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MH 43 8.5% (mh43-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: MH 43 8.5% (mh43-il)
Reynolds number: 200,000
Max Cl/Cd: 61.8 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-mh43-il-200000-n5.txt
Download as CSV file: xf-mh43-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 43  8.5%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.5303   0.08791   0.08458  -0.0043   1.0000   0.0096
  -8.500  -0.5317   0.08327   0.07999  -0.0070   1.0000   0.0093
  -8.250  -0.5345   0.07850   0.07527  -0.0100   1.0000   0.0091
  -8.000  -0.5402   0.07341   0.07024  -0.0138   1.0000   0.0089
  -7.750  -0.5465   0.06712   0.06398  -0.0199   1.0000   0.0088
  -7.500  -0.5476   0.05994   0.05673  -0.0258   1.0000   0.0085
  -7.250  -0.5470   0.05243   0.04905  -0.0300   1.0000   0.0082
  -7.000  -0.5443   0.04476   0.04105  -0.0324   1.0000   0.0077
  -6.750  -0.5391   0.03715   0.03288  -0.0333   1.0000   0.0072
  -6.500  -0.5267   0.03182   0.02697  -0.0330   1.0000   0.0069
  -6.250  -0.5094   0.02806   0.02268  -0.0324   1.0000   0.0067
  -6.000  -0.4897   0.02518   0.01934  -0.0317   1.0000   0.0066
  -5.750  -0.4688   0.02281   0.01657  -0.0309   1.0000   0.0066
  -5.500  -0.4401   0.02060   0.01399  -0.0315   0.9839   0.0067
  -5.250  -0.4073   0.01864   0.01172  -0.0327   0.9652   0.0068
  -5.000  -0.3755   0.01708   0.00992  -0.0336   0.9481   0.0071
  -4.750  -0.3454   0.01587   0.00852  -0.0341   0.9313   0.0075
  -4.500  -0.3175   0.01495   0.00737  -0.0340   0.9152   0.0082
  -4.250  -0.2911   0.01419   0.00643  -0.0336   0.8999   0.0092
  -4.000  -0.2651   0.01357   0.00560  -0.0329   0.8856   0.0113
  -3.750  -0.2402   0.01281   0.00482  -0.0322   0.8723   0.0250
  -3.500  -0.2165   0.01193   0.00428  -0.0316   0.8597   0.0880
  -3.250  -0.1917   0.01143   0.00394  -0.0310   0.8477   0.1492
  -3.000  -0.1660   0.01111   0.00366  -0.0306   0.8361   0.1890
  -2.750  -0.1408   0.01070   0.00342  -0.0301   0.8250   0.2507
  -2.500  -0.1161   0.01026   0.00318  -0.0296   0.8145   0.3316
  -2.250  -0.0913   0.00988   0.00300  -0.0290   0.8044   0.4100
  -2.000  -0.0668   0.00950   0.00286  -0.0283   0.7941   0.4958
  -1.750  -0.0425   0.00916   0.00276  -0.0274   0.7839   0.5813
  -1.500  -0.0186   0.00886   0.00269  -0.0263   0.7743   0.6630
  -1.250   0.0052   0.00865   0.00262  -0.0250   0.7650   0.7369
  -1.000   0.0299   0.00848   0.00258  -0.0238   0.7550   0.8024
  -0.750   0.0576   0.00839   0.00254  -0.0231   0.7454   0.8611
  -0.500   0.0921   0.00835   0.00248  -0.0240   0.7360   0.9113
  -0.250   0.1326   0.00834   0.00237  -0.0264   0.7260   0.9503
   0.000   0.1737   0.00835   0.00229  -0.0291   0.7153   0.9794
   0.250   0.2149   0.00836   0.00221  -0.0319   0.7045   1.0000
   0.500   0.2396   0.00841   0.00218  -0.0313   0.6937   1.0000
   0.750   0.2646   0.00848   0.00215  -0.0307   0.6827   1.0000
   1.000   0.2898   0.00855   0.00214  -0.0301   0.6712   1.0000
   1.250   0.3153   0.00862   0.00216  -0.0296   0.6592   1.0000
   1.500   0.3410   0.00870   0.00218  -0.0291   0.6471   1.0000
