MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.28 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh60-il-1000000.txt Download as CSV file: xf-mh60-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5847 0.09639 0.09498 0.0138 1.0000 0.0089
-9.500 -0.5851 0.09168 0.09029 0.0112 1.0000 0.0090
-9.250 -0.5893 0.08609 0.08473 0.0079 1.0000 0.0091
-6.000 -0.5615 0.01808 0.01304 -0.0088 0.7940 0.0083
-5.750 -0.5387 0.01536 0.01006 -0.0076 0.7879 0.0066
-5.500 -0.5150 0.01334 0.00776 -0.0065 0.7812 0.0058
-5.250 -0.4893 0.01249 0.00676 -0.0059 0.7748 0.0056
-5.000 -0.4631 0.01178 0.00595 -0.0054 0.7682 0.0055
-4.750 -0.4368 0.01117 0.00524 -0.0050 0.7617 0.0055
-4.500 -0.4102 0.01059 0.00456 -0.0046 0.7553 0.0056
-4.250 -0.3833 0.01008 0.00395 -0.0043 0.7486 0.0057
-4.000 -0.3560 0.00966 0.00344 -0.0040 0.7421 0.0059
-3.750 -0.3285 0.00932 0.00303 -0.0038 0.7352 0.0064
-3.500 -0.3008 0.00904 0.00269 -0.0035 0.7288 0.0074
-3.250 -0.2739 0.00846 0.00222 -0.0032 0.7218 0.0360
-3.000 -0.2470 0.00805 0.00197 -0.0030 0.7154 0.0779
-2.750 -0.2200 0.00766 0.00176 -0.0029 0.7083 0.1290
-2.500 -0.1931 0.00730 0.00160 -0.0028 0.7016 0.1911
-2.250 -0.1660 0.00696 0.00148 -0.0027 0.6941 0.2519
-2.000 -0.1387 0.00671 0.00137 -0.0025 0.6870 0.3039
-1.750 -0.1111 0.00648 0.00128 -0.0025 0.6790 0.3516
-1.500 -0.0838 0.00625 0.00120 -0.0023 0.6713 0.4090
-1.250 -0.0562 0.00607 0.00113 -0.0022 0.6627 0.4545
-1.000 -0.0287 0.00589 0.00108 -0.0021 0.6542 0.5045
-0.750 -0.0013 0.00573 0.00102 -0.0019 0.6453 0.5528
-0.500 0.0259 0.00555 0.00098 -0.0017 0.6355 0.6061
-0.250 0.0527 0.00537 0.00095 -0.0014 0.6256 0.6639
0.000 0.0788 0.00517 0.00093 -0.0009 0.6151 0.7285
0.250 0.1038 0.00495 0.00092 -0.0001 0.6038 0.8022
0.500 0.1287 0.00472 0.00093 0.0009 0.5920 0.8837
0.750 0.1722 0.00467 0.00097 -0.0022 0.5774 0.9535
1.000 0.2208 0.00477 0.00099 -0.0067 0.5608 0.9750
1.250 0.2581 0.00487 0.00102 -0.0086 0.5443 0.9880
1.500 0.2962 0.00497 0.00104 -0.0108 0.5266 0.9955
1.750 0.3370 0.00508 0.00106 -0.0136 0.5061 1.0000
2.000 0.3638 0.00518 0.00108 -0.0134 0.4883 1.0000
2.250 0.3906 0.00529 0.00112 -0.0132 0.4700 1.0000
2.500 0.4175 0.00542 0.00117 -0.0130 0.4509 1.0000
2.750 0.4444 0.00556 0.00123 -0.0128 0.4329 1.0000
3.000 0.4713 0.00570 0.00129 -0.0126 0.4155 1.0000
3.250 0.4982 0.00584 0.00138 -0.0125 0.3973 1.0000
3.500 0.5251 0.00600 0.00147 -0.0123 0.3804 1.0000
4.000 0.5789 0.00633 0.00168 -0.0120 0.3469 1.0000
4.250 0.6058 0.00650 0.00180 -0.0118 0.3306 1.0000
4.500 0.6326 0.00669 0.00193 -0.0117 0.3134 1.0000
