MH 18 11.16% (mh18-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 18 11.16% (mh18-il) Reynolds number: 50,000 Max Cl/Cd: 32.27 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh18-il-50000.txt Download as CSV file: xf-mh18-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: MH 18 11.16%
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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3863 0.11221 0.10617 -0.0204 1.0000 0.2128
-9.250 -0.3726 0.10764 0.10164 -0.0206 1.0000 0.2205
-9.000 -0.3945 0.10707 0.10123 -0.0243 1.0000 0.2282
-8.750 -0.3684 0.10168 0.09583 -0.0231 1.0000 0.2395
-8.500 -0.3603 0.09781 0.09204 -0.0235 1.0000 0.2492
-8.250 -0.3614 0.09490 0.08923 -0.0245 1.0000 0.2598
-8.000 -0.3855 0.09423 0.08876 -0.0259 1.0000 0.2701
-7.750 -0.3785 0.09103 0.08562 -0.0242 1.0000 0.2834
-7.500 -0.3798 0.08870 0.08339 -0.0212 1.0000 0.2962
-7.250 -0.3863 0.08690 0.08168 -0.0174 1.0000 0.3075
-7.000 -0.4223 0.08731 0.08225 -0.0127 1.0000 0.3101
-6.750 -0.4300 0.08547 0.08048 -0.0088 1.0000 0.3210
-6.500 -0.4709 0.08571 0.08088 -0.0042 1.0000 0.3248
-5.000 -0.5367 0.05585 0.04934 -0.0173 1.0000 0.1163
-4.750 -0.5285 0.05119 0.04391 -0.0156 1.0000 0.1035
-4.500 -0.5155 0.04765 0.04030 -0.0142 1.0000 0.1011
-4.250 -0.5026 0.04455 0.03675 -0.0125 1.0000 0.1005
-4.000 -0.4879 0.04173 0.03328 -0.0106 1.0000 0.1022
-3.750 -0.4712 0.03896 0.03003 -0.0089 1.0000 0.1049
-3.500 -0.4522 0.03654 0.02731 -0.0074 1.0000 0.1073
-3.250 -0.4318 0.03451 0.02475 -0.0057 1.0000 0.1154
-3.000 -0.4116 0.03284 0.02272 -0.0042 1.0000 0.1306
-2.750 -0.3898 0.03100 0.02089 -0.0031 1.0000 0.1500
-2.500 -0.3663 0.02952 0.01927 -0.0021 1.0000 0.1838
-2.250 -0.2147 0.02443 0.01764 -0.0213 1.0000 1.0000
-2.000 -0.2008 0.02464 0.01723 -0.0198 1.0000 1.0000
-1.750 -0.1869 0.02489 0.01700 -0.0182 1.0000 1.0000
-1.500 -0.1730 0.02518 0.01690 -0.0168 1.0000 1.0000
-1.250 -0.1586 0.02551 0.01688 -0.0154 1.0000 1.0000
-1.000 -0.1440 0.02588 0.01688 -0.0141 1.0000 1.0000
-0.750 -0.1157 0.02658 0.01723 -0.0156 0.9954 1.0000
-0.500 -0.0830 0.02742 0.01774 -0.0180 0.9883 1.0000
-0.250 -0.0475 0.02845 0.01847 -0.0208 0.9806 1.0000
0.000 -0.0174 0.02930 0.01905 -0.0226 0.9727 1.0000
0.250 0.0124 0.03022 0.01976 -0.0244 0.9644 1.0000
0.500 0.0477 0.03136 0.02069 -0.0272 0.9552 1.0000
0.750 0.0739 0.03222 0.02140 -0.0283 0.9460 1.0000
1.000 0.1005 0.03318 0.02220 -0.0294 0.9365 1.0000
1.250 0.1311 0.03427 0.02317 -0.0312 0.9258 1.0000
1.500 0.1636 0.03545 0.02425 -0.0333 0.9149 1.0000
1.750 0.1911 0.03650 0.02521 -0.0345 0.9036 1.0000
2.000 0.2137 0.03747 0.02611 -0.0349 0.8920 1.0000
