MH 46 9.1% (mh46-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 46 9.1% (mh46-il) Reynolds number: 50,000 Max Cl/Cd: 30.29 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh46-il-50000.txt Download as CSV file: xf-mh46-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 46 9.1%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5115 0.11026 0.10374 0.0115 1.0000 0.2405
-8.750 -0.5092 0.10663 0.10017 0.0106 1.0000 0.2491
-8.500 -0.5257 0.10526 0.09894 0.0083 1.0000 0.2586
-8.250 -0.5023 0.09976 0.09342 0.0095 1.0000 0.2690
-8.000 -0.4989 0.09613 0.08986 0.0089 1.0000 0.2769
-7.500 -0.5143 0.09083 0.08478 0.0069 1.0000 0.3002
-7.250 -0.4943 0.08549 0.07945 0.0073 1.0000 0.3045
-6.750 -0.5564 0.05962 0.05279 -0.0288 1.0000 0.1078
-6.500 -0.5429 0.05492 0.04805 -0.0287 1.0000 0.1063
-6.250 -0.5308 0.05031 0.04325 -0.0287 1.0000 0.1031
-6.000 -0.5204 0.04524 0.03767 -0.0286 1.0000 0.0988
-5.750 -0.5077 0.04080 0.03220 -0.0275 1.0000 0.0942
-5.500 -0.4898 0.03713 0.02807 -0.0262 1.0000 0.0942
-5.250 -0.4708 0.03373 0.02444 -0.0250 1.0000 0.0974
-5.000 -0.4513 0.03140 0.02169 -0.0233 1.0000 0.1067
-4.750 -0.4307 0.02887 0.01903 -0.0218 1.0000 0.1177
-4.500 -0.4111 0.02670 0.01677 -0.0200 1.0000 0.1386
-4.250 -0.3910 0.02462 0.01475 -0.0181 1.0000 0.1706
-4.000 -0.3726 0.02266 0.01303 -0.0158 1.0000 0.2296
-3.750 -0.3584 0.02102 0.01198 -0.0131 1.0000 0.3273
-3.500 -0.3464 0.01981 0.01138 -0.0097 1.0000 0.4344
-3.250 -0.3351 0.01884 0.01089 -0.0057 1.0000 0.5396
-3.000 -0.3241 0.01793 0.01049 -0.0011 1.0000 0.6494
-2.750 -0.3065 0.01712 0.01020 0.0037 1.0000 0.7895
-2.500 -0.0830 0.01679 0.00850 -0.0293 1.0000 1.0000
-2.250 -0.0979 0.01651 0.00812 -0.0247 1.0000 1.0000
-2.000 -0.1024 0.01650 0.00790 -0.0209 1.0000 1.0000
-1.750 -0.1000 0.01661 0.00777 -0.0178 1.0000 1.0000
-1.500 -0.0940 0.01679 0.00773 -0.0152 1.0000 1.0000
-1.250 -0.0855 0.01701 0.00773 -0.0130 1.0000 1.0000
-1.000 -0.0752 0.01727 0.00779 -0.0110 1.0000 1.0000
-0.750 -0.0634 0.01758 0.00792 -0.0094 1.0000 1.0000
-0.500 -0.0507 0.01793 0.00807 -0.0080 1.0000 1.0000
-0.250 -0.0372 0.01832 0.00831 -0.0068 1.0000 1.0000
0.000 -0.0233 0.01876 0.00861 -0.0058 1.0000 1.0000
0.250 -0.0090 0.01926 0.00899 -0.0050 1.0000 1.0000
0.500 0.0129 0.01988 0.00950 -0.0058 0.9970 1.0000
0.750 0.0730 0.02095 0.01046 -0.0136 0.9785 1.0000
1.000 0.1305 0.02190 0.01138 -0.0206 0.9592 1.0000
1.250 0.1884 0.02277 0.01224 -0.0274 0.9398 1.0000
1.500 0.2392 0.02349 0.01298 -0.0326 0.9190 1.0000
1.750 0.3000 0.02410 0.01367 -0.0392 0.8995 1.0000
2.000 0.3468 0.02461 0.01430 -0.0430 0.8777 1.0000
2.250 0.3980 0.02497 0.01476 -0.0469 0.8572 1.0000
2.500 0.4353 0.02537 0.01526 -0.0482 0.8350 1.0000
2.750 0.4707 0.02570 0.01575 -0.0488 0.8134 1.0000
3.000 0.5041 0.02593 0.01610 -0.0486 0.7918 1.0000
3.250 0.5294 0.02631 0.01657 -0.0473 0.7691 1.0000
3.500 0.5602 0.02632 0.01669 -0.0459 0.7485 1.0000
3.750 0.5812 0.02670 0.01722 -0.0437 0.7245 1.0000
4.000 0.6048 0.02689 0.01751 -0.0415 0.7018 1.0000
4.250 0.6301 0.02679 0.01751 -0.0389 0.6797 1.0000
4.500 0.6514 0.02700 0.01783 -0.0364 0.6546 1.0000
4.750 0.6737 0.02708 0.01806 -0.0337 0.6293 1.0000
5.000 0.6964 0.02706 0.01815 -0.0310 0.6032 1.0000
5.250 0.7192 0.02701 0.01818 -0.0282 0.5757 1.0000
5.500 0.7419 0.02697 0.01820 -0.0254 0.5464 1.0000
5.750 0.7651 0.02687 0.01811 -0.0226 0.5155 1.0000
6.000 0.7869 0.02703 0.01837 -0.0199 0.4813 1.0000
6.250 0.8094 0.02714 0.01839 -0.0172 0.4451 1.0000
6.500 0.8298 0.02756 0.01878 -0.0148 0.4051 1.0000
6.750 0.8498 0.02806 0.01914 -0.0123 0.3628 1.0000
7.000 0.8681 0.02885 0.01978 -0.0099 0.3179 1.0000
7.250 0.8846 0.02997 0.02078 -0.0077 0.2720 1.0000
7.500 0.9010 0.03150 0.02211 -0.0055 0.2292 1.0000
7.750 0.9179 0.03350 0.02393 -0.0037 0.1934 1.0000
8.000 0.9340 0.03574 0.02616 -0.0019 0.1645 1.0000
8.250 0.9535 0.03835 0.02876 -0.0006 0.1437 1.0000
8.500 0.9707 0.04146 0.03201 0.0008 0.1293 1.0000
8.750 0.9852 0.04435 0.03508 0.0021 0.1162 1.0000
9.000 0.9906 0.04853 0.04006 0.0041 0.1119 1.0000
9.250 0.9951 0.05285 0.04487 0.0056 0.1085 1.0000
9.500 1.0074 0.05682 0.04884 0.0066 0.1028 1.0000
9.750 0.9978 0.06135 0.05391 0.0081 0.1016 1.0000
10.000 0.9839 0.06602 0.05895 0.0092 0.1010 1.0000
10.250 0.9667 0.07080 0.06398 0.0097 0.1013 1.0000
10.500 0.9477 0.07549 0.06881 0.0101 0.1020 1.0000
10.750 0.9277 0.08057 0.07396 0.0094 0.1026 1.0000
11.000 0.9132 0.08618 0.07961 0.0077 0.1033 1.0000
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Polar data table (+)
Polar graphs
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