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DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
Reynolds number: 100,000
Max Cl/Cd: 41.67 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-defcnd2-il-100000.txt
Download as CSV file: xf-defcnd2-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3759   0.10251   0.09860  -0.0343   1.0000   0.1145
  -8.500  -0.4138   0.10137   0.09758  -0.0339   1.0000   0.1151
  -8.250  -0.4542   0.09812   0.09436  -0.0403   0.9939   0.1156
  -8.000  -0.3829   0.09369   0.08993  -0.0338   0.9950   0.1208
  -7.750  -0.3783   0.08901   0.08526  -0.0409   0.9866   0.1274
  -7.500  -0.4167   0.08227   0.07835  -0.0544   0.9706   0.1314
  -7.250  -0.3629   0.07947   0.07569  -0.0519   0.9700   0.1393
  -7.000  -0.3843   0.07355   0.06951  -0.0606   0.9553   0.1469
  -6.750  -0.3525   0.07093   0.06698  -0.0597   0.9490   0.1571
  -6.500  -0.3352   0.06662   0.06261  -0.0631   0.9413   0.1672
  -6.250  -0.3331   0.06307   0.05891  -0.0646   0.9296   0.1795
  -5.750  -0.3154   0.04781   0.04176  -0.0685   0.9101   0.1005
  -5.500  -0.3012   0.04206   0.03569  -0.0669   0.9003   0.0817
  -5.250  -0.2681   0.03746   0.03009  -0.0674   0.8949   0.0717
  -5.000  -0.2464   0.03498   0.02725  -0.0663   0.8844   0.0708
  -4.750  -0.2013   0.03256   0.02425  -0.0688   0.8799   0.0726
  -4.500  -0.1746   0.03091   0.02224  -0.0681   0.8694   0.0736
  -4.250  -0.1276   0.02812   0.01929  -0.0710   0.8649   0.0758
  -4.000  -0.0972   0.02676   0.01788  -0.0710   0.8546   0.0795
  -3.750  -0.0523   0.02517   0.01615  -0.0732   0.8489   0.0882
  -3.500  -0.0276   0.02410   0.01518  -0.0722   0.8378   0.0969
  -3.250   0.0085   0.02253   0.01372  -0.0728   0.8323   0.1189
  -3.000   0.0204   0.02126   0.01294  -0.0696   0.8200   0.1861
  -2.750   0.0198   0.01916   0.01256  -0.0643   0.8087   0.4984
  -2.500   0.0465   0.01871   0.01303  -0.0601   0.8027   0.7999
  -2.250   0.1027   0.01948   0.01367  -0.0613   0.7939   0.8825
  -2.000   0.2120   0.01997   0.01367  -0.0732   0.7891   0.9232
  -1.750   0.3066   0.01999   0.01331  -0.0844   0.7798   0.9491
  -1.500   0.3915   0.01945   0.01243  -0.0946   0.7709   0.9731
  -1.250   0.4561   0.01885   0.01160  -0.1021   0.7574   0.9917
  -1.000   0.4973   0.01839   0.01095  -0.1053   0.7436   1.0000
  -0.750   0.5135   0.01829   0.01074  -0.1036   0.7302   1.0000
  -0.500   0.5302   0.01817   0.01051  -0.1020   0.7171   1.0000
  -0.250   0.5474   0.01803   0.01025  -0.1003   0.7040   1.0000
   0.000   0.5652   0.01789   0.00996  -0.0988   0.6915   1.0000
   0.250   0.5838   0.01772   0.00965  -0.0973   0.6792   1.0000
   0.500   0.6019   0.01759   0.00939  -0.0957   0.6664   1.0000
   0.750   0.6186   0.01757   0.00926  -0.0940   0.6530   1.0000
   1.000   0.6355   0.01758   0.00916  -0.0923   0.6400   1.0000
   1.250   0.6529   0.01763   0.00911  -0.0907   0.6279   1.0000
   1.500   0.6714   0.01769   0.00904  -0.0892   0.6170   1.0000
   1.750   0.6911   0.01775   0.00895  -0.0879   0.6068   1.0000
   2.000   0.7064   0.01797   0.00911  -0.0860   0.5953   1.0000
   2.250   0.7237   0.01818   0.00922  -0.0843   0.5852   1.0000
   2.500   0.7446   0.01834   0.00922  -0.0832   0.5768   1.0000
   2.750   0.7592   0.01869   0.00958  -0.0812   0.5675   1.0000
   3.000   0.7818   0.01893   0.00966  -0.0803   0.5608   1.0000
   3.250   0.7959   0.01937   0.01014  -0.0782   0.5526   1.0000
   3.500   0.8193   0.01966   0.01031  -0.0776   0.5467   1.0000