2.250 0.2392 0.03854 0.02713 -0.0356 0.8794 1.0000
2.500 0.2647 0.03964 0.02820 -0.0364 0.8666 1.0000
2.750 0.2901 0.04075 0.02930 -0.0370 0.8534 1.0000
3.000 0.3154 0.04188 0.03042 -0.0377 0.8399 1.0000
3.250 0.3408 0.04301 0.03156 -0.0382 0.8258 1.0000
3.500 0.3658 0.04415 0.03271 -0.0387 0.8116 1.0000
3.750 0.3916 0.04527 0.03387 -0.0392 0.7969 1.0000
4.000 0.4173 0.04641 0.03507 -0.0396 0.7822 1.0000
4.250 0.4445 0.04752 0.03624 -0.0401 0.7673 1.0000
4.500 0.4732 0.04861 0.03741 -0.0407 0.7523 1.0000
4.750 0.5000 0.04968 0.03856 -0.0410 0.7375 1.0000
5.000 0.5140 0.05080 0.03978 -0.0397 0.7218 1.0000
5.250 0.5315 0.05194 0.04101 -0.0389 0.7065 1.0000
5.500 0.5505 0.05307 0.04223 -0.0383 0.6909 1.0000
5.750 0.5715 0.05416 0.04343 -0.0377 0.6752 1.0000
6.000 0.5954 0.05513 0.04454 -0.0374 0.6594 1.0000
6.250 0.6223 0.05598 0.04558 -0.0371 0.6439 1.0000
6.500 0.6533 0.05660 0.04639 -0.0370 0.6284 1.0000
6.750 0.6665 0.05779 0.04771 -0.0356 0.6121 1.0000
7.000 0.6779 0.05908 0.04912 -0.0341 0.5952 1.0000
7.250 0.6983 0.05993 0.05014 -0.0331 0.5785 1.0000
7.500 0.7302 0.06000 0.05052 -0.0323 0.5617 1.0000
7.750 0.7632 0.05973 0.05052 -0.0312 0.5446 1.0000
8.000 0.7667 0.06143 0.05234 -0.0293 0.5261 1.0000
8.250 0.8086 0.05994 0.05120 -0.0277 0.5074 1.0000
8.500 0.8404 0.05887 0.05045 -0.0256 0.4878 1.0000
8.750 1.0690 0.03449 0.02738 -0.0218 0.4205 1.0000
9.000 1.0804 0.03348 0.02612 -0.0168 0.3655 1.0000
9.250 1.0741 0.03422 0.02653 -0.0114 0.3134 1.0000
9.500 1.0592 0.03583 0.02776 -0.0058 0.2655 1.0000
9.750 1.0436 0.03790 0.02937 -0.0007 0.2227 1.0000
10.000 1.0314 0.04043 0.03145 0.0033 0.1830 1.0000
10.250 1.0360 0.04336 0.03393 0.0061 0.1443 1.0000
10.500 1.0438 0.04610 0.03646 0.0083 0.1183 1.0000
10.750 1.0806 0.04993 0.04026 0.0088 0.0951 1.0000
11.000 1.1017 0.05352 0.04392 0.0095 0.0835 1.0000
11.250 1.1040 0.05713 0.04805 0.0118 0.0803 1.0000
11.500 1.1045 0.06064 0.05188 0.0139 0.0769 1.0000
11.750 1.1167 0.06503 0.05625 0.0145 0.0715 1.0000
12.000 1.1033 0.06838 0.05993 0.0167 0.0711 1.0000
12.250 1.0861 0.07206 0.06392 0.0184 0.0707 1.0000
12.500 1.0674 0.07613 0.06826 0.0194 0.0706 1.0000
12.750 1.0507 0.08058 0.07294 0.0197 0.0708 1.0000
13.000 1.0289 0.08550 0.07807 0.0192 0.0709 1.0000
13.250 1.0086 0.09093 0.08366 0.0182 0.0713 1.0000
13.500 0.9920 0.09660 0.08946 0.0167 0.0718 1.0000
13.750 0.9240 0.10897 0.10220 0.0083 0.0830 1.0000
14.000 0.8999 0.11772 0.11101 0.0034 0.0854 1.0000
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Polar data table (+)
Polar graphs
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