MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 500,000 Max Cl/Cd: 77.52 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh60-il-500000-n5.txt Download as CSV file: xf-mh60-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 60 10.08%
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 -0.6184 0.08141 0.07945 0.0059 1.0000 0.0049
-9.250 -0.6338 0.07334 0.07143 0.0006 1.0000 0.0049
-9.000 -0.6700 0.05574 0.05376 -0.0150 0.9277 0.0047
-8.500 -0.7131 0.04399 0.04132 -0.0163 0.8682 0.0046
-8.250 -0.7209 0.03789 0.03474 -0.0160 0.8551 0.0045
-7.750 -0.7090 0.02858 0.02438 -0.0140 0.8356 0.0043
-7.500 -0.6940 0.02529 0.02060 -0.0129 0.8277 0.0042
-7.250 -0.6751 0.02279 0.01768 -0.0119 0.8198 0.0042
-7.000 -0.6540 0.02080 0.01532 -0.0111 0.8126 0.0042
-6.750 -0.6312 0.01922 0.01346 -0.0103 0.8053 0.0042
-6.500 -0.6076 0.01787 0.01187 -0.0096 0.7985 0.0042
-6.250 -0.5834 0.01673 0.01053 -0.0090 0.7915 0.0042
-6.000 -0.5586 0.01575 0.00938 -0.0084 0.7850 0.0043
-5.750 -0.5335 0.01489 0.00837 -0.0079 0.7780 0.0043
-5.500 -0.5080 0.01414 0.00749 -0.0074 0.7716 0.0044
-5.250 -0.4821 0.01347 0.00669 -0.0070 0.7647 0.0045
-5.000 -0.4559 0.01289 0.00599 -0.0066 0.7583 0.0047
-4.750 -0.4292 0.01239 0.00539 -0.0063 0.7513 0.0049
-4.500 -0.4024 0.01196 0.00484 -0.0060 0.7449 0.0051
-4.250 -0.3755 0.01148 0.00427 -0.0057 0.7378 0.0057
-3.750 -0.3209 0.01078 0.00344 -0.0052 0.7239 0.0097
-3.250 -0.2666 0.01008 0.00282 -0.0048 0.7094 0.0393
-3.000 -0.2408 0.00947 0.00251 -0.0046 0.7023 0.1087
-2.750 -0.2141 0.00903 0.00229 -0.0045 0.6944 0.1672
-2.500 -0.1867 0.00881 0.00212 -0.0043 0.6869 0.1998
-2.250 -0.1592 0.00857 0.00197 -0.0043 0.6787 0.2381
-2.000 -0.1321 0.00828 0.00184 -0.0041 0.6708 0.2935
-1.750 -0.1046 0.00808 0.00172 -0.0040 0.6622 0.3317
-1.500 -0.0771 0.00789 0.00163 -0.0039 0.6534 0.3719
-1.250 -0.0496 0.00774 0.00154 -0.0038 0.6443 0.4092
-1.000 -0.0220 0.00759 0.00146 -0.0037 0.6344 0.4477
-0.750 0.0055 0.00744 0.00139 -0.0035 0.6243 0.4861
-0.500 0.0328 0.00730 0.00134 -0.0033 0.6136 0.5281
-0.250 0.0598 0.00717 0.00130 -0.0031 0.6023 0.5727
0.000 0.0866 0.00702 0.00126 -0.0028 0.5901 0.6218
0.250 0.1129 0.00685 0.00124 -0.0023 0.5774 0.6775
0.500 0.1384 0.00668 0.00124 -0.0017 0.5640 0.7405
0.750 0.1634 0.00649 0.00124 -0.0008 0.5498 0.8105
1.000 0.1918 0.00635 0.00128 -0.0006 0.5346 0.8871
1.250 0.2409 0.00639 0.00133 -0.0050 0.5156 0.9456
1.500 0.2851 0.00651 0.00136 -0.0085 0.4957 0.9709
1.750 0.3225 0.00665 0.00140 -0.0105 0.4763 0.9858
2.000 0.3581 0.00679 0.00145 -0.0122 0.4571 0.9965
2.250 0.3908 0.00693 0.00150 -0.0133 0.4382 1.0000
2.500 0.4174 0.00708 0.00157 -0.0131 0.4204 1.0000
2.750 0.4441 0.00724 0.00165 -0.0129 0.4030 1.0000
3.000 0.4708 0.00740 0.00174 -0.0127 0.3856 1.0000
3.250 0.4974 0.00758 0.00185 -0.0125 0.3681 1.0000
