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SD8040 (10%) (sd8040-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: SD8040 (10%) (sd8040-il)
Reynolds number: 500,000
Max Cl/Cd: 84.69 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd8040-il-500000-n5.txt
Download as CSV file: xf-sd8040-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD8040 (10%)                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6809   0.03970   0.03684  -0.0627   1.0000   0.0085
  -9.750  -0.6956   0.03600   0.03290  -0.0611   1.0000   0.0085
  -9.500  -0.6836   0.03089   0.02731  -0.0648   0.9930   0.0086
  -9.250  -0.6613   0.02815   0.02427  -0.0669   0.9881   0.0087
  -9.000  -0.6351   0.02590   0.02176  -0.0690   0.9849   0.0089
  -8.750  -0.6101   0.02412   0.01975  -0.0701   0.9802   0.0090
  -8.500  -0.5833   0.02262   0.01803  -0.0711   0.9759   0.0093
  -8.250  -0.5545   0.02125   0.01643  -0.0723   0.9726   0.0096
  -8.000  -0.5304   0.01984   0.01479  -0.0724   0.9664   0.0098
  -7.750  -0.5039   0.01851   0.01323  -0.0728   0.9615   0.0100
  -7.500  -0.4785   0.01739   0.01192  -0.0727   0.9559   0.0102
  -7.250  -0.4539   0.01642   0.01078  -0.0724   0.9496   0.0104
  -7.000  -0.4279   0.01561   0.00981  -0.0722   0.9445   0.0106
  -6.750  -0.4038   0.01491   0.00899  -0.0715   0.9374   0.0108
  -6.500  -0.3789   0.01420   0.00817  -0.0710   0.9314   0.0110
  -6.250  -0.3544   0.01351   0.00741  -0.0705   0.9251   0.0114
  -6.000  -0.3291   0.01300   0.00686  -0.0700   0.9183   0.0117
  -5.750  -0.3035   0.01255   0.00634  -0.0695   0.9123   0.0121
  -5.500  -0.2777   0.01211   0.00584  -0.0690   0.9049   0.0126
  -5.250  -0.2518   0.01171   0.00536  -0.0685   0.8984   0.0130
  -5.000  -0.2255   0.01135   0.00495  -0.0681   0.8908   0.0137
  -4.750  -0.1994   0.01097   0.00451  -0.0677   0.8834   0.0145
  -4.500  -0.1728   0.01066   0.00418  -0.0673   0.8753   0.0155
  -4.250  -0.1462   0.01038   0.00383  -0.0669   0.8668   0.0165
  -4.000  -0.1194   0.01007   0.00348  -0.0666   0.8575   0.0179
  -3.750  -0.0925   0.00983   0.00319  -0.0662   0.8484   0.0199
  -3.500  -0.0654   0.00958   0.00292  -0.0659   0.8378   0.0233
  -3.250  -0.0383   0.00936   0.00268  -0.0656   0.8271   0.0295
  -3.000  -0.0114   0.00914   0.00246  -0.0652   0.8157   0.0400
  -2.750   0.0157   0.00894   0.00227  -0.0650   0.8030   0.0536
  -2.500   0.0428   0.00875   0.00210  -0.0647   0.7894   0.0715
  -2.250   0.0698   0.00855   0.00196  -0.0644   0.7750   0.1004
  -2.000   0.0965   0.00829   0.00183  -0.0642   0.7599   0.1470
  -1.750   0.1234   0.00809   0.00171  -0.0640   0.7441   0.1930
  -1.500   0.1501   0.00788   0.00162  -0.0637   0.7276   0.2471
  -1.250   0.1767   0.00767   0.00154  -0.0635   0.7106   0.3130
  -1.000   0.2032   0.00747   0.00148  -0.0632   0.6933   0.3848
  -0.750   0.2296   0.00728   0.00145  -0.0629   0.6758   0.4608
  -0.500   0.2559   0.00712   0.00144  -0.0626   0.6577   0.5326
  -0.250   0.2820   0.00699   0.00144  -0.0621   0.6393   0.6023
   0.000   0.3080   0.00691   0.00146  -0.0616   0.6198   0.6623
   0.250   0.3338   0.00686   0.00150  -0.0610   0.6002   0.7156
   0.500   0.3592   0.00685   0.00154  -0.0603   0.5804   0.7643
   0.750   0.3841   0.00685   0.00159  -0.0594   0.5607   0.8108
   1.000   0.4082   0.00686   0.00165  -0.0584   0.5412   0.8554
   1.250   0.4320   0.00689   0.00170  -0.0571   0.5219   0.9012
   1.500   0.4608   0.00697   0.00175  -0.0570   0.5015   0.9464
   1.750   0.4978   0.00711   0.00178  -0.0589   0.4792   0.9778
   2.000   0.5333   0.00728   0.00183  -0.0606   0.4567   1.0000
   2.250   0.5589   0.00747   0.00191  -0.0601   0.4366   1.0000
   2.500   0.5847   0.00766   0.00200  -0.0597   0.4171   1.0000
   2.750   0.6106   0.00785   0.00210  -0.0593   0.3975   1.0000
   3.000   0.6366   0.00806   0.00221  -0.0590   0.3779   1.0000
   3.250   0.6625   0.00828   0.00233  -0.0586   0.3592   1.0000
