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DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il)
Reynolds number: 50,000
Max Cl/Cd: 12.52 at α=-0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-davis-corrected-il-50000.txt
Download as CSV file: xf-davis-corrected-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DAVIS BASIC B-24 WING 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3610   0.10914   0.10205  -0.0106   1.0000   0.3587
  -9.500  -0.5340   0.07657   0.06974  -0.0419   1.0000   0.1850
  -9.250  -0.5505   0.07173   0.06491  -0.0417   1.0000   0.1831
  -9.000  -0.5705   0.06706   0.06026  -0.0409   1.0000   0.1817
  -8.750  -0.5941   0.06254   0.05572  -0.0393   1.0000   0.1801
  -8.500  -0.6184   0.05854   0.05163  -0.0366   1.0000   0.1789
  -8.250  -0.6420   0.05532   0.04832  -0.0328   1.0000   0.1785
  -8.000  -0.6663   0.05306   0.04597  -0.0278   1.0000   0.1782
  -7.750  -0.6898   0.05129   0.04407  -0.0226   1.0000   0.1783
  -7.500  -0.7077   0.04944   0.04202  -0.0181   1.0000   0.1791
  -7.250  -0.7208   0.04743   0.03973  -0.0142   1.0000   0.1807
  -7.000  -0.7304   0.04533   0.03721  -0.0107   1.0000   0.1832
  -6.750  -0.7296   0.04349   0.03522  -0.0082   1.0000   0.1869
  -6.500  -0.7149   0.04215   0.03386  -0.0075   0.9975   0.1932
  -6.250  -0.6764   0.03958   0.03082  -0.0114   0.9840   0.2047
  -6.000  -0.6364   0.03769   0.02856  -0.0149   0.9706   0.2192
  -5.750  -0.5963   0.03617   0.02688  -0.0180   0.9570   0.2362
  -5.500  -0.5579   0.03491   0.02561  -0.0206   0.9438   0.2556
  -5.250  -0.5200   0.03388   0.02462  -0.0230   0.9309   0.2796
  -5.000  -0.4784   0.03283   0.02360  -0.0258   0.9190   0.3104
  -4.750  -0.4440   0.03203   0.02288  -0.0272   0.9065   0.3451
  -4.500  -0.4156   0.03145   0.02248  -0.0274   0.8941   0.3829
  -4.250  -0.3767   0.03083   0.02209  -0.0290   0.8835   0.4357
  -4.000  -0.3494   0.03048   0.02198  -0.0285   0.8717   0.4884
  -3.750  -0.3263   0.03037   0.02213  -0.0270   0.8604   0.5431
  -3.500  -0.2852   0.03030   0.02233  -0.0275   0.8511   0.6140
  -3.250  -0.2671   0.03072   0.02296  -0.0245   0.8394   0.6645
  -3.000  -0.2064   0.03137   0.02371  -0.0262   0.8317   0.7335
  -2.750  -0.1829   0.03231   0.02464  -0.0239   0.8198   0.7785
  -2.500  -0.0603   0.03374   0.02574  -0.0346   0.8117   0.8331
  -2.250   0.0444   0.03458   0.02627  -0.0454   0.8005   0.8731
  -2.000   0.1505   0.03459   0.02596  -0.0576   0.7904   0.9089
  -1.750   0.2389   0.03408   0.02520  -0.0681   0.7796   0.9416
  -1.500   0.3150   0.03354   0.02449  -0.0782   0.7679   0.9721
  -1.250   0.3992   0.03209   0.02280  -0.0893   0.7583   1.0000
  -1.000   0.4019   0.03291   0.02362  -0.0883   0.7476   1.0000
  -0.750   0.4142   0.03309   0.02368  -0.0870   0.7404   1.0000
  -0.500   0.4132   0.03423   0.02482  -0.0854   0.7305   1.0000
  -0.250   0.4236   0.03466   0.02516  -0.0838   0.7233   1.0000
   0.000   0.4191   0.03603   0.02651  -0.0815   0.7149   1.0000
   0.250   0.4215   0.03697   0.02741  -0.0793   0.7074   1.0000
   0.500   0.4292   0.03774   0.02810  -0.0773   0.7011   1.0000
   0.750   0.4026   0.03996   0.03032  -0.0726   0.6931   1.0000
   1.000   0.4074   0.04089   0.03119  -0.0701   0.6872   1.0000
   1.250   0.3963   0.04251   0.03275  -0.0663   0.6817   1.0000
   1.500   0.3458   0.04511   0.03530  -0.0584   0.6765   1.0000
   1.750   0.3194   0.04682   0.03692  -0.0524   0.6723   1.0000
   2.000   0.3262   0.04803   0.03805  -0.0503   0.6681   1.0000
   2.250   0.3271   0.04953   0.03945  -0.0476   0.6646   1.0000
   2.500   0.2951   0.05160   0.04142  -0.0418   0.6633   1.0000
   2.750   0.2805   0.05347   0.04321  -0.0382   0.6625   1.0000
   3.000   0.2769   0.05537   0.04503  -0.0360   0.6632   1.0000
   3.250   0.2799   0.05731   0.04691  -0.0347   0.6644   1.0000
   3.500   0.0965   0.06081   0.05048  -0.0220   0.8387   1.0000
   3.750   0.1272   0.06373   0.05332  -0.0242   0.8310   1.0000
   4.000   0.1405   0.06465   0.05419  -0.0234   0.8161   1.0000
   4.250   0.1514   0.06581   0.05529  -0.0224   0.8028   1.0000
   4.500   0.1850   0.06908   0.05851  -0.0249   0.7945   1.0000
   4.750   0.1918   0.06962   0.05902  -0.0233   0.7803   1.0000
   5.000   0.2022   0.07104   0.06041  -0.0224   0.7692   1.0000
   5.250   0.2355   0.07412   0.06346  -0.0246   0.7592   1.0000
   5.500   0.2371   0.07464   0.06395  -0.0225   0.7459   1.0000
   5.750   0.2710   0.07837   0.06767  -0.0249   0.7394   1.0000
   6.000   0.2718   0.07860   0.06789  -0.0227   0.7252   1.0000
   6.250   0.2818   0.08030   0.06957  -0.0221   0.7152   1.0000
   6.500   0.3081   0.08293   0.07222  -0.0232   0.7049   1.0000
   6.750   0.3095   0.08400   0.07327  -0.0216   0.6943   1.0000
   7.000   0.3423   0.08745   0.07676  -0.0235   0.6853   1.0000
   7.250   0.3386   0.08797   0.07727  -0.0214   0.6732   1.0000
   7.500   0.3752   0.09216   0.08150  -0.0238   0.6661   1.0000
   7.750   0.3667   0.09217   0.08151  -0.0214   0.6533   1.0000
   8.000   0.4019   0.09662   0.08601  -0.0236   0.6468   1.0000
   8.250   0.3953   0.09660   0.08601  -0.0214   0.6333   1.0000
   8.500   0.4125   0.09966   0.08910  -0.0219   0.6265   1.0000
   8.750   0.4238   0.10134   0.09082  -0.0216   0.6136   1.0000
   9.000   0.4278   0.10325   0.09277  -0.0210   0.6044   1.0000
   9.250   0.4537   0.10653   0.09612  -0.0220   0.5940   1.0000
   9.500   0.4498   0.10773   0.09734  -0.0208   0.5830   1.0000
   9.750   0.4881   0.11270   0.10242  -0.0229   0.5743   1.0000
  10.000   0.4753   0.11272   0.10245  -0.0211   0.5614   1.0000
  10.250   0.4893   0.11592   0.10572  -0.0215   0.5529   1.0000
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