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DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
Reynolds number: 50,000
Max Cl/Cd: 8.41 at α=0.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-defcnd2-il-50000.txt
Download as CSV file: xf-defcnd2-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2795   0.11404   0.10789  -0.0344   1.0000   0.2512
  -9.250  -0.2771   0.11113   0.10507  -0.0327   1.0000   0.2581
  -9.000  -0.2958   0.11070   0.10480  -0.0305   1.0000   0.2673
  -8.750  -0.2891   0.10772   0.10189  -0.0279   1.0000   0.2758
  -8.500  -0.3238   0.10842   0.10277  -0.0248   1.0000   0.2835
  -8.250  -0.3144   0.10550   0.09989  -0.0218   1.0000   0.2962
  -8.000  -0.3296   0.10416   0.09868  -0.0189   1.0000   0.3031
  -7.750  -0.3528   0.10393   0.09858  -0.0155   1.0000   0.3142
  -7.500  -0.3509   0.10165   0.09636  -0.0125   1.0000   0.3283
  -7.250  -0.3534   0.09964   0.09443  -0.0095   1.0000   0.3418
  -7.000  -0.3604   0.09795   0.09284  -0.0064   1.0000   0.3547
  -6.750  -0.4171   0.09927   0.09437  -0.0017   1.0000   0.3620
  -6.500  -0.3810   0.09501   0.09010   0.0002   1.0000   0.3839
  -6.250  -0.3897   0.09349   0.08867   0.0037   1.0000   0.4003
  -6.000  -0.3988   0.09213   0.08740   0.0073   1.0000   0.4181
  -5.750  -0.4253   0.09176   0.08717   0.0123   1.0000   0.4383
  -5.500  -0.4144   0.08923   0.08469   0.0150   1.0000   0.4605
  -4.750  -0.3903   0.08352   0.07911   0.0227   0.9957   0.5542
  -4.500  -0.5037   0.05866   0.05229  -0.0228   0.9845   0.1574
  -4.250  -0.4648   0.05323   0.04607  -0.0270   0.9721   0.1379
  -4.000  -0.4244   0.04926   0.04114  -0.0301   0.9584   0.1277
  -3.750  -0.3833   0.04633   0.03763  -0.0329   0.9438   0.1253
  -3.500  -0.3428   0.04422   0.03488  -0.0352   0.9291   0.1283
  -3.250  -0.3034   0.04248   0.03256  -0.0369   0.9155   0.1311
  -3.000  -0.2643   0.04076   0.03071  -0.0388   0.9037   0.1365
  -2.750  -0.2177   0.03949   0.02918  -0.0416   0.8929   0.1488
  -2.500   0.0881   0.03475   0.02756  -0.0772   0.8966   1.0000
  -2.250   0.1119   0.03479   0.02725  -0.0783   0.8821   1.0000
  -2.000   0.1353   0.03491   0.02706  -0.0790   0.8676   1.0000
  -1.750   0.1575   0.03508   0.02695  -0.0794   0.8533   1.0000
  -1.500   0.1795   0.03529   0.02690  -0.0795   0.8391   1.0000
  -1.250   0.2013   0.03552   0.02690  -0.0794   0.8250   1.0000
  -1.000   0.2245   0.03576   0.02692  -0.0793   0.8114   1.0000
  -0.750   0.2792   0.03560   0.02645  -0.0839   0.8016   1.0000
  -0.500   0.2844   0.03614   0.02686  -0.0810   0.7872   1.0000
  -0.250   0.2855   0.03681   0.02741  -0.0775   0.7731   1.0000
   0.000   0.2825   0.03764   0.02811  -0.0734   0.7595   1.0000
   0.250   0.2815   0.03851   0.02884  -0.0697   0.7465   1.0000
   0.500   0.2918   0.03926   0.02944  -0.0676   0.7350   1.0000
   0.750   0.3315   0.03942   0.02941  -0.0693   0.7262   1.0000
   1.000   0.3106   0.04104   0.03092  -0.0633   0.7141   1.0000
   1.250   0.3074   0.04248   0.03223  -0.0599   0.7052   1.0000
   1.500   0.3278   0.04331   0.03292  -0.0593   0.6975   1.0000
   1.750   0.3150   0.04516   0.03467  -0.0551   0.6887   1.0000
   2.000   0.3509   0.04557   0.03493  -0.0561   0.6815   1.0000
   2.250   0.3355   0.04753   0.03681  -0.0519   0.6720   1.0000
   2.500   0.3620   0.04815   0.03730  -0.0517   0.6632   1.0000
   2.750   0.3711   0.04939   0.03844  -0.0500   0.6542   1.0000
   3.000   0.3770   0.05087   0.03984  -0.0481   0.6459   1.0000
   3.250   0.3994   0.05178   0.04067  -0.0478   0.6384   1.0000
   3.500   0.3985   0.05381   0.04262  -0.0458   0.6319   1.0000
   3.750   0.4057   0.05551   0.04428  -0.0446   0.6254   1.0000
   4.000   0.4304   0.05668   0.04538  -0.0447   0.6199   1.0000
   4.250   0.4148   0.05951   0.04818  -0.0422   0.6146   1.0000
   4.500   0.4322   0.06104   0.04967  -0.0419   0.6089   1.0000
   4.750   0.4400   0.06306   0.05166  -0.0411   0.6034   1.0000
   5.000   0.4344   0.06567   0.05424  -0.0397   0.5991   1.0000
   5.250   0.4393   0.06805   0.05660  -0.0391   0.5963   1.0000
   5.500   0.4339   0.07114   0.05969  -0.0385   0.5982   1.0000
   5.750   0.4367   0.07427   0.06281  -0.0386   0.6034   1.0000
   6.000   0.3291   0.08259   0.07131  -0.0374   0.7206   1.0000
   6.250   0.3474   0.08471   0.07340  -0.0379   0.7132   1.0000
   6.500   0.3633   0.08719   0.07585  -0.0383   0.7089   1.0000
   6.750   0.3685   0.08842   0.07707  -0.0373   0.7005   1.0000
   7.000   0.3951   0.09153   0.08017  -0.0389   0.6962   1.0000
   7.250   0.3917   0.09246   0.08110  -0.0371   0.6894   1.0000
   7.500   0.4117   0.09489   0.08353  -0.0379   0.6831   1.0000
   7.750   0.4217   0.09699   0.08563  -0.0377   0.6780   1.0000
   8.000   0.4357   0.09885   0.08750  -0.0377   0.6689   1.0000
   8.250   0.4493   0.10131   0.08997  -0.0380   0.6638   1.0000
   8.500   0.4587   0.10289   0.09158  -0.0376   0.6550   1.0000
   8.750   0.4835   0.10636   0.09507  -0.0390   0.6504   1.0000
   9.000   0.4841   0.10717   0.09591  -0.0377   0.6400   1.0000
   9.250   0.5035   0.11024   0.09902  -0.0386   0.6348   1.0000
   9.500   0.5099   0.11159   0.10043  -0.0380   0.6246   1.0000
   9.750   0.5209   0.11400   0.10288  -0.0381   0.6179   1.0000
  10.000   0.5375   0.11633   0.10528  -0.0385   0.6085   1.0000
  10.250   0.5415   0.11818   0.10717  -0.0381   0.6004   1.0000
  10.500   0.5670   0.12156   0.11063  -0.0393   0.5923   1.0000
  10.750   0.5647   0.12279   0.11191  -0.0384   0.5826   1.0000
  11.000   0.5974   0.12742   0.11666  -0.0402   0.5761   1.0000
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