4.750 0.6594 0.00688 0.00206 -0.0115 0.2973 1.0000
5.000 0.6860 0.00710 0.00222 -0.0114 0.2795 1.0000
5.250 0.7126 0.00732 0.00239 -0.0112 0.2636 1.0000
5.500 0.7392 0.00754 0.00256 -0.0111 0.2469 1.0000
5.750 0.7656 0.00779 0.00275 -0.0109 0.2295 1.0000
6.000 0.7919 0.00806 0.00297 -0.0108 0.2117 1.0000
6.250 0.8180 0.00835 0.00319 -0.0106 0.1952 1.0000
6.500 0.8440 0.00864 0.00343 -0.0104 0.1796 1.0000
6.750 0.8699 0.00895 0.00368 -0.0102 0.1635 1.0000
7.000 0.8955 0.00929 0.00395 -0.0100 0.1466 1.0000
7.250 0.9209 0.00964 0.00426 -0.0098 0.1311 1.0000
7.500 0.9462 0.00999 0.00456 -0.0095 0.1181 1.0000
7.750 0.9712 0.01038 0.00489 -0.0093 0.1040 1.0000
8.000 0.9959 0.01081 0.00525 -0.0090 0.0897 1.0000
8.250 1.0200 0.01128 0.00564 -0.0087 0.0745 1.0000
8.500 1.0444 0.01171 0.00604 -0.0083 0.0640 1.0000
8.750 1.0681 0.01221 0.00649 -0.0080 0.0523 1.0000
9.000 1.0912 0.01276 0.00698 -0.0075 0.0408 1.0000
9.250 1.1138 0.01335 0.00752 -0.0071 0.0309 1.0000
9.500 1.1364 0.01390 0.00805 -0.0066 0.0243 1.0000
9.750 1.1587 0.01446 0.00860 -0.0060 0.0190 1.0000
10.000 1.1804 0.01507 0.00921 -0.0054 0.0149 1.0000
10.250 1.2018 0.01566 0.00983 -0.0048 0.0123 1.0000
10.500 1.2227 0.01627 0.01046 -0.0042 0.0097 1.0000
10.750 1.2418 0.01704 0.01124 -0.0033 0.0065 1.0000
11.000 1.2567 0.01817 0.01238 -0.0021 0.0030 1.0000
11.250 1.2720 0.01916 0.01346 -0.0008 0.0022 1.0000
11.500 1.2882 0.01996 0.01435 0.0004 0.0021 1.0000
11.750 1.3016 0.02090 0.01538 0.0018 0.0019 1.0000
12.000 1.3122 0.02187 0.01644 0.0035 0.0018 1.0000
12.250 1.3108 0.02333 0.01802 0.0064 0.0016 1.0000
12.500 1.3149 0.02475 0.01954 0.0080 0.0016 1.0000
12.750 1.3146 0.02674 0.02168 0.0094 0.0016 1.0000
13.000 1.3197 0.02846 0.02350 0.0101 0.0016 1.0000
13.250 1.3096 0.03181 0.02704 0.0106 0.0015 1.0000
13.500 1.3101 0.03430 0.02964 0.0106 0.0015 1.0000
13.750 1.2975 0.03846 0.03398 0.0100 0.0015 1.0000
14.000 1.2953 0.04161 0.03725 0.0093 0.0015 1.0000
14.250 1.2893 0.04541 0.04118 0.0082 0.0015 1.0000
14.500 1.2864 0.04895 0.04482 0.0070 0.0015 1.0000
14.750 1.2749 0.05385 0.04985 0.0050 0.0015 1.0000
15.000 1.2539 0.06034 0.05651 0.0023 0.0014 1.0000
15.250 1.2421 0.06576 0.06206 -0.0002 0.0014 1.0000
15.500 1.2269 0.07189 0.06832 -0.0030 0.0015 1.0000
15.750 1.2127 0.07807 0.07462 -0.0059 0.0015 1.0000
16.000 1.1965 0.08467 0.08134 -0.0090 0.0015 1.0000
16.250 1.1833 0.09091 0.08768 -0.0119 0.0015 1.0000
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Polar data table (+)
Polar graphs
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