MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 200,000 Max Cl/Cd: 60.04 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh60-il-200000-n5.txt Download as CSV file: xf-mh60-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5774 0.08626 0.08316 0.0041 1.0000 0.0098
-9.000 -0.5854 0.07951 0.07647 -0.0003 1.0000 0.0095
-8.750 -0.5988 0.07101 0.06803 -0.0066 1.0000 0.0091
-8.500 -0.6548 0.05115 0.04780 -0.0216 1.0000 0.0083
-8.250 -0.6630 0.04470 0.04090 -0.0236 1.0000 0.0080
-7.750 -0.6459 0.03657 0.03194 -0.0248 0.9786 0.0079
-7.500 -0.6294 0.03285 0.02769 -0.0254 0.9406 0.0078
-7.250 -0.6151 0.03007 0.02445 -0.0242 0.9200 0.0078
-7.000 -0.5993 0.02767 0.02162 -0.0228 0.9048 0.0078
-6.750 -0.5810 0.02565 0.01922 -0.0214 0.8926 0.0079
-6.500 -0.5613 0.02373 0.01697 -0.0202 0.8818 0.0079
-6.250 -0.5414 0.02193 0.01489 -0.0189 0.8724 0.0081
-6.000 -0.5193 0.02050 0.01327 -0.0179 0.8629 0.0084
-5.750 -0.4968 0.01936 0.01197 -0.0170 0.8543 0.0087
-5.500 -0.4739 0.01839 0.01083 -0.0160 0.8461 0.0091
-5.250 -0.4498 0.01748 0.00979 -0.0152 0.8377 0.0097
-5.000 -0.4262 0.01668 0.00882 -0.0143 0.8305 0.0106
-4.750 -0.4009 0.01597 0.00795 -0.0137 0.8221 0.0116
-4.500 -0.3763 0.01534 0.00725 -0.0130 0.8149 0.0147
-4.250 -0.3508 0.01468 0.00651 -0.0125 0.8069 0.0197
-4.000 -0.3256 0.01401 0.00576 -0.0118 0.7997 0.0314
-3.750 -0.3007 0.01325 0.00517 -0.0113 0.7919 0.0680
-3.500 -0.2764 0.01247 0.00475 -0.0109 0.7846 0.1454
-3.250 -0.2507 0.01203 0.00446 -0.0105 0.7768 0.1994
-3.000 -0.2248 0.01165 0.00421 -0.0102 0.7692 0.2527
-2.750 -0.1992 0.01128 0.00399 -0.0097 0.7616 0.3106
-2.500 -0.1731 0.01098 0.00380 -0.0093 0.7535 0.3621
-2.250 -0.1474 0.01071 0.00362 -0.0088 0.7460 0.4096
-2.000 -0.1211 0.01045 0.00347 -0.0084 0.7373 0.4571
-1.750 -0.0954 0.01021 0.00331 -0.0078 0.7296 0.5050
-1.500 -0.0695 0.00997 0.00319 -0.0072 0.7207 0.5551
-1.250 -0.0441 0.00972 0.00309 -0.0065 0.7123 0.6099
-1.000 -0.0192 0.00947 0.00300 -0.0055 0.7039 0.6699
-0.750 0.0061 0.00921 0.00293 -0.0046 0.6945 0.7376
-0.500 0.0337 0.00898 0.00288 -0.0039 0.6857 0.8132
-0.250 0.0749 0.00887 0.00285 -0.0060 0.6756 0.8892
0.000 0.1232 0.00885 0.00279 -0.0100 0.6642 0.9401
0.250 0.1656 0.00886 0.00271 -0.0128 0.6526 0.9706
0.500 0.2061 0.00889 0.00264 -0.0154 0.6404 0.9910
0.750 0.2400 0.00893 0.00257 -0.0166 0.6278 1.0000
1.000 0.2657 0.00897 0.00253 -0.0162 0.6152 1.0000
1.250 0.2916 0.00903 0.00250 -0.0157 0.6017 1.0000
1.500 0.3176 0.00910 0.00249 -0.0153 0.5873 1.0000
1.750 0.3438 0.00919 0.00249 -0.0149 0.5721 1.0000
2.000 0.3699 0.00928 0.00251 -0.0145 0.5562 1.0000
2.250 0.3961 0.00939 0.00255 -0.0142 0.5393 1.0000
2.500 0.4223 0.00953 0.00261 -0.0138 0.5218 1.0000
