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DORNIER A-5 AIRFOIL (doa5-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DORNIER A-5 AIRFOIL (doa5-il)
Reynolds number: 50,000
Max Cl/Cd: 29.86 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-doa5-il-50000.txt
Download as CSV file: xf-doa5-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DORNIER A-5 AIRFOIL                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3604   0.11399   0.10685  -0.0109   1.0000   0.4551
  -8.500  -0.6304   0.08701   0.08038  -0.0319   1.0000   0.2261
  -8.250  -0.7240   0.08294   0.07632  -0.0286   1.0000   0.2281
  -8.000  -0.7335   0.07496   0.06818  -0.0294   1.0000   0.1984
  -7.750  -0.7579   0.06970   0.06259  -0.0283   1.0000   0.1847
  -7.500  -0.7762   0.06480   0.05712  -0.0271   1.0000   0.1721
  -7.250  -0.7750   0.06061   0.05262  -0.0260   1.0000   0.1653
  -7.000  -0.7739   0.05716   0.04835  -0.0248   1.0000   0.1574
  -6.750  -0.7618   0.05405   0.04500  -0.0238   1.0000   0.1560
  -6.500  -0.7486   0.05130   0.04191  -0.0229   1.0000   0.1553
  -6.250  -0.7335   0.04880   0.03904  -0.0219   1.0000   0.1551
  -6.000  -0.7161   0.04649   0.03641  -0.0210   1.0000   0.1548
  -5.750  -0.6972   0.04438   0.03399  -0.0201   1.0000   0.1545
  -5.500  -0.6771   0.04253   0.03184  -0.0191   1.0000   0.1548
  -5.250  -0.6568   0.04104   0.02998  -0.0181   1.0000   0.1572
  -5.000  -0.6364   0.03947   0.02821  -0.0171   1.0000   0.1604
  -4.750  -0.6158   0.03804   0.02681  -0.0159   1.0000   0.1642
  -4.500  -0.5945   0.03695   0.02566  -0.0145   1.0000   0.1684
  -4.250  -0.5733   0.03613   0.02471  -0.0129   1.0000   0.1739
  -4.000  -0.5537   0.03525   0.02401  -0.0108   1.0000   0.1819
  -3.750  -0.5345   0.03472   0.02345  -0.0087   1.0000   0.1916
  -3.500  -0.5185   0.03400   0.02295  -0.0061   1.0000   0.2028
  -3.250  -0.5037   0.03315   0.02227  -0.0039   1.0000   0.2204
  -3.000  -0.4892   0.03198   0.02136  -0.0023   1.0000   0.2471
  -2.750  -0.4834   0.02929   0.02084   0.0000   1.0000   0.4144
  -2.500  -0.4950   0.03337   0.02558   0.0151   1.0000   0.6769
  -2.250  -0.5025   0.03692   0.02904   0.0285   1.0000   0.7386
  -2.000  -0.1219   0.04725   0.03795  -0.0073   1.0000   0.9796
  -1.750  -0.1071   0.04698   0.03759  -0.0072   1.0000   0.9831
  -1.500  -0.1071   0.04673   0.03729  -0.0044   1.0000   0.9822
  -1.250  -0.1037   0.04647   0.03699  -0.0023   1.0000   0.9822
  -1.000  -0.0947   0.04623   0.03669  -0.0012   1.0000   0.9834
  -0.750  -0.0873   0.04602   0.03643   0.0001   1.0000   0.9843
  -0.500  -0.0776   0.04585   0.03622   0.0010   1.0000   0.9859
  -0.250  -0.0658   0.04576   0.03609   0.0015   1.0000   0.9883
   0.000  -0.0544   0.04573   0.03602   0.0020   1.0000   0.9907
   0.250  -0.0442   0.04575   0.03601   0.0027   1.0000   0.9927
   0.500  -0.0286   0.04583   0.03605   0.0023   1.0000   0.9957
   0.750  -0.0089   0.04614   0.03633   0.0011   1.0000   0.9998
   1.000  -0.0056   0.04613   0.03632   0.0030   1.0000   1.0000
   1.250  -0.0033   0.04610   0.03629   0.0050   1.0000   1.0000
