 0.01999 0.00963 -0.0152 1.0000 1.0000
-1.250 -0.0782 0.01998 0.00944 -0.0127 1.0000 1.0000
-1.000 -0.0660 0.01999 0.00924 -0.0103 1.0000 1.0000
-0.750 -0.0537 0.02003 0.00913 -0.0080 1.0000 1.0000
-0.500 -0.0412 0.02009 0.00907 -0.0057 1.0000 1.0000
-0.250 -0.0286 0.02018 0.00904 -0.0035 1.0000 1.0000
0.000 -0.0158 0.02030 0.00905 -0.0013 1.0000 1.0000
0.250 -0.0030 0.02045 0.00911 0.0008 1.0000 1.0000
0.500 0.0099 0.02063 0.00918 0.0029 1.0000 1.0000
0.750 0.0229 0.02085 0.00933 0.0048 1.0000 1.0000
1.000 0.0358 0.02110 0.00954 0.0067 1.0000 1.0000
1.250 0.0488 0.02139 0.00979 0.0086 1.0000 1.0000
1.500 0.0617 0.02173 0.01011 0.0103 1.0000 1.0000
1.750 0.0746 0.02211 0.01049 0.0119 1.0000 1.0000
2.000 0.0875 0.02255 0.01093 0.0134 1.0000 1.0000
2.250 0.1003 0.02305 0.01144 0.0148 1.0000 1.0000
2.500 0.1130 0.02361 0.01202 0.0160 1.0000 1.0000
2.750 0.1254 0.02424 0.01269 0.0172 1.0000 1.0000
3.000 0.1375 0.02496 0.01345 0.0181 1.0000 1.0000
3.250 0.1515 0.02579 0.01435 0.0185 0.9991 1.0000
3.500 0.2313 0.02798 0.01683 0.0062 0.9697 1.0000
3.750 0.2976 0.02934 0.01847 -0.0026 0.9380 1.0000
4.000 0.3647 0.03021 0.01968 -0.0106 0.9052 1.0000
4.250 0.4276 0.03042 0.02036 -0.0169 0.8705 1.0000
4.500 0.5004 0.02978 0.02023 -0.0234 0.8333 1.0000
4.750 0.5842 0.02778 0.01899 -0.0297 0.7901 1.0000
5.000 0.6828 0.02382 0.01582 -0.0349 0.7310 1.0000
5.250 0.7386 0.02184 0.01391 -0.0338 0.6342 1.0000
5.500 0.7588 0.02221 0.01382 -0.0295 0.5296 1.0000
5.750 0.7697 0.02338 0.01452 -0.0249 0.4327 1.0000
6.000 0.7787 0.02494 0.01550 -0.0207 0.3458 1.0000
6.250 0.7907 0.02682 0.01687 -0.0173 0.2713 1.0000
6.500 0.8051 0.02884 0.01847 -0.0146 0.2138 1.0000
6.750 0.8246 0.03119 0.02065 -0.0126 0.1726 1.0000
7.000 0.8443 0.03362 0.02309 -0.0107 0.1453 1.0000
7.250 0.8664 0.03666 0.02643 -0.0090 0.1301 1.0000
7.500 0.8802 0.03904 0.02904 -0.0065 0.1156 1.0000
7.750 0.8958 0.04220 0.03241 -0.0044 0.1068 1.0000
8.000 0.9039 0.04575 0.03659 -0.0009 0.1039 1.0000
8.250 0.9084 0.04955 0.04092 0.0026 0.1024 1.0000
8.500 0.9085 0.05351 0.04534 0.0061 0.1023 1.0000
8.750 0.9034 0.05766 0.04993 0.0097 0.1031 1.0000
9.000 0.8951 0.06174 0.05436 0.0130 0.1040 1.0000
9.250 0.8828 0.06580 0.05871 0.0162 0.1043 1.0000
9.500 0.8684 0.06991 0.06302 0.0188 0.1052 1.0000
9.750 0.8528 0.07408 0.06733 0.0211 0.1063 1.0000
10.000 0.8409 0.07825 0.07156 0.0229 0.1076 1.0000
10.250 0.8267 0.08269 0.07604 0.0241 0.1082 1.0000
10.500 0.8126 0.08745 0.08083 0.0244 0.1086 1.0000
10.750 0.7346 0.09977 0.09311 0.0119 0.1317 1.0000
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Polar data table (+)
Polar graphs
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