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DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
Reynolds number: 200,000
Max Cl/Cd: 64.5 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-defcnd2-il-200000-n5.txt
Download as CSV file: xf-defcnd2-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DEFIANT CANARD BL110 AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3125   0.10109   0.09765  -0.0510   1.0000   0.0198
 -10.750  -0.3201   0.09594   0.09257  -0.0528   1.0000   0.0199
 -10.500  -0.3192   0.09131   0.08798  -0.0551   0.9909   0.0198
 -10.250  -0.3126   0.08579   0.08247  -0.0601   0.9776   0.0196
 -10.000  -0.3047   0.08007   0.07674  -0.0660   0.9646   0.0193
  -9.750  -0.3015   0.07240   0.06906  -0.0742   0.9508   0.0190
  -9.500  -0.3166   0.05778   0.05429  -0.0914   0.9312   0.0185
  -9.000  -0.3565   0.04445   0.04025  -0.0974   0.8892   0.0180
  -8.750  -0.3691   0.04025   0.03565  -0.0952   0.8748   0.0179
  -8.500  -0.3759   0.03654   0.03150  -0.0924   0.8635   0.0180
  -8.250  -0.3761   0.03351   0.02804  -0.0896   0.8535   0.0181
  -8.000  -0.3697   0.03091   0.02500  -0.0872   0.8455   0.0183
  -7.750  -0.3597   0.02865   0.02233  -0.0849   0.8371   0.0186
  -7.500  -0.3453   0.02672   0.01999  -0.0831   0.8303   0.0189
  -7.250  -0.3284   0.02523   0.01812  -0.0815   0.8230   0.0195
  -7.000  -0.3089   0.02385   0.01643  -0.0802   0.8172   0.0201
  -6.750  -0.2886   0.02277   0.01527  -0.0793   0.8102   0.0209
  -6.500  -0.2666   0.02182   0.01416  -0.0784   0.8035   0.0215
  -6.250  -0.2442   0.02084   0.01303  -0.0775   0.7966   0.0220
  -6.000  -0.2213   0.01994   0.01198  -0.0766   0.7894   0.0226
  -5.750  -0.1982   0.01911   0.01102  -0.0757   0.7824   0.0232
  -5.500  -0.1752   0.01837   0.01015  -0.0748   0.7750   0.0240
  -5.250  -0.1521   0.01771   0.00938  -0.0738   0.7684   0.0247
  -5.000  -0.1302   0.01705   0.00868  -0.0728   0.7606   0.0260
  -4.750  -0.1074   0.01656   0.00815  -0.0719   0.7531   0.0276
  -4.500  -0.0849   0.01610   0.00762  -0.0709   0.7441   0.0293
  -4.250  -0.0623   0.01565   0.00709  -0.0699   0.7352   0.0306
  -4.000  -0.0397   0.01521   0.00656  -0.0688   0.7261   0.0324
  -3.750  -0.0171   0.01482   0.00614  -0.0678   0.7152   0.0352
  -3.500   0.0063   0.01449   0.00575  -0.0668   0.7042   0.0402
  -3.250   0.0293   0.01413   0.00536  -0.0658   0.6934   0.0498
  -3.000   0.0517   0.01373   0.00501  -0.0648   0.6816   0.0715
  -2.750   0.0740   0.01336   0.00473  -0.0638   0.6688   0.1065
  -2.500   0.0957   0.01298   0.00449  -0.0627   0.6551   0.1597
  -2.250   0.1150   0.01245   0.00426  -0.0613   0.6408   0.2512
  -2.000   0.1306   0.01174   0.00405  -0.0592   0.6263   0.3954
  -1.750   0.1412   0.01099   0.00403  -0.0557   0.6131   0.5947
  -1.500   0.1605   0.01083   0.00406  -0.0536   0.5992   0.6962
  -1.250   0.1834   0.01081   0.00404  -0.0522   0.5859   0.7392
  -1.000   0.2070   0.01083   0.00402  -0.0510   0.5736   0.7757
  -0.750   0.2318   0.01088   0.00403  -0.0500   0.5622   0.8071
  -0.500   0.2580   0.01096   0.00405  -0.0494   0.5515   0.8322
  -0.250   0.2856   0.01108   0.00410  -0.0490   0.5417   0.8605
   0.250   0.3515   0.01147   0.00431  -0.0505   0.5196   0.9086
   0.500   0.3851   0.01163   0.00436  -0.0517   0.5091   0.9190
   0.750   0.4188   0.01180   0.00440  -0.0530   0.4992   0.9272
   1.000   0.4509   0.01192   0.00444  -0.0540   0.4897   0.9363
   1.250   0.4862   0.01207   0.00450  -0.0557   0.4807   0.9425
   1.500   0.5197   0.01222   0.00456  -0.0571   0.4716   0.9500
   1.750   0.5541   0.01236   0.00462  -0.0587   0.4625   0.9563
   2.000   0.5889   0.01252   0.00469  -0.0604   0.4537   0.9621
