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DEFIANT CANARD BL145 AIRFOIL (defcnd3-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DEFIANT CANARD BL145 AIRFOIL (defcnd3-il)
Reynolds number: 50,000
Max Cl/Cd: 25.64 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-defcnd3-il-50000.txt
Download as CSV file: xf-defcnd3-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DEFIANT CANARD BL145 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3883   0.09367   0.08711  -0.0049   1.0000   0.3456
  -7.000  -0.3769   0.08818   0.08178  -0.0015   1.0000   0.3793
  -6.750  -0.3527   0.08371   0.07732  -0.0005   1.0000   0.3907
  -6.500  -0.3508   0.08101   0.07471   0.0011   1.0000   0.4057
  -6.250  -0.3525   0.07853   0.07236   0.0032   1.0000   0.4215
  -6.000  -0.3597   0.07638   0.07034   0.0057   1.0000   0.4376
  -5.750  -0.4642   0.05390   0.04696  -0.0294   1.0000   0.1454
  -5.500  -0.4569   0.04895   0.04152  -0.0291   1.0000   0.1282
  -5.250  -0.4463   0.04496   0.03690  -0.0279   1.0000   0.1173
  -5.000  -0.4330   0.04169   0.03331  -0.0265   1.0000   0.1125
  -4.750  -0.4183   0.03889   0.02959  -0.0244   1.0000   0.1062
  -4.500  -0.4006   0.03656   0.02697  -0.0228   1.0000   0.1049
  -4.250  -0.3823   0.03435   0.02448  -0.0212   1.0000   0.1046
  -4.000  -0.3636   0.03248   0.02230  -0.0196   1.0000   0.1062
  -3.750  -0.3449   0.03063   0.02047  -0.0184   1.0000   0.1101
  -3.500  -0.3252   0.02925   0.01896  -0.0169   1.0000   0.1143
  -3.250  -0.3045   0.02805   0.01752  -0.0153   1.0000   0.1190
  -3.000  -0.2840   0.02671   0.01625  -0.0139   1.0000   0.1269
  -2.750  -0.2641   0.02567   0.01524  -0.0125   1.0000   0.1412
  -2.500  -0.2437   0.02458   0.01423  -0.0112   1.0000   0.1705
  -2.250  -0.0597   0.02104   0.01388  -0.0248   1.0000   1.0000
  -2.000  -0.0997   0.02065   0.01361  -0.0179   1.0000   1.0000
  -1.750  -0.1221   0.02054   0.01340  -0.0131   1.0000   1.0000
  -1.500  -0.1254   0.02075   0.01337  -0.0105   1.0000   1.0000
  -1.250  -0.1204   0.02115   0.01351  -0.0089   1.0000   1.0000
  -1.000  -0.0969   0.02182   0.01388  -0.0105   0.9952   1.0000
  -0.750  -0.0323   0.02286   0.01453  -0.0190   0.9757   1.0000
  -0.500   0.0252   0.02360   0.01496  -0.0259   0.9554   1.0000
  -0.250   0.0806   0.02417   0.01530  -0.0320   0.9355   1.0000
   0.000   0.1319   0.02462   0.01555  -0.0370   0.9148   1.0000
   0.250   0.1878   0.02486   0.01563  -0.0423   0.8929   1.0000
   0.500   0.2626   0.02459   0.01523  -0.0500   0.8710   1.0000
   0.750   0.3203   0.02428   0.01483  -0.0544   0.8475   1.0000
   1.000   0.3696   0.02407   0.01454  -0.0572   0.8254   1.0000
   1.250   0.4143   0.02395   0.01435  -0.0593   0.8046   1.0000
   1.500   0.4555   0.02385   0.01419  -0.0605   0.7837   1.0000
   1.750   0.4930   0.02382   0.01407  -0.0610   0.7627   1.0000
   2.000   0.5243   0.02394   0.01412  -0.0604   0.7411   1.0000
   2.250   0.5465   0.02436   0.01449  -0.0587   0.7177   1.0000
   2.500   0.5720   0.02467   0.01474  -0.0574   0.6949   1.0000
   2.750   0.5985   0.02498   0.01496  -0.0561   0.6731   1.0000
   3.000   0.6253   0.02529   0.01518  -0.0548   0.6517   1.0000
   3.250   0.6461   0.02589   0.01572  -0.0529   0.6294   1.0000
   3.500   0.6665   0.02658   0.01637  -0.0512   0.6080   1.0000
   3.750   0.6880   0.02728   0.01703  -0.0496   0.5881   1.0000
   4.000   0.7095   0.02802   0.01776  -0.0481   0.5696   1.0000
   4.250   0.7307   0.02885   0.01857  -0.0466   0.5528   1.0000
   4.500   0.7531   0.02968   0.01937  -0.0454   0.5378   1.0000
   4.750   0.7783   0.03036   0.02000  -0.0444   0.5240   1.0000
   5.000   0.7934   0.03166   0.02143  -0.0427   0.5098   1.0000
   5.250   0.8095   0.03302   0.02288  -0.0413   0.4971   1.0000
   5.500   0.8341   0.03382   0.02366  -0.0403   0.4858   1.0000
   5.750   0.8511   0.03507   0.02501  -0.0388   0.4734   1.0000
   6.000   0.8636   0.03668   0.02678  -0.0371   0.4611   1.0000
   6.250   0.8857   0.03739   0.02751  -0.0357   0.4476   1.0000
   6.500   0.9112   0.03763   0.02772  -0.0343   0.4324   1.0000
   6.750   0.9363   0.03780   0.02785  -0.0329   0.4161   1.0000
   7.000   0.9615   0.03799   0.02802  -0.0315   0.3999   1.0000
   7.250   0.9781   0.03883   0.02897  -0.0296   0.3838   1.0000
   7.500   0.9975   0.03946   0.02964  -0.0278   0.3670   1.0000
   7.750   1.0200   0.03986   0.03005  -0.0262   0.3491   1.0000
   8.000   1.0386   0.04057   0.03077  -0.0243   0.3304   1.0000
   8.250   1.0511   0.04182   0.03213  -0.0220   0.3118   1.0000
   8.500   1.0636   0.04310   0.03351  -0.0197   0.2929   1.0000
   8.750   1.0771   0.04454   0.03500  -0.0176   0.2756   1.0000
   9.000   1.0904   0.04608   0.03657  -0.0156   0.2599   1.0000
   9.250   1.1065   0.04766   0.03815  -0.0140   0.2464   1.0000
   9.500   1.1324   0.04881   0.03914  -0.0132   0.2329   1.0000
   9.750   1.1051   0.05342   0.04433  -0.0091   0.2276   1.0000
  10.000   1.1416   0.05418   0.04485  -0.0091   0.2160   1.0000
  10.250   1.1065   0.05938   0.05053  -0.0052   0.2138   1.0000
  10.500   1.0630   0.06530   0.05671  -0.0021   0.2133   1.0000
  10.750   1.0090   0.07288   0.06441  -0.0009   0.2144   1.0000
  11.000   0.9488   0.08416   0.07569  -0.0049   0.2161   1.0000
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