MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 500,000 Max Cl/Cd: 80.53 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh62-il-500000.txt Download as CSV file: xf-mh62-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: MH 62 9.3%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5666 0.08269 0.08074 0.0033 1.0000 0.0145
-8.250 -0.5703 0.07767 0.07576 -0.0002 1.0000 0.0146
-8.000 -0.5798 0.07189 0.07003 -0.0051 1.0000 0.0146
-7.750 -0.5887 0.06378 0.06189 -0.0136 1.0000 0.0143
-7.500 -0.5914 0.05595 0.05391 -0.0191 1.0000 0.0145
-7.250 -0.5878 0.04991 0.04768 -0.0221 1.0000 0.0148
-7.000 -0.5791 0.04449 0.04201 -0.0241 1.0000 0.0155
-5.750 -0.5083 0.01917 0.01380 -0.0182 0.8969 0.0076
-5.500 -0.4848 0.01804 0.01242 -0.0170 0.8868 0.0073
-5.250 -0.4605 0.01670 0.01088 -0.0161 0.8766 0.0072
-5.000 -0.4368 0.01508 0.00904 -0.0150 0.8673 0.0072
-4.750 -0.4143 0.01340 0.00714 -0.0138 0.8588 0.0077
-4.500 -0.3893 0.01252 0.00616 -0.0132 0.8496 0.0086
-4.250 -0.3635 0.01194 0.00550 -0.0126 0.8411 0.0096
-4.000 -0.3375 0.01142 0.00486 -0.0120 0.8330 0.0108
-3.750 -0.3112 0.01080 0.00415 -0.0115 0.8243 0.0139
-3.500 -0.2851 0.01016 0.00344 -0.0109 0.8167 0.0251
-3.250 -0.2605 0.00916 0.00287 -0.0104 0.8081 0.1261
-3.000 -0.2349 0.00860 0.00265 -0.0102 0.8000 0.2148
-2.750 -0.2089 0.00820 0.00247 -0.0098 0.7920 0.2864
-2.500 -0.1818 0.00795 0.00232 -0.0097 0.7835 0.3307
-2.250 -0.1551 0.00773 0.00218 -0.0093 0.7758 0.3786
-2.000 -0.1286 0.00740 0.00206 -0.0091 0.7670 0.4463
-1.750 -0.1023 0.00714 0.00196 -0.0087 0.7589 0.5095
-1.500 -0.0761 0.00689 0.00187 -0.0082 0.7504 0.5702
-1.250 -0.0501 0.00663 0.00180 -0.0077 0.7415 0.6347
-1.000 -0.0250 0.00637 0.00172 -0.0069 0.7331 0.7047
-0.750 -0.0007 0.00608 0.00168 -0.0058 0.7236 0.7832
-0.500 0.0244 0.00580 0.00166 -0.0047 0.7142 0.8703
-0.250 0.0697 0.00573 0.00165 -0.0079 0.7043 0.9454
0.000 0.1189 0.00576 0.00159 -0.0123 0.6933 0.9760
0.500 0.1973 0.00582 0.00150 -0.0170 0.6685 1.0000
0.750 0.2235 0.00585 0.00146 -0.0166 0.6559 1.0000
1.000 0.2497 0.00589 0.00143 -0.0162 0.6424 1.0000
1.250 0.2761 0.00594 0.00141 -0.0158 0.6279 1.0000
1.500 0.3026 0.00601 0.00141 -0.0155 0.6126 1.0000
1.750 0.3292 0.00609 0.00141 -0.0152 0.5964 1.0000
2.000 0.3559 0.00617 0.00143 -0.0149 0.5782 1.0000
2.250 0.3825 0.00628 0.00146 -0.0146 0.5588 1.0000
2.500 0.4092 0.00640 0.00150 -0.0143 0.5387 1.0000
2.750 0.4359 0.00654 0.00157 -0.0140 0.5167 1.0000
3.000 0.4626 0.00670 0.00165 -0.0138 0.4947 1.0000
3.500 0.5159 0.00706 0.00186 -0.0134 0.4497 1.0000