   3.750   0.8336   0.02018   0.01089  -0.0755   0.5397   1.0000
   4.000   0.8546   0.02056   0.01121  -0.0745   0.5338   1.0000
   4.250   0.8745   0.02104   0.01166  -0.0733   0.5282   1.0000
   4.500   0.8906   0.02159   0.01228  -0.0715   0.5220   1.0000
   4.750   0.9146   0.02198   0.01260  -0.0710   0.5170   1.0000
   5.000   0.9304   0.02261   0.01330  -0.0692   0.5113   1.0000
   5.250   0.9480   0.02318   0.01392  -0.0677   0.5055   1.0000
   5.500   0.9738   0.02359   0.01428  -0.0675   0.5009   1.0000
   5.750   0.9862   0.02436   0.01519  -0.0652   0.4952   1.0000
   6.000   1.0043   0.02497   0.01585  -0.0638   0.4896   1.0000
   6.250   1.0317   0.02538   0.01620  -0.0638   0.4853   1.0000
   6.500   1.0402   0.02633   0.01735  -0.0611   0.4794   1.0000
   6.750   1.0582   0.02700   0.01808  -0.0597   0.4741   1.0000
   7.000   1.0878   0.02737   0.01840  -0.0601   0.4699   1.0000
   7.250   1.0911   0.02855   0.01980  -0.0567   0.4636   1.0000
   7.500   1.1101   0.02922   0.02056  -0.0555   0.4585   1.0000
   7.750   1.1403   0.02966   0.02098  -0.0560   0.4548   1.0000
   8.000   1.1368   0.03130   0.02287  -0.0519   0.4492   1.0000
   8.250   1.1505   0.03235   0.02404  -0.0503   0.4446   1.0000
   8.500   1.1757   0.03302   0.02476  -0.0501   0.4413   1.0000
   8.750   1.1834   0.03452   0.02641  -0.0478   0.4375   1.0000
   9.000   1.1627   0.03723   0.02937  -0.0422   0.4324   1.0000
   9.250   1.1687   0.03887   0.03113  -0.0400   0.4289   1.0000
   9.500   1.2020   0.03927   0.03159  -0.0409   0.4262   1.0000
  10.250   1.0530   0.05448   0.04706  -0.0217   0.4098   1.0000
  11.000   1.2101   0.04777   0.04070  -0.0240   0.3947   1.0000
  11.250   0.7494   0.10534   0.09782  -0.0275   0.3943   1.0000
  11.500   0.7424   0.11011   0.10266  -0.0285   0.3943   1.0000
  11.750   0.7487   0.11420   0.10685  -0.0295   0.3959   1.0000
  12.000   0.7682   0.11076   0.10344  -0.0263   0.3612   1.0000
  12.250   0.8450   0.10453   0.09739  -0.0230   0.3511   1.0000
  13.000   1.4353   0.04346   0.03727  -0.0200   0.3353   1.0000
  13.250   1.3647   0.04942   0.04345  -0.0126   0.3345   1.0000
  13.500   1.3892   0.04754   0.04163  -0.0110   0.3219   1.0000
  13.750   1.3044   0.05697   0.05121  -0.0068   0.3210   1.0000
  14.000   1.3626   0.05082   0.04513  -0.0055   0.3045   1.0000
  14.250   1.3652   0.05055   0.04493  -0.0035   0.2918   1.0000
  14.500   1.2802   0.06249   0.05704  -0.0026   0.2919   1.0000
  14.750   1.2815   0.06310   0.05774  -0.0016   0.2798   1.0000
  15.000   1.2986   0.06157   0.05625  -0.0004   0.2636   1.0000
  15.250   1.2940   0.06356   0.05828  -0.0001   0.2477   1.0000
  15.500   1.2786   0.06743   0.06214  -0.0004   0.2311   1.0000
  15.750   1.2611   0.07223   0.06697  -0.0011   0.2169   1.0000
  16.000   1.2337   0.07883   0.07363  -0.0026   0.2034   1.0000
  16.250   1.2061   0.08585   0.08071  -0.0046   0.1894   1.0000
  16.500   1.2042   0.08874   0.08338  -0.0054   0.1690   1.0000
  16.750   1.1946   0.09290   0.08733  -0.0063   0.1522   1.0000
  17.000   1.1847   0.09722   0.09151  -0.0073   0.1378   1.0000
  17.250   1.1752   0.10164   0.09583  -0.0084   0.1250   1.0000
  17.500   1.1642   0.10644   0.10055  -0.0098   0.1126   1.0000
  17.750   1.1518   0.11159   0.10562  -0.0115   0.0998   1.0000
  18.000   1.1408   0.11657   0.11050  -0.0131   0.0874   1.0000
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