MH 32 8.7% (mh32-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 32 8.7% (mh32-il) Reynolds number: 500,000 Max Cl/Cd: 84 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh32-il-500000-n5.txt Download as CSV file: xf-mh32-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 32 8.7%
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3475 0.08404 0.08190 -0.0272 1.0000 0.0047
-9.000 -0.3487 0.07960 0.07748 -0.0286 1.0000 0.0045
-8.750 -0.4233 0.08532 0.08306 -0.0282 1.0000 0.0047
-8.500 -0.4236 0.08161 0.07939 -0.0298 1.0000 0.0046
-8.250 -0.4273 0.07752 0.07533 -0.0316 1.0000 0.0044
-8.000 -0.4316 0.07380 0.07166 -0.0331 1.0000 0.0043
-7.750 -0.4430 0.07025 0.06817 -0.0340 1.0000 0.0042
-7.500 -0.4492 0.06560 0.06356 -0.0380 0.9989 0.0042
-7.250 -0.4316 0.05592 0.05378 -0.0514 0.9873 0.0040
-7.000 -0.4113 0.04642 0.04403 -0.0613 0.9794 0.0037
-6.750 -0.4073 0.02807 0.02467 -0.0677 0.9651 0.0029
-6.500 -0.3867 0.02349 0.01950 -0.0682 0.9568 0.0027
-6.250 -0.3650 0.02094 0.01653 -0.0678 0.9485 0.0027
-6.000 -0.3420 0.01871 0.01389 -0.0673 0.9418 0.0027
-5.750 -0.3194 0.01699 0.01185 -0.0666 0.9340 0.0026
-5.250 -0.2722 0.01391 0.00820 -0.0650 0.9209 0.0027
-5.000 -0.2480 0.01276 0.00683 -0.0642 0.9149 0.0028
-4.750 -0.2232 0.01187 0.00579 -0.0636 0.9080 0.0029
-4.500 -0.1979 0.01120 0.00500 -0.0630 0.9017 0.0030
-4.250 -0.1720 0.01068 0.00435 -0.0626 0.8948 0.0034
-4.000 -0.1458 0.01026 0.00383 -0.0621 0.8881 0.0038
-3.750 -0.1193 0.00990 0.00337 -0.0618 0.8806 0.0047
-3.500 -0.0928 0.00954 0.00293 -0.0613 0.8734 0.0066
-3.250 -0.0663 0.00921 0.00261 -0.0610 0.8649 0.0154
-3.000 -0.0401 0.00880 0.00234 -0.0607 0.8570 0.0463
-2.750 -0.0139 0.00843 0.00210 -0.0605 0.8486 0.0906
-2.500 0.0127 0.00811 0.00191 -0.0603 0.8399 0.1395
-2.250 0.0392 0.00783 0.00175 -0.0600 0.8311 0.1912
-2.000 0.0656 0.00752 0.00162 -0.0598 0.8213 0.2574
-1.500 0.1186 0.00701 0.00140 -0.0594 0.8000 0.3855
-1.250 0.1449 0.00678 0.00133 -0.0591 0.7878 0.4555
-1.000 0.1710 0.00657 0.00127 -0.0587 0.7741 0.5232
-0.750 0.1969 0.00639 0.00122 -0.0583 0.7581 0.5881
-0.500 0.2224 0.00624 0.00118 -0.0577 0.7400 0.6515
-0.250 0.2475 0.00612 0.00117 -0.0570 0.7213 0.7123
0.000 0.2723 0.00602 0.00117 -0.0562 0.7016 0.7701
0.250 0.2965 0.00595 0.00118 -0.0551 0.6817 0.8253
0.500 0.3206 0.00592 0.00120 -0.0540 0.6608 0.8785
0.750 0.3492 0.00595 0.00122 -0.0539 0.6397 0.9292
1.000 0.3878 0.00605 0.00123 -0.0562 0.6162 0.9674
1.250 0.4259 0.00617 0.00124 -0.0585 0.5928 0.9924
1.500 0.4560 0.00632 0.00129 -0.0591 0.5707 1.0000
1.750 0.4810 0.00649 0.00134 -0.0585 0.5486 1.0000
2.000 0.5063 0.00665 0.00141 -0.0580 0.5265 1.0000
2.250 0.5316 0.00684 0.00149 -0.0576 0.5035 1.0000
