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Davis AIRFOIL (davis-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: Davis AIRFOIL (davis-il)
Reynolds number: 1,000,000
Max Cl/Cd: 120.76 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davis-il-1000000.txt
Download as CSV file: xf-davis-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Davis AIRFOIL                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.3921   0.11935   0.11768  -0.0365   1.0000   0.0128
 -11.750  -0.3956   0.11471   0.11306  -0.0373   1.0000   0.0128
 -11.500  -0.7514   0.03595   0.03365  -0.0862   0.9941   0.0080
 -11.250  -0.7389   0.03277   0.03026  -0.0890   0.9897   0.0082
 -11.000  -0.7260   0.02909   0.02627  -0.0918   0.9863   0.0083
 -10.750  -0.7049   0.02642   0.02332  -0.0940   0.9845   0.0085
 -10.500  -0.6838   0.02459   0.02129  -0.0949   0.9818   0.0087
 -10.250  -0.6667   0.02252   0.01896  -0.0948   0.9775   0.0089
 -10.000  -0.6412   0.02099   0.01722  -0.0958   0.9753   0.0091
  -9.750  -0.6124   0.01985   0.01591  -0.0970   0.9738   0.0094
  -9.500  -0.5817   0.01897   0.01490  -0.0983   0.9727   0.0096
  -9.250  -0.5571   0.01632   0.01193  -0.0995   0.9713   0.0102
  -9.000  -0.5312   0.01564   0.01118  -0.0996   0.9682   0.0106
  -8.750  -0.5043   0.01524   0.01075  -0.0997   0.9646   0.0110
  -8.500  -0.4746   0.01463   0.01005  -0.1005   0.9621   0.0115
  -8.250  -0.4436   0.01416   0.00952  -0.1014   0.9600   0.0122
  -8.000  -0.4128   0.01357   0.00884  -0.1023   0.9579   0.0126
  -7.750  -0.3908   0.01262   0.00775  -0.1014   0.9530   0.0133
  -7.500  -0.3659   0.01200   0.00708  -0.1010   0.9480   0.0141
  -7.250  -0.3363   0.01161   0.00665  -0.1015   0.9442   0.0148
  -7.000  -0.3097   0.01127   0.00626  -0.1013   0.9391   0.0157
  -6.750  -0.2841   0.01098   0.00592  -0.1009   0.9331   0.0165
  -6.500  -0.2566   0.01039   0.00523  -0.1009   0.9282   0.0178
  -6.250  -0.2329   0.01009   0.00492  -0.1001   0.9208   0.0190
  -6.000  -0.2049   0.00984   0.00463  -0.1001   0.9147   0.0205
  -5.750  -0.1793   0.00964   0.00438  -0.0996   0.9064   0.0217
  -5.500  -0.1538   0.00917   0.00381  -0.0991   0.8975   0.0234
  -5.250  -0.1285   0.00889   0.00348  -0.0985   0.8859   0.0257
  -5.000  -0.1027   0.00869   0.00323  -0.0980   0.8741   0.0278
  -4.750  -0.0764   0.00856   0.00303  -0.0976   0.8622   0.0289
  -4.500  -0.0518   0.00820   0.00258  -0.0969   0.8486   0.0328
  -4.250  -0.0264   0.00803   0.00233  -0.0963   0.8333   0.0360
  -4.000  -0.0010   0.00790   0.00211  -0.0956   0.8171   0.0393
  -3.750   0.0234   0.00766   0.00188  -0.0949   0.8021   0.0548
  -3.500   0.0465   0.00726   0.00169  -0.0940   0.7891   0.1183
  -3.250   0.0720   0.00717   0.00161  -0.0935   0.7778   0.1403
  -3.000   0.0975   0.00710   0.00152  -0.0930   0.7671   0.1571
  -2.750   0.1232   0.00702   0.00144  -0.0925   0.7566   0.1736
