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DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DEFIANT CANARD BL20 AIRFOIL (defcnd1-il)
Reynolds number: 100,000
Max Cl/Cd: 4.56 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-defcnd1-il-100000.txt
Download as CSV file: xf-defcnd1-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DEFIANT CANARD BL20 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1035   0.11370   0.10814  -0.0870   0.7951   0.1798
 -11.750  -0.3042   0.06744   0.06192  -0.1113   0.8104   0.1243
 -11.500  -0.3829   0.05634   0.05065  -0.1173   0.8063   0.1226
 -11.250  -0.4402   0.05084   0.04493  -0.1169   0.7992   0.1218
 -11.000  -0.4842   0.04771   0.04152  -0.1125   0.7921   0.1222
 -10.750  -0.5223   0.04519   0.03852  -0.1073   0.7864   0.1238
 -10.500  -0.4872   0.04526   0.03885  -0.1078   0.7782   0.1298
 -10.250  -0.4980   0.04377   0.03709  -0.1044   0.7719   0.1341
 -10.000  -0.5160   0.04172   0.03454  -0.1001   0.7670   0.1377
  -9.750  -0.4795   0.04200   0.03515  -0.1009   0.7604   0.1445
  -9.500  -0.4890   0.04048   0.03320  -0.0972   0.7546   0.1492
  -9.250  -0.4674   0.03974   0.03253  -0.0965   0.7489   0.1550
  -9.000  -0.4553   0.03912   0.03174  -0.0947   0.7437   0.1612
  -8.750  -0.4525   0.03782   0.03016  -0.0921   0.7378   0.1662
  -8.500  -0.4274   0.03746   0.02994  -0.0918   0.7323   0.1722
  -8.250  -0.4179   0.03660   0.02872  -0.0895   0.7279   0.1781
  -8.000  -0.4018   0.03569   0.02773  -0.0882   0.7232   0.1833
  -7.750  -0.3827   0.03530   0.02738  -0.0872   0.7170   0.1889
  -7.500  -0.3696   0.03463   0.02639  -0.0853   0.7119   0.1946
  -7.250  -0.3485   0.03377   0.02548  -0.0844   0.7077   0.1999
  -7.000  -0.3283   0.03347   0.02513  -0.0834   0.7035   0.2056
  -6.750  -0.3144   0.03318   0.02467  -0.0818   0.6978   0.2110
  -6.500  -0.2946   0.03256   0.02399  -0.0808   0.6927   0.2161
  -6.250  -0.2705   0.03215   0.02356  -0.0801   0.6885   0.2221
  -6.000  -0.2490   0.03180   0.02295  -0.0789   0.6850   0.2285
  -5.750  -0.2348   0.03175   0.02296  -0.0776   0.6791   0.2334
  -5.500  -0.2152   0.03168   0.02297  -0.0766   0.6740   0.2392
  -5.250  -0.1936   0.03144   0.02256  -0.0756   0.6697   0.2464
  -5.000  -0.1667   0.03095   0.02205  -0.0751   0.6664   0.2535
  -4.750  -0.1501   0.03117   0.02231  -0.0738   0.6615   0.2607
  -4.500  -0.1395   0.03162   0.02271  -0.0719   0.6555   0.2677
  -4.250  -0.1196   0.03161   0.02285  -0.0709   0.6510   0.2761
  -4.000  -0.0945   0.03134   0.02250  -0.0701   0.6475   0.2879
  -3.750  -0.0659   0.03103   0.02217  -0.0696   0.6448   0.3035
  -3.500  -0.0690   0.03227   0.02365  -0.0665   0.6373   0.3119
  -3.250  -0.0612   0.03297   0.02443  -0.0642   0.6319   0.3274
  -3.000  -0.0412   0.03302   0.02462  -0.0628   0.6282   0.3515
  -2.750  -0.0146   0.03283   0.02451  -0.0617   0.6255   0.3879
  -2.500   0.0157   0.03269   0.02437  -0.0609   0.6234   0.4276
  -2.250  -0.0397   0.03647   0.02839  -0.0533   0.6114   0.4206
  -2.000  -0.0190   0.03674   0.02870  -0.0518   0.6079   0.4519
  -1.750   0.0135   0.03652   0.02848  -0.0512   0.6054   0.4833
  -1.500  -0.0654   0.04104   0.03306  -0.0415   0.5944   0.4716
