MH 62 9.3% (mh62-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 62 9.3% (mh62-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.64 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh62-il-1000000.txt Download as CSV file: xf-mh62-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6153 0.15227 0.15069 0.0407 1.0000 0.0055
-12.250 -0.6094 0.14805 0.14648 0.0386 1.0000 0.0057
-6.000 -0.5563 0.01742 0.01267 -0.0128 0.8411 0.0045
-5.750 -0.5298 0.01691 0.01200 -0.0123 0.8325 0.0043
-5.500 -0.5066 0.01466 0.00951 -0.0114 0.8241 0.0039
-5.250 -0.4821 0.01319 0.00782 -0.0106 0.8163 0.0038
-5.000 -0.4567 0.01212 0.00659 -0.0100 0.8081 0.0038
-4.750 -0.4308 0.01130 0.00561 -0.0094 0.8005 0.0039
-4.500 -0.4043 0.01070 0.00490 -0.0090 0.7927 0.0041
-4.250 -0.3783 0.00983 0.00386 -0.0085 0.7850 0.0046
-4.000 -0.3513 0.00940 0.00335 -0.0082 0.7775 0.0056
-3.750 -0.3236 0.00911 0.00301 -0.0080 0.7696 0.0065
-3.500 -0.2960 0.00883 0.00264 -0.0078 0.7623 0.0074
-3.250 -0.2689 0.00830 0.00216 -0.0075 0.7543 0.0284
-3.000 -0.2425 0.00777 0.00187 -0.0073 0.7470 0.0879
-2.750 -0.2157 0.00734 0.00166 -0.0071 0.7390 0.1504
-2.500 -0.1890 0.00693 0.00151 -0.0070 0.7315 0.2243
-2.250 -0.1617 0.00667 0.00139 -0.0069 0.7234 0.2728
-2.000 -0.1339 0.00650 0.00128 -0.0068 0.7153 0.3084
-1.750 -0.1064 0.00631 0.00118 -0.0067 0.7071 0.3527
-1.500 -0.0789 0.00609 0.00111 -0.0066 0.6982 0.4057
-1.250 -0.0516 0.00587 0.00105 -0.0065 0.6894 0.4632
-1.000 -0.0242 0.00570 0.00098 -0.0064 0.6800 0.5128
-0.750 0.0032 0.00553 0.00094 -0.0062 0.6701 0.5633
-0.500 0.0303 0.00536 0.00090 -0.0060 0.6600 0.6171
-0.250 0.0570 0.00518 0.00087 -0.0056 0.6492 0.6765
0.250 0.1078 0.00475 0.00085 -0.0043 0.6255 0.8214
0.500 0.1331 0.00453 0.00086 -0.0033 0.6125 0.9066
0.750 0.1818 0.00454 0.00089 -0.0077 0.5960 0.9662
1.000 0.2251 0.00462 0.00090 -0.0110 0.5782 0.9849
1.250 0.2629 0.00472 0.00091 -0.0131 0.5594 0.9957
1.500 0.3003 0.00482 0.00092 -0.0152 0.5389 1.0000
1.750 0.3270 0.00492 0.00094 -0.0149 0.5187 1.0000
2.000 0.3537 0.00504 0.00097 -0.0147 0.4979 1.0000
2.250 0.3806 0.00517 0.00101 -0.0145 0.4763 1.0000
2.500 0.4074 0.00531 0.00106 -0.0143 0.4556 1.0000
2.750 0.4343 0.00545 0.00114 -0.0141 0.4341 1.0000
3.000 0.4611 0.00561 0.00122 -0.0139 0.4139 1.0000
3.250 0.4880 0.00577 0.00130 -0.0137 0.3928 1.0000
3.500 0.5148 0.00595 0.00141 -0.0135 0.3736 1.0000
3.750 0.5417 0.00612 0.00151 -0.0133 0.3529 1.0000
4.250 0.5952 0.00650 0.00176 -0.0130 0.3136 1.0000
