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DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: DEFIANT CANARD BL20 AIRFOIL (defcnd1-il)
Reynolds number: 50,000
Max Cl/Cd: 6.08 at α=2.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-defcnd1-il-50000-n5.txt
Download as CSV file: xf-defcnd1-il-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.1834   0.11220   0.10469  -0.0763   0.8233   0.1049
 -12.500  -0.1717   0.10969   0.10205  -0.0777   0.8112   0.1088
 -12.250  -0.1917   0.10254   0.09484  -0.0821   0.8053   0.1131
 -12.000  -0.1748   0.10126   0.09348  -0.0822   0.7944   0.1166
 -11.750  -0.1761   0.09732   0.08944  -0.0842   0.7874   0.1212
 -11.500  -0.2069   0.08882   0.08095  -0.0892   0.7831   0.1255
 -11.250  -0.1833   0.08902   0.08107  -0.0883   0.7737   0.1293
 -11.000  -0.2092   0.08151   0.07353  -0.0925   0.7695   0.1341
 -10.750  -0.3583   0.05973   0.05162  -0.1064   0.7703   0.1358
 -10.500  -0.4166   0.05402   0.04559  -0.1058   0.7648   0.1365
 -10.250  -0.3835   0.05425   0.04595  -0.1055   0.7567   0.1416
 -10.000  -0.4015   0.05202   0.04354  -0.1031   0.7505   0.1444
  -9.750  -0.4242   0.04942   0.04060  -0.1003   0.7454   0.1475
  -9.500  -0.4402   0.04719   0.03808  -0.0975   0.7389   0.1509
  -9.250  -0.4163   0.04680   0.03778  -0.0969   0.7324   0.1557
  -9.000  -0.4130   0.04540   0.03613  -0.0950   0.7273   0.1604
  -8.750  -0.4174   0.04367   0.03401  -0.0924   0.7219   0.1649
  -8.500  -0.3954   0.04324   0.03370  -0.0917   0.7155   0.1695
  -8.250  -0.3828   0.04228   0.03257  -0.0903   0.7102   0.1747
  -8.000  -0.3758   0.04091   0.03076  -0.0884   0.7059   0.1801
  -7.750  -0.3547   0.04051   0.03050  -0.0877   0.6999   0.1846
  -7.500  -0.3392   0.03988   0.02976  -0.0865   0.6943   0.1899
  -7.250  -0.3267   0.03894   0.02846  -0.0849   0.6895   0.1957
  -7.000  -0.3027   0.03837   0.02792  -0.0843   0.6855   0.2008
  -6.750  -0.2877   0.03802   0.02753  -0.0829   0.6796   0.2062
  -6.500  -0.2732   0.03747   0.02674  -0.0815   0.6742   0.2122
  -6.250  -0.2518   0.03705   0.02635  -0.0806   0.6696   0.2176
  -6.000  -0.2301   0.03657   0.02576  -0.0797   0.6659   0.2244
  -5.750  -0.2144   0.03627   0.02528  -0.0783   0.6608   0.2309
  -5.500  -0.1979   0.03620   0.02533  -0.0769   0.6550   0.2367
  -5.250  -0.1788   0.03594   0.02497  -0.0757   0.6504   0.2447
  -5.000  -0.1565   0.03559   0.02457  -0.0749   0.6466   0.2529
  -4.750  -0.1339   0.03531   0.02421  -0.0740   0.6433   0.2631
  -4.500  -0.1253   0.03566   0.02466  -0.0718   0.6367   0.2713
  -4.250  -0.1089   0.03567   0.02466  -0.0703   0.6316   0.2833
  -4.000  -0.0885   0.03555   0.02459  -0.0692   0.6276   0.2968
  -3.750  -0.0652   0.03536   0.02440  -0.0683   0.6245   0.3146
  -3.500  -0.0568   0.03589   0.02500  -0.0659   0.6189   0.3304
  -3.250  -0.0482   0.03641   0.02559  -0.0636   0.6129   0.3483
  -3.000  -0.0302   0.03657   0.02576  -0.0621   0.6086   0.3706
  -2.750  -0.0080   0.03660   0.02577  -0.0609   0.6054   0.3960
  -2.500   0.0174   0.03657   0.02565  -0.0601   0.6029   0.4224
  -2.250   0.0029   0.03824   0.02745  -0.0557   0.5939   0.4329
  -2.000   0.0182   0.03864   0.02782  -0.0540   0.5892   0.4539
  -1.750   0.0419   0.03871   0.02783  -0.0531   0.5860   0.4770
  -1.500   0.0687   0.03865   0.02771  -0.0524   0.5836   0.4998
  -1.250   0.0438   0.04086   0.02999  -0.0473   0.5738   0.5080
  -1.000   0.0579   0.04136   0.03049  -0.0456   0.5692   0.5266
  -0.750   0.0824   0.04141   0.03053  -0.0447   0.5662   0.5493