3.000 0.4746 0.00984 0.00276 -0.0131 0.4854 1.0000
3.250 0.5008 0.01002 0.00289 -0.0128 0.4664 1.0000
3.750 0.5530 0.01044 0.00317 -0.0122 0.4286 1.0000
4.000 0.5790 0.01068 0.00334 -0.0119 0.4095 1.0000
4.250 0.6050 0.01093 0.00355 -0.0116 0.3912 1.0000
4.500 0.6309 0.01119 0.00376 -0.0114 0.3726 1.0000
4.750 0.6568 0.01146 0.00400 -0.0111 0.3545 1.0000
5.000 0.6825 0.01176 0.00425 -0.0109 0.3363 1.0000
5.250 0.7081 0.01207 0.00455 -0.0106 0.3187 1.0000
5.500 0.7337 0.01238 0.00485 -0.0103 0.3007 1.0000
5.750 0.7591 0.01272 0.00517 -0.0101 0.2829 1.0000
6.000 0.7842 0.01310 0.00551 -0.0098 0.2650 1.0000
6.250 0.8092 0.01348 0.00590 -0.0095 0.2474 1.0000
6.500 0.8339 0.01389 0.00630 -0.0092 0.2297 1.0000
6.750 0.8584 0.01433 0.00673 -0.0089 0.2127 1.0000
7.000 0.8825 0.01480 0.00718 -0.0085 0.1960 1.0000
7.250 0.9062 0.01531 0.00768 -0.0081 0.1799 1.0000
7.500 0.9298 0.01582 0.00822 -0.0077 0.1645 1.0000
7.750 0.9529 0.01637 0.00878 -0.0073 0.1501 1.0000
8.000 0.9757 0.01694 0.00937 -0.0068 0.1363 1.0000
8.250 0.9979 0.01756 0.00999 -0.0064 0.1223 1.0000
8.500 1.0196 0.01820 0.01066 -0.0058 0.1094 1.0000
8.750 1.0407 0.01889 0.01139 -0.0052 0.0967 1.0000
9.000 1.0611 0.01963 0.01213 -0.0046 0.0837 1.0000
9.250 1.0807 0.02042 0.01294 -0.0039 0.0721 1.0000
9.500 1.0992 0.02128 0.01382 -0.0031 0.0615 1.0000
9.750 1.1167 0.02219 0.01476 -0.0022 0.0520 1.0000
10.000 1.1330 0.02316 0.01579 -0.0012 0.0434 1.0000
10.250 1.1473 0.02425 0.01694 0.0000 0.0366 1.0000
10.500 1.1586 0.02551 0.01823 0.0013 0.0312 1.0000
10.750 1.1693 0.02671 0.01958 0.0028 0.0269 1.0000
11.000 1.1741 0.02806 0.02099 0.0047 0.0236 1.0000
11.250 1.1765 0.02967 0.02268 0.0065 0.0209 1.0000
11.500 1.1819 0.03121 0.02435 0.0077 0.0183 1.0000
11.750 1.1838 0.03316 0.02638 0.0087 0.0165 1.0000
12.000 1.1824 0.03555 0.02888 0.0094 0.0150 1.0000
12.250 1.1849 0.03774 0.03123 0.0098 0.0134 1.0000
12.500 1.1871 0.04005 0.03363 0.0098 0.0116 1.0000
12.750 1.1826 0.04321 0.03691 0.0095 0.0110 1.0000
13.000 1.1761 0.04681 0.04064 0.0088 0.0103 1.0000
13.250 1.1732 0.05015 0.04416 0.0080 0.0094 1.0000
13.500 1.1667 0.05411 0.04828 0.0068 0.0090 1.0000
13.750 1.1635 0.05783 0.05213 0.0053 0.0081 1.0000
14.000 1.1520 0.06290 0.05736 0.0032 0.0080 1.0000
14.250 1.1437 0.06772 0.06232 0.0010 0.0078 1.0000
14.500 1.1306 0.07350 0.06826 -0.0018 0.0077 1.0000
14.750 1.1185 0.07946 0.07435 -0.0048 0.0075 1.0000
15.000 1.1035 0.08622 0.08120 -0.0084 0.0069 1.0000
15.250 1.0892 0.09296 0.08808 -0.0119 0.0070 1.0000
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Polar data table (+)
Polar graphs
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