3.500 0.5240 0.00776 0.00197 -0.0123 0.3517 1.0000
3.750 0.5506 0.00795 0.00209 -0.0122 0.3355 1.0000
4.000 0.5772 0.00815 0.00223 -0.0120 0.3196 1.0000
4.250 0.6037 0.00835 0.00239 -0.0118 0.3038 1.0000
4.500 0.6302 0.00857 0.00256 -0.0116 0.2878 1.0000
4.750 0.6566 0.00879 0.00273 -0.0114 0.2727 1.0000
5.000 0.6828 0.00903 0.00293 -0.0112 0.2561 1.0000
5.250 0.7090 0.00929 0.00315 -0.0110 0.2406 1.0000
5.500 0.7350 0.00957 0.00338 -0.0108 0.2243 1.0000
5.750 0.7609 0.00986 0.00362 -0.0106 0.2089 1.0000
6.250 0.8124 0.01048 0.00417 -0.0102 0.1788 1.0000
6.500 0.8379 0.01081 0.00447 -0.0099 0.1643 1.0000
6.750 0.8632 0.01116 0.00478 -0.0097 0.1502 1.0000
7.000 0.8884 0.01152 0.00512 -0.0094 0.1376 1.0000
7.250 0.9133 0.01191 0.00549 -0.0091 0.1245 1.0000
7.500 0.9379 0.01233 0.00587 -0.0088 0.1115 1.0000
7.750 0.9622 0.01277 0.00628 -0.0085 0.0983 1.0000
8.000 0.9862 0.01324 0.00672 -0.0082 0.0854 1.0000
8.250 1.0100 0.01372 0.00717 -0.0078 0.0750 1.0000
8.500 1.0335 0.01420 0.00765 -0.0074 0.0649 1.0000
8.750 1.0566 0.01472 0.00818 -0.0070 0.0555 1.0000
9.000 1.0791 0.01529 0.00874 -0.0065 0.0467 1.0000
9.250 1.1009 0.01592 0.00936 -0.0059 0.0380 1.0000
9.500 1.1215 0.01665 0.01005 -0.0053 0.0288 1.0000
9.750 1.1411 0.01744 0.01080 -0.0046 0.0205 1.0000
10.000 1.1601 0.01824 0.01158 -0.0038 0.0152 1.0000
10.250 1.1792 0.01896 0.01234 -0.0030 0.0120 1.0000
10.500 1.1975 0.01973 0.01317 -0.0021 0.0098 1.0000
10.750 1.2150 0.02050 0.01400 -0.0012 0.0082 1.0000
11.000 1.2307 0.02136 0.01492 -0.0001 0.0069 1.0000
11.250 1.2454 0.02223 0.01586 0.0011 0.0053 1.0000
11.500 1.2569 0.02322 0.01692 0.0026 0.0046 1.0000
11.750 1.2640 0.02422 0.01801 0.0047 0.0038 1.0000
12.000 1.2702 0.02541 0.01929 0.0064 0.0033 1.0000
12.250 1.2735 0.02701 0.02096 0.0079 0.0025 1.0000
12.500 1.2789 0.02857 0.02264 0.0089 0.0023 1.0000
12.750 1.2835 0.03031 0.02449 0.0096 0.0021 1.0000
13.000 1.2879 0.03221 0.02653 0.0102 0.0021 1.0000
13.250 1.2881 0.03458 0.02901 0.0105 0.0017 1.0000
13.500 1.2899 0.03695 0.03150 0.0105 0.0017 1.0000
13.750 1.2841 0.04028 0.03497 0.0102 0.0015 1.0000
14.000 1.2826 0.04328 0.03811 0.0096 0.0015 1.0000
14.250 1.2772 0.04694 0.04190 0.0087 0.0015 1.0000
14.500 1.2742 0.05042 0.04551 0.0075 0.0015 1.0000
14.750 1.2649 0.05496 0.05019 0.0058 0.0015 1.0000
15.000 1.2511 0.06036 0.05576 0.0035 0.0014 1.0000
15.250 1.2408 0.06549 0.06103 0.0012 0.0014 1.0000
15.500 1.2284 0.07118 0.06686 -0.0015 0.0014 1.0000
15.750 1.2156 0.07718 0.07298 -0.0044 0.0014 1.0000
16.000 1.2001 0.08375 0.07970 -0.0076 0.0014 1.0000
16.250 1.1821 0.09101 0.08709 -0.0112 0.0014 1.0000
16.500 1.1641 0.09846 0.09468 -0.0149 0.0014 1.0000
16.750 1.1458 0.10615 0.10249 -0.0188 0.0014 1.0000
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Polar data table (+)
Polar graphs
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