MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 20 9.01% (mh20-il) Reynolds number: 1,000,000 Max Cl/Cd: 93.27 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh20-il-1000000-n5.txt Download as CSV file: xf-mh20-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 20 9.01%
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
------ -------- --------- --------- -------- -------- --------
-12.750 -0.5832 0.15368 0.15210 0.0320 1.0000 0.0026
-12.500 -0.5775 0.14927 0.14770 0.0300 1.0000 0.0028
-6.000 -0.5230 0.02431 0.02029 -0.0151 0.7148 0.0032
-5.750 -0.5057 0.02101 0.01656 -0.0136 0.7097 0.0031
-5.500 -0.4855 0.01837 0.01352 -0.0123 0.7043 0.0030
-5.250 -0.4630 0.01637 0.01119 -0.0112 0.6994 0.0029
-5.000 -0.4390 0.01477 0.00933 -0.0103 0.6945 0.0028
-4.750 -0.4144 0.01348 0.00779 -0.0095 0.6896 0.0028
-4.500 -0.3894 0.01240 0.00652 -0.0088 0.6852 0.0027
-4.250 -0.3640 0.01151 0.00548 -0.0081 0.6805 0.0027
-4.000 -0.3384 0.01080 0.00463 -0.0075 0.6758 0.0026
-3.750 -0.3123 0.01020 0.00391 -0.0070 0.6711 0.0026
-3.500 -0.2858 0.00972 0.00333 -0.0066 0.6655 0.0026
-3.000 -0.2319 0.00905 0.00246 -0.0060 0.6550 0.0027
-2.750 -0.2045 0.00882 0.00214 -0.0058 0.6498 0.0027
-2.500 -0.1770 0.00863 0.00186 -0.0056 0.6451 0.0029
-2.250 -0.1492 0.00847 0.00164 -0.0055 0.6400 0.0032
-2.000 -0.1216 0.00833 0.00148 -0.0054 0.6350 0.0065
-1.750 -0.0954 0.00790 0.00127 -0.0051 0.6306 0.0621
-1.500 -0.0683 0.00769 0.00116 -0.0050 0.6256 0.0938
-1.250 -0.0430 0.00718 0.00105 -0.0047 0.6208 0.2044
-1.000 -0.0161 0.00695 0.00096 -0.0046 0.6161 0.2580
-0.750 0.0112 0.00679 0.00090 -0.0045 0.6108 0.2970
-0.500 0.0379 0.00658 0.00084 -0.0044 0.6056 0.3555
-0.250 0.0645 0.00634 0.00080 -0.0042 0.6000 0.4245
0.000 0.0902 0.00604 0.00074 -0.0039 0.5940 0.5149
0.250 0.1154 0.00572 0.00072 -0.0034 0.5879 0.6102
0.500 0.1396 0.00540 0.00070 -0.0027 0.5811 0.7088
0.750 0.1622 0.00505 0.00069 -0.0015 0.5740 0.8108
1.000 0.1920 0.00480 0.00075 -0.0016 0.5656 0.9167
1.750 0.3137 0.00509 0.00095 -0.0100 0.5262 0.9772
2.000 0.3465 0.00521 0.00101 -0.0111 0.5078 0.9832
2.250 0.3889 0.00538 0.00108 -0.0144 0.4826 0.9898
2.500 0.4288 0.00558 0.00117 -0.0172 0.4559 0.9944
2.750 0.4669 0.00574 0.00123 -0.0197 0.4298 0.9969
3.000 0.5026 0.00592 0.00132 -0.0216 0.4036 0.9989
3.250 0.5353 0.00609 0.00141 -0.0228 0.3798 1.0000
3.500 0.5613 0.00625 0.00151 -0.0226 0.3590 1.0000
3.750 0.5871 0.00644 0.00162 -0.0223 0.3376 1.0000
4.000 0.6130 0.00663 0.00177 -0.0221 0.3169 1.0000