   3.500   0.6884   0.00851   0.00247  -0.0582   0.3401   1.0000
   3.750   0.7144   0.00873   0.00261  -0.0579   0.3225   1.0000
   4.000   0.7404   0.00896   0.00276  -0.0576   0.3052   1.0000
   4.250   0.7663   0.00921   0.00293  -0.0572   0.2876   1.0000
   4.500   0.7920   0.00946   0.00311  -0.0569   0.2703   1.0000
   4.750   0.8177   0.00972   0.00330  -0.0565   0.2542   1.0000
   5.000   0.8434   0.00999   0.00350  -0.0562   0.2388   1.0000
   5.250   0.8689   0.01027   0.00373  -0.0558   0.2231   1.0000
   5.500   0.8943   0.01056   0.00395  -0.0554   0.2089   1.0000
   5.750   0.9195   0.01086   0.00420  -0.0550   0.1940   1.0000
   6.000   0.9446   0.01117   0.00446  -0.0546   0.1804   1.0000
   6.250   0.9694   0.01150   0.00473  -0.0541   0.1669   1.0000
   6.500   0.9941   0.01185   0.00502  -0.0537   0.1534   1.0000
   6.750   1.0184   0.01221   0.00534  -0.0532   0.1401   1.0000
   7.000   1.0426   0.01259   0.00566  -0.0527   0.1281   1.0000
   7.250   1.0666   0.01297   0.00600  -0.0521   0.1177   1.0000
   7.500   1.0907   0.01333   0.00635  -0.0516   0.1080   1.0000
   7.750   1.1144   0.01372   0.00671  -0.0510   0.0993   1.0000
   8.000   1.1377   0.01414   0.00711  -0.0504   0.0911   1.0000
   8.250   1.1607   0.01456   0.00751  -0.0498   0.0829   1.0000
   8.500   1.1836   0.01498   0.00793  -0.0491   0.0757   1.0000
   8.750   1.2057   0.01546   0.00839  -0.0483   0.0688   1.0000
   9.000   1.2279   0.01592   0.00885  -0.0476   0.0626   1.0000
   9.250   1.2495   0.01640   0.00934  -0.0467   0.0573   1.0000
   9.500   1.2702   0.01694   0.00987  -0.0458   0.0515   1.0000
   9.750   1.2911   0.01743   0.01039  -0.0449   0.0474   1.0000
  10.000   1.3106   0.01802   0.01097  -0.0438   0.0433   1.0000
  10.250   1.3303   0.01855   0.01155  -0.0427   0.0402   1.0000
  10.500   1.3485   0.01917   0.01219  -0.0415   0.0369   1.0000
  10.750   1.3663   0.01977   0.01283  -0.0401   0.0344   1.0000
  11.000   1.3828   0.02037   0.01348  -0.0386   0.0323   1.0000
  11.250   1.3960   0.02108   0.01422  -0.0366   0.0303   1.0000
  11.500   1.4094   0.02174   0.01495  -0.0347   0.0288   1.0000
  11.750   1.4223   0.02245   0.01572  -0.0328   0.0273   1.0000
  12.000   1.4335   0.02327   0.01659  -0.0308   0.0260   1.0000
  12.250   1.4428   0.02424   0.01760  -0.0287   0.0247   1.0000
  12.500   1.4540   0.02511   0.01857  -0.0269   0.0239   1.0000
  12.750   1.4641   0.02608   0.01963  -0.0252   0.0229   1.0000
  13.000   1.4729   0.02719   0.02080  -0.0235   0.0218   1.0000
  13.250   1.4795   0.02849   0.02218  -0.0218   0.0211   1.0000
  13.500   1.4846   0.02998   0.02374  -0.0202   0.0203   1.0000
  13.750   1.4917   0.03138   0.02524  -0.0189   0.0197   1.0000
  14.000   1.4974   0.03296   0.02693  -0.0177   0.0191   1.0000
  14.250   1.5018   0.03473   0.02881  -0.0167   0.0185   1.0000
  14.500   1.5047   0.03674   0.03092  -0.0158   0.0180   1.0000
  14.750   1.5060   0.03902   0.03329  -0.0152   0.0174   1.0000
  15.000   1.5048   0.04171   0.03606  -0.0149   0.0169   1.0000
  15.250   1.5026   0.04466   0.03912  -0.0149   0.0166   1.0000
  15.500   1.5023   0.04755   0.04214  -0.0151   0.0162   1.0000
  15.750   1.5001   0.05082   0.04554  -0.0157   0.0158   1.0000
  16.000   1.4960   0.05448   0.04933  -0.0166   0.0155   1.0000
  16.250   1.4897   0.05863   0.05362  -0.0179   0.0152   1.0000
  16.500   1.4823   0.06315   0.05827  -0.0195   0.0150   1.0000
  16.750   1.4734   0.06808   0.06333  -0.0215   0.0147   1.0000
  17.000   1.4628   0.07348   0.06887  -0.0238   0.0145   1.0000
  17.250   1.4499   0.07942   0.07494  -0.0266   0.0144   1.0000
  17.500   1.4364   0.08567   0.08132  -0.0296   0.0142   1.0000
  17.750   1.4209   0.09247   0.08826  -0.0330   0.0141   1.0000
  18.000   1.4044   0.09962   0.09553  -0.0367   0.0139   1.0000
  18.250   1.3877   0.10694   0.10299  -0.0406   0.0138   1.0000
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