  -2.500   0.1490   0.00693   0.00138  -0.0921   0.7480   0.1949
  -2.250   0.1747   0.00685   0.00134  -0.0917   0.7399   0.2245
  -2.000   0.2012   0.00678   0.00130  -0.0914   0.7329   0.2453
  -1.750   0.2273   0.00674   0.00127  -0.0910   0.7253   0.2628
  -1.500   0.2536   0.00668   0.00123  -0.0906   0.7174   0.2809
  -1.250   0.2793   0.00663   0.00120  -0.0902   0.7095   0.3055
  -1.000   0.3046   0.00647   0.00120  -0.0897   0.7008   0.3584
  -0.750   0.3295   0.00637   0.00120  -0.0891   0.6913   0.4079
  -0.500   0.3548   0.00629   0.00120  -0.0885   0.6810   0.4468
  -0.250   0.3804   0.00621   0.00119  -0.0880   0.6708   0.4841
   0.000   0.4052   0.00613   0.00119  -0.0874   0.6595   0.5248
   0.250   0.4285   0.00596   0.00119  -0.0865   0.6474   0.5945
   0.500   0.4456   0.00554   0.00124  -0.0842   0.6327   0.7628
   0.750   0.4650   0.00535   0.00130  -0.0821   0.6136   0.8687
   1.000   0.5012   0.00540   0.00141  -0.0838   0.5901   0.9405
   1.250   0.5493   0.00559   0.00150  -0.0883   0.5673   0.9652
   1.500   0.5903   0.00578   0.00160  -0.0913   0.5504   0.9776
   1.750   0.6297   0.00596   0.00170  -0.0939   0.5368   0.9878
   2.000   0.6670   0.00611   0.00179  -0.0961   0.5250   0.9939
   2.500   0.7423   0.00639   0.00194  -0.1007   0.5011   1.0000
   2.750   0.7643   0.00649   0.00201  -0.0995   0.4901   1.0000
   3.000   0.7864   0.00659   0.00209  -0.0983   0.4785   1.0000
   3.250   0.8082   0.00672   0.00217  -0.0970   0.4649   1.0000
   3.500   0.8296   0.00687   0.00226  -0.0957   0.4469   1.0000
   3.750   0.8501   0.00707   0.00236  -0.0942   0.4214   1.0000
   4.000   0.8680   0.00740   0.00252  -0.0923   0.3842   1.0000
   4.250   0.8860   0.00774   0.00271  -0.0904   0.3557   1.0000
   4.500   0.9054   0.00803   0.00291  -0.0887   0.3350   1.0000
   4.750   0.9262   0.00826   0.00308  -0.0874   0.3226   1.0000
   5.000   0.9471   0.00849   0.00326  -0.0860   0.3110   1.0000
   5.250   0.9691   0.00867   0.00342  -0.0849   0.3013   1.0000
   5.500   0.9910   0.00886   0.00359  -0.0837   0.2906   1.0000
   5.750   1.0125   0.00907   0.00376  -0.0825   0.2799   1.0000
   6.000   1.0338   0.00929   0.00394  -0.0813   0.2670   1.0000
   6.250   1.0549   0.00952   0.00413  -0.0800   0.2513   1.0000
   6.500   1.0740   0.00986   0.00436  -0.0784   0.2281   1.0000
   6.750   1.0907   0.01032   0.00467  -0.0764   0.1984   1.0000
   7.000   1.0884   0.01181   0.00555  -0.0711   0.0948   1.0000
   7.250   1.0933   0.01293   0.00633  -0.0671   0.0374   1.0000
   7.500   1.1039   0.01362   0.00690  -0.0639   0.0188   1.0000
   7.750   1.1183   0.01409   0.00739  -0.0614   0.0159   1.0000
   8.000   1.1347   0.01447   0.00781  -0.0593   0.0150   1.0000
   8.250   1.1511   0.01486   0.00825  -0.0574   0.0142   1.0000
   8.500   1.1659   0.01535   0.00878  -0.0551   0.0132   1.0000