  -1.250  -0.0671   0.04247   0.03450  -0.0386   0.5899   0.4895
  -1.000  -0.0364   0.04238   0.03444  -0.0380   0.5867   0.5162
  -0.750   0.0138   0.04146   0.03357  -0.0391   0.5848   0.5461
  -0.500   0.0483   0.04140   0.03352  -0.0391   0.5820   0.5698
   0.250  -0.1439   0.05704   0.04939  -0.0240   0.6159   0.5570
   0.500  -0.1370   0.05817   0.05059  -0.0226   0.6141   0.5747
   0.750  -0.1197   0.05907   0.05156  -0.0218   0.6095   0.5961
   1.000  -0.0115   0.05320   0.04569  -0.0219   0.5516   0.6501
   1.250   0.0296   0.05289   0.04548  -0.0223   0.5472   0.6849
   1.500   0.1019   0.05130   0.04408  -0.0244   0.5443   0.7432
   1.750   0.0427   0.05623   0.04919  -0.0208   0.5391   0.7560
   2.000   0.1032   0.05826   0.05181  -0.0299   0.5325   0.8868
   2.250   0.2600   0.05699   0.05026  -0.0467   0.5264   1.0000
   2.500   0.1303   0.06747   0.06100  -0.0413   0.5497   1.0000
   2.750   0.1498   0.06895   0.06230  -0.0413   0.5475   1.0000
   3.000   0.1711   0.07065   0.06384  -0.0413   0.5461   1.0000
   3.250   0.1946   0.07260   0.06567  -0.0416   0.5450   1.0000
   3.500   0.2204   0.07493   0.06786  -0.0420   0.5438   1.0000
   3.750   0.2391   0.07031   0.06303  -0.0376   0.5028   1.0000
   4.000   0.2336   0.07312   0.06579  -0.0367   0.5021   1.0000
   4.250   0.2363   0.07577   0.06840  -0.0363   0.5028   1.0000
   4.500   0.2604   0.07808   0.07062  -0.0367   0.5052   1.0000
   4.750   0.2886   0.08032   0.07277  -0.0373   0.5063   1.0000
   5.000   0.3083   0.07913   0.07147  -0.0356   0.4892   1.0000
   5.250   0.3163   0.08184   0.07414  -0.0354   0.4890   1.0000
   5.500   0.3313   0.08442   0.07667  -0.0354   0.4882   1.0000
   5.750   0.3649   0.08233   0.07445  -0.0338   0.4703   1.0000
   6.000   0.2559   0.09243   0.08481  -0.0332   0.4973   1.0000
   6.250   0.2777   0.09402   0.08634  -0.0332   0.4927   1.0000
   6.500   0.3098   0.09612   0.08836  -0.0337   0.4901   1.0000
   6.750   0.3603   0.09930   0.09145  -0.0352   0.4884   1.0000
   7.000   0.3020   0.09982   0.09203  -0.0322   0.4777   1.0000
   7.250   0.3280   0.10156   0.09371  -0.0323   0.4736   1.0000
   7.500   0.3634   0.10404   0.09614  -0.0330   0.4715   1.0000
   7.750   0.3793   0.10721   0.09928  -0.0333   0.4700   1.0000
   8.000   0.3466   0.10771   0.09981  -0.0316   0.4590   1.0000
   8.250   0.3742   0.10959   0.10165  -0.0318   0.4554   1.0000
   8.500   0.4129   0.11246   0.10447  -0.0326   0.4535   1.0000
   8.750   0.3752   0.11425   0.10630  -0.0315   0.4467   1.0000
   9.000   0.3904   0.11595   0.10797  -0.0314   0.4408   1.0000
   9.250   0.4192   0.11803   0.11002  -0.0317   0.4376   1.0000
   9.500   0.4586   0.12129   0.11325  -0.0325   0.4359   1.0000
   9.750   0.4157   0.12262   0.11463  -0.0316   0.4276   1.0000
  10.000   0.4329   0.12448   0.11648  -0.0317   0.4230   1.0000
  10.250   0.4609   0.12677   0.11874  -0.0320   0.4202   1.0000
  10.500   0.5003   0.13037   0.12232  -0.0327   0.4186   1.0000
  10.750   0.4566   0.13129   0.12328  -0.0323   0.4095   1.0000
  11.000   0.4745   0.13328   0.12527  -0.0325   0.4055   1.0000
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