MH 121 8.76% (mh121-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 121 8.76% (mh121-il) Reynolds number: 200,000 Max Cl/Cd: 83.98 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh121-il-200000.txt Download as CSV file: xf-mh121-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 121 8.76%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3915 0.08989 0.08696 -0.0286 1.0000 0.0303
-8.000 -0.3993 0.08712 0.08423 -0.0276 1.0000 0.0307
-7.750 -0.4077 0.08433 0.08148 -0.0266 1.0000 0.0311
-7.500 -0.4176 0.08145 0.07864 -0.0257 1.0000 0.0317
-7.250 -0.4289 0.07862 0.07585 -0.0247 1.0000 0.0319
-7.000 -0.4295 0.07380 0.07106 -0.0279 0.9972 0.0326
-6.750 -0.5252 0.07811 0.07526 -0.0309 0.9998 0.0285
-6.500 -0.5079 0.07283 0.06993 -0.0374 0.9963 0.0297
-6.250 -0.4879 0.06641 0.06341 -0.0460 0.9922 0.0308
-6.000 -0.4703 0.06060 0.05744 -0.0526 0.9880 0.0325
-5.750 -0.4459 0.05466 0.05123 -0.0595 0.9843 0.0348
-5.500 -0.4041 0.05154 0.04726 -0.0669 0.9808 0.0389
-5.250 -0.3924 0.04347 0.03916 -0.0696 0.9778 0.0411
-5.000 -0.3691 0.04020 0.03579 -0.0714 0.9751 0.0442
-4.750 -0.3365 0.03640 0.03140 -0.0748 0.9727 0.0542
-4.500 -0.3079 0.03423 0.02912 -0.0773 0.9708 0.0722
-4.250 -0.2735 0.03158 0.02605 -0.0805 0.9694 0.0938
-4.000 -0.2242 0.02551 0.01863 -0.0786 0.9694 0.0273
-3.750 -0.1958 0.02308 0.01596 -0.0787 0.9676 0.0250
-3.500 -0.1674 0.02119 0.01383 -0.0786 0.9652 0.0240
-3.250 -0.1370 0.01970 0.01220 -0.0789 0.9631 0.0240
-3.000 -0.1051 0.01853 0.01092 -0.0797 0.9611 0.0250
-2.750 -0.0703 0.01744 0.00968 -0.0813 0.9595 0.0294
-2.500 -0.0364 0.01493 0.00924 -0.0839 0.9588 0.5446
-2.250 -0.0029 0.01511 0.00938 -0.0851 0.9569 0.5943
-2.000 0.0190 0.01518 0.00941 -0.0840 0.9526 0.6210
-1.750 0.0465 0.01529 0.00942 -0.0840 0.9491 0.6497
-1.500 0.0764 0.01541 0.00959 -0.0844 0.9465 0.6838
-1.250 0.1104 0.01552 0.00968 -0.0857 0.9444 0.7072
-1.000 0.1322 0.01557 0.00973 -0.0847 0.9397 0.7232
-0.750 0.1606 0.01562 0.00976 -0.0851 0.9359 0.7401
-0.500 0.1936 0.01565 0.00975 -0.0863 0.9332 0.7583
-0.250 0.2291 0.01568 0.00981 -0.0880 0.9312 0.7782
0.000 0.2463 0.01573 0.00994 -0.0861 0.9249 0.8003
0.250 0.2759 0.01570 0.00999 -0.0865 0.9213 0.8279
0.500 0.3087 0.01561 0.01002 -0.0874 0.9188 0.8650
0.750 0.3362 0.01545 0.01004 -0.0875 0.9132 0.9929
1.000 0.3720 0.01556 0.01009 -0.0897 0.9091 1.0000
1.250 0.4130 0.01559 0.01009 -0.0926 0.9064 1.0000
1.500 0.4415 0.01575 0.01024 -0.0932 0.9005 1.0000
1.750 0.4774 0.01575 0.01026 -0.0949 0.8957 1.0000
2.000 0.5219 0.01557 0.01016 -0.0982 0.8929 1.0000
2.250 0.5491 0.01562 0.01025 -0.0981 0.8848 1.0000
2.500 0.5973 0.01516 0.00988 -0.1017 0.8811 1.0000
2.750 0.6395 0.01465 0.00947 -0.1040 0.8739 1.0000
3.000 0.7138 0.01288 0.00797 -0.1112 0.8667 1.0000
3.250 0.7599 0.01186 0.00708 -0.1133 0.8534 1.0000
3.500 0.7923 0.01126 0.00660 -0.1131 0.8355 1.0000
3.750 0.8240 0.01061 0.00605 -0.1124 0.8095 1.0000
4.000 0.8501 0.01021 0.00571 -0.1109 0.7728 1.0000
4.250 0.8658 0.01031 0.00498 -0.1064 0.5801 1.0000
4.500 0.8489 0.01290 0.00580 -0.0981 0.2898 1.0000
4.750 0.8501 0.01513 0.00681 -0.0940 0.0929 1.0000
5.000 0.8575 0.01750 0.00881 -0.0901 0.0149 1.0000
5.250 0.8757 0.01868 0.01016 -0.0881 0.0129 1.0000
5.500 0.8934 0.02017 0.01179 -0.0859 0.0118 1.0000
5.750 0.9144 0.02201 0.01377 -0.0844 0.0113 1.0000
6.000 0.9418 0.02437 0.01630 -0.0838 0.0113 1.0000
6.250 0.9725 0.02729 0.01951 -0.0836 0.0116 1.0000
6.500 1.0001 0.03073 0.02336 -0.0828 0.0122 1.0000
6.750 1.0215 0.03446 0.02754 -0.0811 0.0130 1.0000
7.000 1.0357 0.03911 0.03264 -0.0786 0.0139 1.0000
9.250 1.0249 0.07810 0.07471 -0.0483 0.0313 1.0000
9.500 1.0055 0.08198 0.07872 -0.0463 0.0311 1.0000
9.750 0.9853 0.08645 0.08331 -0.0458 0.0311 1.0000
10.000 0.9644 0.09176 0.08873 -0.0470 0.0311 1.0000
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Polar data table (+)
Polar graphs
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