   1.750   0.3668   0.00879   0.00224  -0.0287   0.6348   1.0000
   2.000   0.3927   0.00888   0.00229  -0.0282   0.6219   1.0000
   2.250   0.4187   0.00898   0.00235  -0.0278   0.6082   1.0000
   2.500   0.4448   0.00909   0.00242  -0.0274   0.5937   1.0000
   2.750   0.4709   0.00921   0.00254  -0.0270   0.5782   1.0000
   3.000   0.4970   0.00934   0.00264  -0.0266   0.5616   1.0000
   3.250   0.5232   0.00948   0.00276  -0.0263   0.5428   1.0000
   3.500   0.5491   0.00965   0.00289  -0.0259   0.5224   1.0000
   3.750   0.5752   0.00982   0.00307  -0.0255   0.4993   1.0000
   4.000   0.6009   0.01004   0.00324  -0.0251   0.4736   1.0000
   4.250   0.6265   0.01029   0.00343  -0.0247   0.4447   1.0000
   4.500   0.6518   0.01059   0.00366  -0.0243   0.4112   1.0000
   4.750   0.6767   0.01095   0.00392  -0.0238   0.3740   1.0000
   5.000   0.7012   0.01139   0.00424  -0.0234   0.3333   1.0000
   5.250   0.7254   0.01190   0.00466  -0.0230   0.2902   1.0000
   5.500   0.7492   0.01247   0.00509  -0.0226   0.2472   1.0000
   5.750   0.7728   0.01308   0.00558  -0.0222   0.2051   1.0000
   6.000   0.7959   0.01378   0.00611  -0.0218   0.1632   1.0000
   6.250   0.8188   0.01451   0.00670  -0.0213   0.1261   1.0000
   6.500   0.8413   0.01528   0.00734  -0.0209   0.0942   1.0000
   6.750   0.8637   0.01607   0.00804  -0.0203   0.0688   1.0000
   7.000   0.8859   0.01687   0.00880  -0.0198   0.0492   1.0000
   7.250   0.9078   0.01772   0.00968  -0.0191   0.0370   1.0000
   7.500   0.9287   0.01871   0.01080  -0.0183   0.0282   1.0000
   7.750   0.9481   0.01986   0.01198  -0.0174   0.0205   1.0000
   8.000   0.9695   0.02066   0.01286  -0.0167   0.0146   1.0000
   8.250   0.9877   0.02191   0.01422  -0.0157   0.0104   1.0000
   8.500   1.0069   0.02292   0.01531  -0.0149   0.0075   1.0000
   8.750   1.0196   0.02483   0.01740  -0.0133   0.0065   1.0000
   9.000   1.0348   0.02635   0.01914  -0.0120   0.0058   1.0000
   9.250   1.0480   0.02811   0.02111  -0.0105   0.0053   1.0000
   9.500   1.0600   0.03001   0.02323  -0.0089   0.0050   1.0000
   9.750   1.0702   0.03208   0.02553  -0.0073   0.0047   1.0000
  10.000   1.0784   0.03427   0.02796  -0.0056   0.0045   1.0000
  10.250   1.0823   0.03658   0.03053  -0.0036   0.0044   1.0000
  10.500   1.0816   0.03906   0.03333  -0.0013   0.0043   1.0000
  10.750   1.0786   0.04171   0.03623   0.0004   0.0043   1.0000
  11.000   1.0724   0.04474   0.03951   0.0015   0.0041   1.0000
  11.250   1.0642   0.04826   0.04329   0.0019   0.0042   1.0000
  11.500   1.0537   0.05230   0.04758   0.0015   0.0042   1.0000
  11.750   1.0415   0.05682   0.05233   0.0003   0.0042   1.0000
  12.000   1.0274   0.06204   0.05778  -0.0019   0.0042   1.0000
  12.250   1.0107   0.06819   0.06414  -0.0051   0.0042   1.0000
  12.500   0.9933   0.07506   0.07121  -0.0093   0.0043   1.0000
  12.750   0.9745   0.08302   0.07934  -0.0144   0.0043   1.0000
  13.000   0.9554   0.09187   0.08835  -0.0202   0.0044   1.0000
  13.250   0.9330   0.10260   0.09916  -0.0271   0.0045   1.0000
  13.500   0.9097   0.11464   0.11130  -0.0342   0.0047   1.0000
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