3.750 0.5425 0.00726 0.00199 -0.0131 0.4272 1.0000
4.000 0.5690 0.00748 0.00213 -0.0129 0.4051 1.0000
4.250 0.5956 0.00770 0.00229 -0.0127 0.3828 1.0000
4.750 0.6485 0.00818 0.00266 -0.0124 0.3386 1.0000
5.000 0.6748 0.00846 0.00286 -0.0122 0.3169 1.0000
5.250 0.7010 0.00873 0.00308 -0.0120 0.2946 1.0000
5.500 0.7272 0.00903 0.00332 -0.0118 0.2718 1.0000
5.750 0.7531 0.00937 0.00360 -0.0116 0.2490 1.0000
6.000 0.7789 0.00971 0.00389 -0.0114 0.2263 1.0000
6.250 0.8045 0.01008 0.00419 -0.0112 0.2044 1.0000
6.750 0.8552 0.01090 0.00488 -0.0107 0.1611 1.0000
7.000 0.8800 0.01136 0.00527 -0.0105 0.1404 1.0000
7.250 0.9049 0.01180 0.00569 -0.0102 0.1222 1.0000
7.500 0.9294 0.01231 0.00614 -0.0099 0.1046 1.0000
7.750 0.9536 0.01282 0.00661 -0.0095 0.0888 1.0000
8.000 0.9777 0.01334 0.00711 -0.0092 0.0735 1.0000
8.250 1.0008 0.01398 0.00769 -0.0088 0.0567 1.0000
8.500 1.0228 0.01477 0.00839 -0.0082 0.0400 1.0000
8.750 1.0445 0.01555 0.00913 -0.0077 0.0280 1.0000
9.000 1.0655 0.01642 0.01000 -0.0070 0.0201 1.0000
9.250 1.0857 0.01732 0.01091 -0.0063 0.0144 1.0000
9.500 1.1068 0.01803 0.01167 -0.0057 0.0105 1.0000
9.750 1.1235 0.01929 0.01303 -0.0045 0.0074 1.0000
10.000 1.1386 0.02062 0.01444 -0.0033 0.0054 1.0000
10.250 1.1514 0.02207 0.01605 -0.0018 0.0046 1.0000
10.500 1.1658 0.02320 0.01731 -0.0005 0.0041 1.0000
10.750 1.1775 0.02445 0.01868 0.0009 0.0038 1.0000
11.000 1.1882 0.02563 0.01995 0.0024 0.0034 1.0000
11.250 1.1826 0.02758 0.02203 0.0055 0.0030 1.0000
11.500 1.1838 0.02927 0.02384 0.0073 0.0030 1.0000
11.750 1.1638 0.03320 0.02801 0.0091 0.0028 1.0000
12.000 1.1640 0.03561 0.03058 0.0097 0.0027 1.0000
12.250 1.1624 0.03835 0.03347 0.0098 0.0027 1.0000
12.500 1.1584 0.04153 0.03681 0.0096 0.0027 1.0000
12.750 1.1530 0.04514 0.04060 0.0089 0.0026 1.0000
13.000 1.1454 0.04921 0.04483 0.0077 0.0027 1.0000
13.250 1.1404 0.05317 0.04893 0.0062 0.0026 1.0000
13.500 1.1284 0.05844 0.05440 0.0040 0.0025 1.0000
13.750 1.1188 0.06351 0.05962 0.0015 0.0026 1.0000
14.000 1.1055 0.06947 0.06575 -0.0015 0.0026 1.0000
14.250 1.0917 0.07577 0.07219 -0.0048 0.0026 1.0000
14.500 1.0788 0.08234 0.07891 -0.0084 0.0026 1.0000
14.750 1.0623 0.08984 0.08657 -0.0125 0.0026 1.0000
15.000 1.0480 0.09718 0.09403 -0.0166 0.0026 1.0000
15.250 1.0332 0.10482 0.10179 -0.0208 0.0026 1.0000
15.500 1.0175 0.11287 0.10996 -0.0252 0.0027 1.0000
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Polar data table (+)
Polar graphs
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