4.250 0.6387 0.00685 0.00191 -0.0218 0.2939 1.0000
4.500 0.6641 0.00712 0.00208 -0.0216 0.2656 1.0000
4.750 0.6883 0.00767 0.00235 -0.0213 0.2059 1.0000
5.000 0.7107 0.00852 0.00278 -0.0209 0.1210 1.0000
5.250 0.7332 0.00930 0.00324 -0.0204 0.0576 1.0000
5.500 0.7572 0.00971 0.00355 -0.0199 0.0377 1.0000
5.750 0.7810 0.01014 0.00393 -0.0194 0.0196 1.0000
6.000 0.8043 0.01061 0.00433 -0.0189 0.0058 1.0000
6.250 0.8279 0.01102 0.00472 -0.0183 0.0021 1.0000
6.500 0.8518 0.01139 0.00515 -0.0176 0.0015 1.0000
6.750 0.8754 0.01177 0.00558 -0.0170 0.0014 1.0000
7.000 0.8986 0.01219 0.00606 -0.0163 0.0013 1.0000
7.250 0.9212 0.01266 0.00661 -0.0155 0.0013 1.0000
7.500 0.9430 0.01322 0.00725 -0.0147 0.0012 1.0000
7.750 0.9639 0.01386 0.00799 -0.0136 0.0012 1.0000
8.000 0.9841 0.01454 0.00876 -0.0125 0.0012 1.0000
8.250 1.0028 0.01535 0.00968 -0.0113 0.0012 1.0000
8.500 1.0207 0.01620 0.01067 -0.0099 0.0012 1.0000
8.750 1.0364 0.01723 0.01183 -0.0082 0.0012 1.0000
9.000 1.0509 0.01832 0.01305 -0.0064 0.0012 1.0000
9.250 1.0643 0.01946 0.01432 -0.0045 0.0012 1.0000
9.500 1.0755 0.02078 0.01577 -0.0023 0.0012 1.0000
9.750 1.0867 0.02202 0.01715 -0.0002 0.0012 1.0000
10.000 1.0942 0.02360 0.01889 0.0023 0.0012 1.0000
10.250 1.0995 0.02528 0.02073 0.0050 0.0012 1.0000
10.500 1.0974 0.02704 0.02266 0.0087 0.0012 1.0000
10.750 1.0960 0.02897 0.02477 0.0116 0.0012 1.0000
11.000 1.0981 0.03069 0.02663 0.0135 0.0012 1.0000
11.250 1.0937 0.03336 0.02950 0.0154 0.0012 1.0000
11.500 1.0856 0.03658 0.03295 0.0169 0.0013 1.0000
11.750 1.0801 0.03956 0.03611 0.0177 0.0013 1.0000
12.000 1.0692 0.04337 0.04012 0.0180 0.0013 1.0000
12.250 1.0650 0.04642 0.04331 0.0177 0.0013 1.0000
12.500 1.0487 0.05134 0.04844 0.0168 0.0013 1.0000
12.750 1.0378 0.05577 0.05302 0.0154 0.0013 1.0000
13.000 1.0191 0.06170 0.05913 0.0131 0.0013 1.0000
13.250 1.0019 0.06792 0.06551 0.0100 0.0013 1.0000
13.500 0.9953 0.07272 0.07040 0.0074 0.0013 1.0000
13.750 0.9728 0.08111 0.07895 0.0026 0.0013 1.0000
14.000 0.9548 0.08930 0.08727 -0.0022 0.0013 1.0000
14.250 0.9382 0.09766 0.09574 -0.0070 0.0013 1.0000
14.500 0.9231 0.10604 0.10420 -0.0116 0.0013 1.0000
14.750 0.8971 0.11778 0.11605 -0.0176 0.0013 1.0000
15.000 0.8802 0.12756 0.12590 -0.0222 0.0013 1.0000
15.250 0.8532 0.14108 0.13949 -0.0278 0.0014 1.0000
15.500 0.8263 0.15548 0.15388 -0.0329 0.0014 1.0000
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Polar data table (+)
Polar graphs
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