   8.750   1.1802   0.01590   0.00936  -0.0529   0.0125   1.0000
   9.000   1.1900   0.01669   0.01024  -0.0499   0.0115   1.0000
   9.250   1.2049   0.01722   0.01082  -0.0479   0.0112   1.0000
   9.500   1.2198   0.01775   0.01139  -0.0460   0.0107   1.0000
   9.750   1.2330   0.01838   0.01208  -0.0439   0.0103   1.0000
  10.000   1.2453   0.01908   0.01282  -0.0417   0.0098   1.0000
  10.250   1.2559   0.01988   0.01368  -0.0394   0.0095   1.0000
  10.500   1.2653   0.02078   0.01463  -0.0371   0.0090   1.0000
  10.750   1.2720   0.02188   0.01581  -0.0345   0.0089   1.0000
  11.000   1.2670   0.02376   0.01781  -0.0308   0.0085   1.0000
  11.250   1.2727   0.02507   0.01920  -0.0285   0.0083   1.0000
  11.500   1.2811   0.02624   0.02044  -0.0267   0.0082   1.0000
  11.750   1.2873   0.02764   0.02192  -0.0249   0.0081   1.0000
  12.000   1.2996   0.02862   0.02295  -0.0238   0.0077   1.0000
  12.250   1.3042   0.03026   0.02467  -0.0221   0.0076   1.0000
  12.500   1.3108   0.03180   0.02628  -0.0208   0.0073   1.0000
  12.750   1.3180   0.03335   0.02789  -0.0198   0.0070   1.0000
  13.000   1.3199   0.03543   0.03007  -0.0185   0.0070   1.0000
  13.250   1.3271   0.03710   0.03179  -0.0178   0.0067   1.0000
  13.500   1.3276   0.03945   0.03422  -0.0167   0.0066   1.0000
  13.750   1.3279   0.04189   0.03674  -0.0159   0.0066   1.0000
  14.000   1.3284   0.04439   0.03932  -0.0152   0.0064   1.0000
  14.250   1.3234   0.04750   0.04250  -0.0145   0.0062   1.0000
  14.500   1.3159   0.05090   0.04601  -0.0136   0.0061   1.0000
  14.750   1.3048   0.05466   0.04988  -0.0122   0.0060   1.0000
  15.000   1.3064   0.05739   0.05271  -0.0124   0.0059   1.0000
  15.250   1.3075   0.06028   0.05570  -0.0126   0.0059   1.0000
  15.500   1.3088   0.06329   0.05882  -0.0132   0.0058   1.0000
  15.750   1.3057   0.06672   0.06235  -0.0133   0.0058   1.0000
  16.000   1.3050   0.07011   0.06585  -0.0141   0.0056   1.0000
  16.250   1.3000   0.07390   0.06977  -0.0145   0.0056   1.0000
  16.500   1.2954   0.07783   0.07382  -0.0153   0.0056   1.0000
  16.750   1.2898   0.08198   0.07809  -0.0162   0.0055   1.0000
  17.000   1.2841   0.08629   0.08252  -0.0175   0.0054   1.0000
  17.250   1.2773   0.09075   0.08709  -0.0187   0.0055   1.0000
  17.500   1.2649   0.09613   0.09262  -0.0201   0.0055   1.0000
  17.750   1.2573   0.10111   0.09772  -0.0221   0.0054   1.0000
  18.000   1.2504   0.10617   0.10289  -0.0244   0.0053   1.0000
  18.250   1.2426   0.11141   0.10825  -0.0268   0.0052   1.0000
  18.500   1.2266   0.11812   0.11513  -0.0296   0.0053   1.0000
  18.750   1.2193   0.12365   0.12076  -0.0325   0.0051   1.0000
  19.000   1.2001   0.13139   0.12868  -0.0363   0.0052   1.0000
  19.250   1.1844   0.13876   0.13620  -0.0403   0.0052   1.0000
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