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MH 20 9.01% (mh20-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: MH 20 9.01% (mh20-il)
Reynolds number: 500,000
Max Cl/Cd: 91.55 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-mh20-il-500000.txt
Download as CSV file: xf-mh20-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MH 20  9.01%                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5007   0.08336   0.08146  -0.0075   1.0000   0.0153
  -8.000  -0.5029   0.07860   0.07674  -0.0113   1.0000   0.0153
  -7.750  -0.5076   0.07368   0.07185  -0.0158   1.0000   0.0153
  -7.500  -0.5055   0.06814   0.06629  -0.0200   1.0000   0.0153
  -6.750  -0.5226   0.04752   0.04489  -0.0250   0.8727   0.0163
  -6.500  -0.5168   0.04354   0.04067  -0.0245   0.8580   0.0168
  -6.250  -0.5045   0.04086   0.03782  -0.0240   0.8457   0.0175
  -6.000  -0.4905   0.03809   0.03482  -0.0233   0.8348   0.0182
  -5.750  -0.4744   0.03518   0.03166  -0.0227   0.8245   0.0192
  -5.500  -0.4569   0.03217   0.02830  -0.0217   0.8157   0.0206
  -5.250  -0.4375   0.02942   0.02519  -0.0205   0.8079   0.0226
  -5.000  -0.4083   0.03022   0.02568  -0.0194   0.7993   0.0254
  -4.750  -0.3981   0.02363   0.01845  -0.0177   0.7930   0.0274
  -4.500  -0.3735   0.01795   0.01217  -0.0149   0.7866   0.0120
  -4.000  -0.3235   0.01370   0.00723  -0.0122   0.7741   0.0089
  -3.750  -0.2981   0.01277   0.00612  -0.0114   0.7685   0.0085
  -3.500  -0.2725   0.01197   0.00521  -0.0107   0.7623   0.0084
  -3.250  -0.2470   0.01126   0.00436  -0.0099   0.7565   0.0085
  -3.000  -0.2208   0.01072   0.00366  -0.0093   0.7507   0.0089
  -2.750  -0.1939   0.01030   0.00307  -0.0088   0.7446   0.0105
  -2.500  -0.1693   0.00954   0.00255  -0.0081   0.7393   0.0815
  -2.250  -0.1443   0.00895   0.00236  -0.0078   0.7332   0.1799
  -2.000  -0.1196   0.00846   0.00221  -0.0074   0.7281   0.2802
  -1.750  -0.0982   0.00757   0.00208  -0.0065   0.7225   0.4792
  -1.500  -0.0790   0.00680   0.00197  -0.0047   0.7171   0.6670
  -1.250  -0.0585   0.00618   0.00193  -0.0027   0.7123   0.8364
  -1.000   0.0155   0.00617   0.00205  -0.0121   0.7066   0.9458
  -0.750   0.0531   0.00634   0.00210  -0.0139   0.7015   0.9694
  -0.500   0.0968   0.00646   0.00214  -0.0172   0.6959   0.9825
  -0.250   0.1451   0.00652   0.00209  -0.0215   0.6902   0.9913
   0.000   0.1914   0.00653   0.00202  -0.0255   0.6846   0.9978
   0.250   0.2253   0.00650   0.00194  -0.0269   0.6783   1.0000
   0.500   0.2505   0.00652   0.00188  -0.0264   0.6730   1.0000
   0.750   0.2761   0.00650   0.00185  -0.0260   0.6662   1.0000
   1.000   0.3016   0.00652   0.00181  -0.0256   0.6604   1.0000
   1.250   0.3276   0.00652   0.00180  -0.0252   0.6534   1.0000
   1.500   0.3533   0.00654   0.00177  -0.0248   0.6470   1.0000
   1.750   0.3794   0.00654   0.00179  -0.0245   0.6393   1.0000
   2.000   0.4053   0.00658   0.00178  -0.0241   0.6321   1.0000
   2.250   0.4315   0.00658   0.00180  -0.0237   0.6235   1.0000
   2.500   0.4576   0.00661   0.00181  -0.0234   0.6147   1.0000
   2.750   0.4836   0.00665   0.00183  -0.0230   0.6053   1.0000
   3.000   0.5098   0.00668   0.00189  -0.0227   0.5941   1.0000
   3.250   0.5359   0.00672   0.00194  -0.0223   0.5814   1.0000
   3.500   0.5621   0.00677   0.00199  -0.0220   0.5671   1.0000
   3.750   0.5882   0.00684   0.00205  -0.0217   0.5502   1.0000
   4.000   0.6143   0.00693   0.00216  -0.0213   0.5294   1.0000
   4.250   0.6401   0.00707   0.00225  -0.0210   0.5043   1.0000
   4.500   0.6656   0.00727   0.00238  -0.0206   0.4758   1.0000
   4.750   0.6908   0.00755   0.00256  -0.0202   0.4445   1.0000
   5.000   0.7158   0.00786   0.00278  -0.0199   0.4111   1.0000
   5.250   0.7404   0.00823   0.00304  -0.0195   0.3753   1.0000
   5.500   0.7642   0.00872   0.00334  -0.0191   0.3258   1.0000
   5.750   0.7871   0.00935   0.00374  -0.0186   0.2641   1.0000
   6.000   0.8087   0.01015   0.00420  -0.0181   0.1941   1.0000
   6.250   0.8293   0.01104   0.00476  -0.0174   0.1278   1.0000
   6.500   0.8469   0.01234   0.00557  -0.0164   0.0486   1.0000
   6.750   0.8631   0.01391   0.00697  -0.0147   0.0072   1.0000
   7.000   0.8837   0.01469   0.00788  -0.0135   0.0061   1.0000
   7.250   0.9031   0.01557   0.00888  -0.0123   0.0056   1.0000
   7.500   0.9204   0.01663   0.01008  -0.0107   0.0053   1.0000
   7.750   0.9357   0.01786   0.01144  -0.0088   0.0052   1.0000
   8.000   0.9500   0.01915   0.01286  -0.0069   0.0052   1.0000
   8.250   0.9628   0.02067   0.01452  -0.0047   0.0052   1.0000
   8.500   0.9756   0.02240   0.01641  -0.0024   0.0054   1.0000
   8.750   0.9882   0.02477   0.01900  -0.0001   0.0058   1.0000
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