2.500 0.5570 0.00703 0.00158 -0.0571 0.4794 1.0000
2.750 0.5824 0.00723 0.00171 -0.0567 0.4553 1.0000
3.000 0.6079 0.00745 0.00182 -0.0563 0.4319 1.0000
3.250 0.6332 0.00768 0.00196 -0.0559 0.4072 1.0000
3.750 0.6839 0.00817 0.00229 -0.0551 0.3580 1.0000
4.000 0.7091 0.00845 0.00247 -0.0547 0.3311 1.0000
4.250 0.7342 0.00874 0.00266 -0.0543 0.3053 1.0000
4.500 0.7591 0.00905 0.00288 -0.0538 0.2796 1.0000
4.750 0.7841 0.00937 0.00311 -0.0534 0.2555 1.0000
5.000 0.8088 0.00971 0.00339 -0.0530 0.2312 1.0000
5.250 0.8337 0.01003 0.00365 -0.0526 0.2100 1.0000
5.500 0.8579 0.01043 0.00395 -0.0521 0.1834 1.0000
6.000 0.9050 0.01138 0.00465 -0.0510 0.1265 1.0000
6.250 0.9291 0.01177 0.00504 -0.0505 0.1092 1.0000
6.500 0.9530 0.01220 0.00542 -0.0500 0.0923 1.0000
7.000 0.9992 0.01320 0.00631 -0.0487 0.0591 1.0000
7.250 1.0215 0.01378 0.00682 -0.0480 0.0428 1.0000
7.500 1.0427 0.01446 0.00741 -0.0472 0.0264 1.0000
7.750 1.0643 0.01509 0.00800 -0.0464 0.0171 1.0000
8.000 1.0859 0.01570 0.00862 -0.0455 0.0120 1.0000
8.250 1.1069 0.01636 0.00933 -0.0446 0.0071 1.0000
8.500 1.1271 0.01709 0.01009 -0.0436 0.0042 1.0000
8.750 1.1467 0.01787 0.01093 -0.0424 0.0028 1.0000
9.000 1.1666 0.01855 0.01170 -0.0414 0.0022 1.0000
9.250 1.1852 0.01935 0.01258 -0.0402 0.0018 1.0000
9.500 1.2012 0.02040 0.01377 -0.0386 0.0015 1.0000
9.750 1.2182 0.02127 0.01476 -0.0372 0.0015 1.0000
10.000 1.2340 0.02218 0.01580 -0.0356 0.0014 1.0000
10.250 1.2484 0.02314 0.01689 -0.0339 0.0012 1.0000
10.500 1.2607 0.02417 0.01805 -0.0319 0.0012 1.0000
10.750 1.2686 0.02530 0.01931 -0.0293 0.0011 1.0000
11.000 1.2763 0.02639 0.02057 -0.0267 0.0010 1.0000
11.250 1.2825 0.02763 0.02194 -0.0242 0.0009 1.0000
11.500 1.2875 0.02899 0.02343 -0.0219 0.0008 1.0000
11.750 1.2905 0.03057 0.02516 -0.0196 0.0008 1.0000
12.000 1.2929 0.03226 0.02699 -0.0176 0.0008 1.0000
12.250 1.2935 0.03420 0.02908 -0.0158 0.0007 1.0000
12.500 1.2907 0.03658 0.03162 -0.0141 0.0007 1.0000
12.750 1.2883 0.03909 0.03431 -0.0129 0.0007 1.0000
13.000 1.2807 0.04234 0.03773 -0.0122 0.0007 1.0000
13.250 1.2686 0.04643 0.04202 -0.0122 0.0006 1.0000
13.500 1.2558 0.05103 0.04682 -0.0130 0.0006 1.0000
13.750 1.2540 0.05449 0.05042 -0.0140 0.0006 1.0000
14.000 1.2302 0.06157 0.05773 -0.0168 0.0006 1.0000
14.250 1.2264 0.06598 0.06227 -0.0189 0.0006 1.0000
14.500 1.2124 0.07241 0.06887 -0.0222 0.0006 1.0000
14.750 1.1961 0.07971 0.07633 -0.0262 0.0006 1.0000
15.000 1.1747 0.08847 0.08527 -0.0311 0.0006 1.0000
15.250 1.1633 0.09550 0.09243 -0.0350 0.0006 1.0000
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Polar data table (+)
Polar graphs
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