   2.250   0.6212   0.01267   0.00478  -0.0615   0.4443   0.9695
   2.500   0.6567   0.01283   0.00486  -0.0635   0.4362   0.9748
   2.750   0.6888   0.01300   0.00496  -0.0647   0.4284   0.9821
   3.000   0.7249   0.01315   0.00506  -0.0668   0.4212   0.9871
   3.250   0.7590   0.01332   0.00517  -0.0685   0.4143   0.9931
   3.500   0.7941   0.01350   0.00529  -0.0705   0.4088   0.9984
   3.750   0.8183   0.01365   0.00543  -0.0701   0.4041   1.0000
   4.000   0.8354   0.01381   0.00555  -0.0683   0.4000   1.0000
   4.250   0.8526   0.01400   0.00569  -0.0665   0.3963   1.0000
   4.500   0.8710   0.01418   0.00587  -0.0649   0.3929   1.0000
   4.750   0.8898   0.01437   0.00605  -0.0634   0.3893   1.0000
   5.000   0.9087   0.01458   0.00624  -0.0619   0.3859   1.0000
   5.250   0.9276   0.01481   0.00644  -0.0604   0.3828   1.0000
   5.500   0.9470   0.01505   0.00667  -0.0590   0.3799   1.0000
   5.750   0.9671   0.01526   0.00692  -0.0577   0.3768   1.0000
   6.000   0.9870   0.01550   0.00718  -0.0564   0.3736   1.0000
   6.250   1.0069   0.01576   0.00744  -0.0552   0.3706   1.0000
   6.500   1.0270   0.01604   0.00772  -0.0539   0.3677   1.0000
   6.750   1.0475   0.01634   0.00801  -0.0528   0.3649   1.0000
   7.000   1.0676   0.01659   0.00833  -0.0516   0.3618   1.0000
   7.250   1.0874   0.01686   0.00866  -0.0503   0.3584   1.0000
   7.500   1.1074   0.01717   0.00900  -0.0491   0.3552   1.0000
   7.750   1.1282   0.01751   0.00934  -0.0481   0.3522   1.0000
   8.000   1.1489   0.01784   0.00971  -0.0471   0.3493   1.0000
   8.250   1.1680   0.01814   0.01013  -0.0458   0.3461   1.0000
   8.500   1.1875   0.01847   0.01054  -0.0446   0.3430   1.0000
   8.750   1.2072   0.01881   0.01094  -0.0435   0.3399   1.0000
   9.000   1.2284   0.01920   0.01135  -0.0426   0.3371   1.0000
   9.250   1.2468   0.01957   0.01180  -0.0413   0.3335   1.0000
   9.500   1.2582   0.01987   0.01225  -0.0387   0.3284   1.0000
   9.750   1.2700   0.02020   0.01262  -0.0362   0.3228   1.0000
  10.000   1.2810   0.02055   0.01306  -0.0336   0.3171   1.0000
  10.250   1.2917   0.02092   0.01356  -0.0312   0.3109   1.0000
  10.500   1.3054   0.02133   0.01404  -0.0293   0.3066   1.0000
  10.750   1.3154   0.02175   0.01464  -0.0270   0.2986   1.0000
  11.000   1.3266   0.02224   0.01520  -0.0249   0.2927   1.0000
  11.250   1.3358   0.02278   0.01587  -0.0228   0.2831   1.0000
  11.500   1.3437   0.02345   0.01659  -0.0206   0.2740   1.0000
  11.750   1.3480   0.02434   0.01747  -0.0182   0.2636   1.0000
  12.000   1.3510   0.02545   0.01857  -0.0160   0.2532   1.0000
  12.250   1.3505   0.02689   0.02000  -0.0136   0.2397   1.0000
  12.500   1.3555   0.02817   0.02134  -0.0119   0.2301   1.0000
  12.750   1.3537   0.02994   0.02312  -0.0100   0.2124   1.0000
  13.000   1.3450   0.03234   0.02541  -0.0079   0.1725   1.0000
  13.250   1.3307   0.03538   0.02830  -0.0059   0.1522   1.0000
  13.500   1.3128   0.03900   0.03183  -0.0043   0.1318   1.0000
  13.750   1.3001   0.04247   0.03528  -0.0032   0.1177   1.0000
  14.000   1.2884   0.04608   0.03890  -0.0026   0.1060   1.0000
  14.250   1.2787   0.04970   0.04256  -0.0023   0.0963   1.0000
  14.500   1.2658   0.05389   0.04678  -0.0024   0.0860   1.0000
  15.000   1.2459   0.06204   0.05504  -0.0031   0.0719   1.0000
  15.250   1.2346   0.06644   0.05949  -0.0037   0.0652   1.0000
  15.500   1.2207   0.07127   0.06435  -0.0045   0.0573   1.0000
  15.750   1.2144   0.07523   0.06840  -0.0053   0.0530   1.0000
  16.250   1.1938   0.08442   0.07768  -0.0073   0.0404   1.0000
  16.500   1.1845   0.08901   0.08230  -0.0084   0.0344   1.0000
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