4.500 0.6219 0.00671 0.00191 -0.0128 0.2940 1.0000
4.750 0.6485 0.00693 0.00206 -0.0127 0.2749 1.0000
5.000 0.6750 0.00717 0.00223 -0.0125 0.2537 1.0000
5.250 0.7014 0.00742 0.00241 -0.0123 0.2336 1.0000
5.500 0.7278 0.00769 0.00261 -0.0121 0.2132 1.0000
5.750 0.7540 0.00798 0.00284 -0.0120 0.1936 1.0000
6.000 0.7801 0.00827 0.00307 -0.0118 0.1745 1.0000
6.250 0.8059 0.00861 0.00332 -0.0116 0.1550 1.0000
6.500 0.8317 0.00896 0.00359 -0.0114 0.1347 1.0000
6.750 0.8573 0.00933 0.00389 -0.0111 0.1168 1.0000
7.000 0.8828 0.00969 0.00420 -0.0109 0.1015 1.0000
7.250 0.9081 0.01009 0.00454 -0.0107 0.0850 1.0000
7.500 0.9326 0.01060 0.00494 -0.0104 0.0656 1.0000
7.750 0.9572 0.01108 0.00534 -0.0101 0.0497 1.0000
8.000 0.9812 0.01163 0.00581 -0.0098 0.0352 1.0000
8.250 1.0051 0.01218 0.00630 -0.0094 0.0247 1.0000
8.500 1.0292 0.01268 0.00678 -0.0090 0.0181 1.0000
8.750 1.0529 0.01321 0.00730 -0.0086 0.0133 1.0000
9.000 1.0764 0.01375 0.00786 -0.0082 0.0103 1.0000
9.250 1.0998 0.01427 0.00841 -0.0077 0.0075 1.0000
9.500 1.1211 0.01505 0.00919 -0.0071 0.0039 1.0000
9.750 1.1420 0.01587 0.01007 -0.0063 0.0025 1.0000
10.000 1.1633 0.01658 0.01084 -0.0057 0.0019 1.0000
10.250 1.1793 0.01794 0.01237 -0.0044 0.0014 1.0000
10.500 1.1988 0.01872 0.01324 -0.0036 0.0013 1.0000
10.750 1.2165 0.01965 0.01427 -0.0026 0.0013 1.0000
11.000 1.2325 0.02066 0.01540 -0.0014 0.0012 1.0000
11.250 1.2451 0.02190 0.01679 0.0000 0.0011 1.0000
11.500 1.2567 0.02307 0.01808 0.0016 0.0011 1.0000
11.750 1.2622 0.02444 0.01959 0.0038 0.0011 1.0000
12.000 1.2606 0.02594 0.02122 0.0066 0.0010 1.0000
12.250 1.2605 0.02768 0.02309 0.0084 0.0010 1.0000
12.500 1.2614 0.02960 0.02513 0.0095 0.0010 1.0000
12.750 1.2555 0.03242 0.02811 0.0103 0.0010 1.0000
13.000 1.2522 0.03525 0.03108 0.0104 0.0010 1.0000
13.250 1.2517 0.03800 0.03396 0.0101 0.0010 1.0000
13.500 1.2372 0.04269 0.03884 0.0089 0.0010 1.0000
13.750 1.2326 0.04641 0.04269 0.0076 0.0010 1.0000
14.000 1.2204 0.05144 0.04788 0.0055 0.0010 1.0000
14.250 1.2089 0.05669 0.05327 0.0030 0.0010 1.0000
14.500 1.1939 0.06273 0.05947 0.0000 0.0010 1.0000
14.750 1.1739 0.06986 0.06676 -0.0036 0.0010 1.0000
15.000 1.1609 0.07615 0.07317 -0.0069 0.0010 1.0000
15.250 1.1455 0.08305 0.08019 -0.0105 0.0010 1.0000
15.500 1.1287 0.09039 0.08765 -0.0143 0.0010 1.0000
15.750 1.1071 0.09893 0.09632 -0.0188 0.0010 1.0000
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Polar data table (+)
Polar graphs
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