  -0.500   0.1113   0.04126   0.03036  -0.0441   0.5640   0.5768
  -0.250   0.0694   0.04425   0.03348  -0.0379   0.5526   0.5803
   0.000   0.0860   0.04464   0.03397  -0.0363   0.5487   0.6070
   0.250   0.1118   0.04458   0.03399  -0.0352   0.5461   0.6408
   0.500   0.1432   0.04433   0.03385  -0.0345   0.5443   0.6761
   1.000   0.1246   0.04826   0.03808  -0.0289   0.5287   0.7251
   1.250   0.1608   0.04825   0.03819  -0.0295   0.5264   0.7720
   1.750   0.2248   0.05235   0.04260  -0.0377   0.5125   0.9075
   2.000   0.3015   0.05323   0.04332  -0.0468   0.5095   1.0000
   2.250   0.3237   0.05327   0.04310  -0.0460   0.5073   1.0000
   2.500   0.2821   0.05680   0.04657  -0.0415   0.4966   1.0000
   2.750   0.2967   0.05759   0.04718  -0.0405   0.4928   1.0000
   3.000   0.3193   0.05802   0.04742  -0.0398   0.4901   1.0000
   3.500   0.3110   0.06210   0.05131  -0.0363   0.4770   1.0000
   3.750   0.3309   0.06282   0.05189  -0.0357   0.4737   1.0000
   4.000   0.3561   0.06326   0.05218  -0.0352   0.4714   1.0000
   4.500   0.3493   0.06778   0.05658  -0.0326   0.4580   1.0000
   4.750   0.3719   0.06843   0.05711  -0.0321   0.4551   1.0000
   5.000   0.3982   0.06889   0.05745  -0.0318   0.4530   1.0000
   5.250   0.3728   0.07287   0.06145  -0.0303   0.4432   1.0000
   5.500   0.3906   0.07388   0.06237  -0.0298   0.4394   1.0000
   5.750   0.4148   0.07449   0.06288  -0.0294   0.4368   1.0000
   6.000   0.4042   0.07770   0.06609  -0.0286   0.4297   1.0000
   6.250   0.4124   0.07950   0.06785  -0.0281   0.4246   1.0000
   6.500   0.4325   0.08044   0.06871  -0.0277   0.4213   1.0000
   6.750   0.4580   0.08099   0.06918  -0.0274   0.4190   1.0000
   7.000   0.4393   0.08502   0.07324  -0.0268   0.4107   1.0000
   7.250   0.4523   0.08658   0.07477  -0.0265   0.4065   1.0000
   7.500   0.4741   0.08744   0.07557  -0.0262   0.4036   1.0000
   8.000   0.4761   0.09266   0.08078  -0.0257   0.3924   1.0000
   8.250   0.4915   0.09412   0.08221  -0.0255   0.3888   1.0000
   8.500   0.5139   0.09499   0.08303  -0.0252   0.3862   1.0000
   8.750   0.5066   0.09838   0.08645  -0.0251   0.3796   1.0000
   9.000   0.5126   0.10067   0.08875  -0.0250   0.3747   1.0000
   9.250   0.5293   0.10210   0.09015  -0.0249   0.3715   1.0000
   9.500   0.5522   0.10298   0.09100  -0.0247   0.3692   1.0000
   9.750   0.5381   0.10705   0.09512  -0.0249   0.3619   1.0000
  10.000   0.5473   0.10914   0.09722  -0.0249   0.3577   1.0000
  10.250   0.5646   0.11059   0.09865  -0.0249   0.3547   1.0000
  10.500   0.5872   0.11157   0.09962  -0.0247   0.3526   1.0000
  10.750   0.5697   0.11603   0.10415  -0.0253   0.3451   1.0000
  11.000   0.5804   0.11804   0.10617  -0.0254   0.3410   1.0000
  11.250   0.5983   0.11946   0.10759  -0.0254   0.3383   1.0000
  11.500   0.6208   0.12050   0.10862  -0.0252   0.3362   1.0000
  11.750   0.6008   0.12528   0.11347  -0.0262   0.3289   1.0000
  12.000   0.6117   0.12729   0.11551  -0.0264   0.3249   1.0000
  12.250   0.6296   0.12877   0.11700  -0.0264   0.3222   1.0000
  12.500   0.6514   0.12993   0.11816  -0.0264   0.3203   1.0000
  12.750   0.6319   0.13471   0.12301  -0.0277   0.3133   1.0000
  13.000   0.6418   0.13684   0.12518  -0.0280   0.3094   1.0000
  13.250   0.6589   0.13839   0.12676  -0.0282   0.3066   1.0000
  13.500   0.6800   0.13968   0.12807  -0.0282   0.3047   1.0000
  13.750   0.6636   0.14424   0.13268  -0.0297   0.2985   1.0000
  14.000   0.6717   0.14653   0.13502  -0.0302   0.2944   1.0000
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