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NACA/LANGLEY SYMMETRICAL (n0011sc-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA/LANGLEY SYMMETRICAL (n0011sc-il)
Reynolds number: 50,000
Max Cl/Cd: 22.3 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0011sc-il-50000-n5.txt
Download as CSV file: xf-n0011sc-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA/LANGLEY SYMMETRICAL                        
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6345   0.10126   0.09279  -0.0380   1.0000   0.0666
 -11.250  -0.6501   0.09411   0.08565  -0.0416   1.0000   0.0663
 -11.000  -0.6743   0.08712   0.07866  -0.0449   1.0000   0.0660
 -10.750  -0.6998   0.08143   0.07292  -0.0462   1.0000   0.0657
 -10.500  -0.7293   0.07660   0.06801  -0.0455   1.0000   0.0655
 -10.250  -0.7560   0.07283   0.06415  -0.0428   1.0000   0.0653
 -10.000  -0.7830   0.06973   0.06093  -0.0384   1.0000   0.0652
  -9.750  -0.8069   0.06681   0.05788  -0.0334   1.0000   0.0651
  -9.500  -0.8275   0.06362   0.05447  -0.0285   1.0000   0.0653
  -9.250  -0.8445   0.06046   0.05104  -0.0236   1.0000   0.0657
  -9.000  -0.8571   0.05742   0.04768  -0.0188   1.0000   0.0661
  -8.750  -0.8657   0.05449   0.04438  -0.0141   1.0000   0.0665
  -8.500  -0.8685   0.05172   0.04130  -0.0100   1.0000   0.0670
  -8.250  -0.8630   0.04949   0.03892  -0.0070   1.0000   0.0678
  -8.000  -0.8551   0.04762   0.03691  -0.0042   1.0000   0.0692
  -7.750  -0.8472   0.04576   0.03486  -0.0013   1.0000   0.0708
  -7.500  -0.8392   0.04377   0.03259   0.0017   1.0000   0.0728
  -7.250  -0.8301   0.04166   0.03007   0.0048   1.0000   0.0751
  -7.000  -0.8176   0.03958   0.02756   0.0075   1.0000   0.0770
  -6.750  -0.8005   0.03803   0.02599   0.0091   1.0000   0.0793
  -6.500  -0.7836   0.03667   0.02450   0.0110   1.0000   0.0826
  -6.250  -0.7650   0.03520   0.02273   0.0127   1.0000   0.0867
  -6.000  -0.7436   0.03375   0.02120   0.0139   1.0000   0.0903
  -5.750  -0.7227   0.03262   0.02001   0.0151   1.0000   0.0952
  -5.500  -0.6990   0.03147   0.01867   0.0161   1.0000   0.1015
  -5.250  -0.6762   0.03045   0.01771   0.0169   1.0000   0.1081
  -5.000  -0.6514   0.02948   0.01666   0.0176   1.0000   0.1170
  -4.750  -0.6270   0.02862   0.01574   0.0183   1.0000   0.1282
  -4.500  -0.6030   0.02775   0.01494   0.0190   1.0000   0.1416
  -4.250  -0.5804   0.02693   0.01416   0.0199   1.0000   0.1597
  -4.000  -0.5601   0.02605   0.01346   0.0211   1.0000   0.1823
  -3.750  -0.5413   0.02516   0.01279   0.0226   1.0000   0.2164
  -3.500  -0.5247   0.02416   0.01218   0.0245   1.0000   0.2703
  -3.250  -0.5122   0.02297   0.01163   0.0271   1.0000   0.3628
  -3.000  -0.3876   0.02303   0.01371   0.0127   1.0000   0.8057
  -2.750  -0.3527   0.02398   0.01445   0.0132   1.0000   0.8695
  -2.500  -0.2997   0.02503   0.01525   0.0098   1.0000   0.9147
  -2.250  -0.2340   0.02580   0.01574   0.0032   1.0000   0.9492
  -2.000  -0.1551   0.02607   0.01575  -0.0068   1.0000   0.9778
  -1.750  -0.0778   0.02585   0.01530  -0.0173   1.0000   1.0000
  -1.500  -0.0670   0.02561   0.01500  -0.0149   1.0000   1.0000
  -1.250  -0.0561   0.02541   0.01475  -0.0124   1.0000   1.0000
  -1.000  -0.0450   0.02526   0.01456  -0.0100   1.0000   1.0000