   1.500  -0.0014   0.04609   0.03628   0.0070   1.0000   1.0000
   1.750   0.0001   0.04608   0.03628   0.0090   1.0000   1.0000
   2.000   0.0010   0.04608   0.03630   0.0111   1.0000   1.0000
   2.250   0.0013   0.04610   0.03634   0.0131   1.0000   1.0000
   2.500   0.0903   0.04811   0.03837  -0.0011   0.9652   1.0000
   2.750   0.1397   0.04894   0.03921  -0.0074   0.9385   1.0000
   3.000   0.1808   0.04956   0.03986  -0.0117   0.9151   1.0000
   3.250   0.2105   0.04988   0.04022  -0.0139   0.8926   1.0000
   3.500   0.2492   0.05034   0.04072  -0.0173   0.8718   1.0000
   3.750   0.2689   0.05049   0.04091  -0.0176   0.8498   1.0000
   4.000   0.2910   0.05076   0.04123  -0.0182   0.8293   1.0000
   4.250   0.3179   0.05100   0.04152  -0.0192   0.8091   1.0000
   4.500   0.3464   0.05115   0.04173  -0.0202   0.7894   1.0000
   4.750   0.3780   0.05108   0.04172  -0.0212   0.7701   1.0000
   5.000   0.3851   0.05109   0.04176  -0.0188   0.7493   1.0000
   5.250   0.4029   0.05059   0.04131  -0.0173   0.7264   1.0000
   5.500   0.4446   0.04932   0.04010  -0.0180   0.7050   1.0000
   5.750   0.4837   0.04800   0.03886  -0.0182   0.6862   1.0000
   6.000   0.5048   0.04750   0.03843  -0.0169   0.6693   1.0000
   6.250   0.5297   0.04695   0.03795  -0.0159   0.6523   1.0000
   6.500   0.5616   0.04608   0.03718  -0.0155   0.6350   1.0000
   6.750   0.6034   0.04445   0.03568  -0.0156   0.6175   1.0000
   7.000   0.6604   0.04137   0.03276  -0.0161   0.6000   1.0000
   7.250   0.7217   0.03768   0.02923  -0.0165   0.5757   1.0000
   7.500   0.8508   0.03134   0.02286  -0.0240   0.5283   1.0000
   7.750   0.8787   0.03099   0.02231  -0.0227   0.4829   1.0000
   8.000   0.9204   0.03122   0.02216  -0.0238   0.4321   1.0000
   8.250   0.9710   0.03252   0.02299  -0.0273   0.3862   1.0000
   8.500   1.0071   0.03406   0.02423  -0.0290   0.3536   1.0000
   8.750   1.0228   0.03549   0.02571  -0.0277   0.3324   1.0000
   9.000   1.0433   0.03701   0.02723  -0.0271   0.3132   1.0000
   9.250   1.0670   0.03862   0.02883  -0.0271   0.2966   1.0000
   9.500   1.0940   0.04022   0.03041  -0.0276   0.2816   1.0000
   9.750   1.1022   0.04194   0.03239  -0.0254   0.2710   1.0000
  10.000   1.1201   0.04385   0.03441  -0.0248   0.2606   1.0000
  10.250   1.1538   0.04558   0.03601  -0.0263   0.2490   1.0000
  10.500   1.1449   0.04787   0.03875  -0.0221   0.2433   1.0000
  10.750   1.1723   0.04975   0.04064  -0.0227   0.2342   1.0000
  11.000   1.1644   0.05237   0.04357  -0.0190   0.2296   1.0000
  11.250   1.1503   0.05504   0.04654  -0.0147   0.2256   1.0000
  11.500   1.1893   0.05714   0.04853  -0.0169   0.2164   1.0000
  11.750   1.1601   0.06037   0.05211  -0.0114   0.2150   1.0000
  12.000   1.1271   0.06425   0.05629  -0.0066   0.2140   1.0000
  12.250   1.0879   0.06903   0.06134  -0.0028   0.2139   1.0000
  12.500   1.0419   0.07517   0.06769  -0.0004   0.2147   1.0000
  12.750   0.9898   0.08328   0.07595  -0.0001   0.2162   1.0000
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