  -0.750  -0.0338   0.02514   0.01440  -0.0075   1.0000   1.0000
  -0.500  -0.0226   0.02505   0.01430  -0.0050   1.0000   1.0000
  -0.250  -0.0113   0.02500   0.01423  -0.0025   1.0000   1.0000
   0.000   0.0000   0.02498   0.01421   0.0000   1.0000   1.0000
   0.250   0.0113   0.02500   0.01423   0.0025   1.0000   1.0000
   0.500   0.0226   0.02505   0.01429   0.0050   1.0000   1.0000
   0.750   0.0339   0.02513   0.01440   0.0075   1.0000   1.0000
   1.000   0.0450   0.02525   0.01455   0.0100   1.0000   1.0000
   1.250   0.0561   0.02541   0.01475   0.0124   1.0000   1.0000
   1.500   0.0670   0.02560   0.01500   0.0149   1.0000   1.0000
   1.750   0.0779   0.02584   0.01529   0.0173   1.0000   1.0000
   2.000   0.1548   0.02606   0.01574   0.0068   0.9779   1.0000
   2.250   0.2356   0.02578   0.01572  -0.0035   0.9488   1.0000
   2.500   0.2997   0.02501   0.01522  -0.0098   0.9142   1.0000
   2.750   0.3528   0.02397   0.01444  -0.0132   0.8696   1.0000
   3.000   0.3865   0.02305   0.01373  -0.0126   0.8070   1.0000
   3.250   0.5122   0.02297   0.01163  -0.0271   0.3631   1.0000
   3.500   0.5247   0.02415   0.01217  -0.0245   0.2709   1.0000
   3.750   0.5412   0.02515   0.01279  -0.0226   0.2167   1.0000
   4.000   0.5600   0.02604   0.01345  -0.0211   0.1829   1.0000
   4.250   0.5803   0.02692   0.01415  -0.0199   0.1595   1.0000
   4.500   0.6029   0.02775   0.01493  -0.0190   0.1414   1.0000
   4.750   0.6268   0.02861   0.01574  -0.0183   0.1278   1.0000
   5.000   0.6513   0.02947   0.01665  -0.0176   0.1170   1.0000
   5.250   0.6762   0.03045   0.01771  -0.0169   0.1079   1.0000
   5.500   0.6990   0.03146   0.01866  -0.0160   0.1015   1.0000
   5.750   0.7229   0.03264   0.02003  -0.0151   0.0952   1.0000
   6.000   0.7435   0.03375   0.02119  -0.0139   0.0902   1.0000
   6.250   0.7650   0.03520   0.02274  -0.0127   0.0867   1.0000
   6.500   0.7838   0.03670   0.02454  -0.0110   0.0826   1.0000
   6.750   0.8004   0.03803   0.02598  -0.0091   0.0792   1.0000
   7.000   0.8175   0.03958   0.02755  -0.0076   0.0769   1.0000
   7.250   0.8297   0.04169   0.03012  -0.0048   0.0749   1.0000
   7.500   0.8391   0.04377   0.03258  -0.0017   0.0727   1.0000
   7.750   0.8472   0.04574   0.03484   0.0013   0.0708   1.0000
   8.000   0.8559   0.04747   0.03673   0.0041   0.0688   1.0000
   8.250   0.8633   0.04944   0.03885   0.0070   0.0677   1.0000
   8.500   0.8690   0.05169   0.04125   0.0099   0.0669   1.0000
   8.750   0.8645   0.05455   0.04446   0.0143   0.0664   1.0000
   9.000   0.8564   0.05748   0.04775   0.0189   0.0660   1.0000
   9.250   0.8434   0.06052   0.05111   0.0237   0.0656   1.0000
   9.500   0.8265   0.06363   0.05449   0.0286   0.0652   1.0000
   9.750   0.8067   0.06681   0.05788   0.0334   0.0651   1.0000
  10.000   0.7811   0.06976   0.06098   0.0386   0.0650   1.0000
  10.250   0.7533   0.07295   0.06428   0.0429   0.0651   1.0000
  10.500   0.7265   0.07678   0.06820   0.0455   0.0653   1.0000
  10.750   0.6974   0.08172   0.07322   0.0461   0.0656   1.0000
  11.000   0.6732   0.08734   0.07888   0.0447   0.0660   1.0000
  11.250   0.6510   0.09407   0.08561   0.0416   0.0663   1.0000
  11.500   0.6351   0.10128   0.09281   0.0379   0.0666   1.0000
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