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WORTMANN FX 76-120 (fx76120-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 76-120 (fx76120-il)
Reynolds number: 50,000
Max Cl/Cd: 25.03 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76120-il-50000.txt
Download as CSV file: xf-fx76120-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 76-120                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.7080   0.08225   0.07449  -0.0254   1.0000   0.1809
 -10.000  -0.7327   0.07533   0.06758  -0.0276   1.0000   0.1792
  -9.750  -0.7674   0.06914   0.06139  -0.0275   1.0000   0.1771
  -9.500  -0.8045   0.06324   0.05538  -0.0260   1.0000   0.1750
  -9.250  -0.8315   0.05805   0.04996  -0.0236   1.0000   0.1748
  -9.000  -0.8474   0.05364   0.04523  -0.0209   1.0000   0.1766
  -8.750  -0.8604   0.04954   0.04070  -0.0177   1.0000   0.1795
  -8.500  -0.8493   0.04724   0.03834  -0.0158   1.0000   0.1870
  -8.250  -0.8473   0.04442   0.03519  -0.0130   1.0000   0.1941
  -8.000  -0.8371   0.04208   0.03273  -0.0107   1.0000   0.2027
  -7.750  -0.8350   0.03961   0.02977  -0.0074   1.0000   0.2130
  -7.500  -0.8170   0.03800   0.02825  -0.0057   1.0000   0.2263
  -7.250  -0.8029   0.03640   0.02659  -0.0035   1.0000   0.2415
  -7.000  -0.7894   0.03479   0.02488  -0.0011   1.0000   0.2586
  -6.750  -0.7770   0.03331   0.02325   0.0015   1.0000   0.2778
  -6.500  -0.7581   0.03220   0.02233   0.0034   1.0000   0.2985
  -6.250  -0.7418   0.03111   0.02126   0.0057   1.0000   0.3206
  -6.000  -0.7285   0.02995   0.01995   0.0082   1.0000   0.3435
  -5.750  -0.7089   0.02909   0.01927   0.0102   1.0000   0.3658
  -5.500  -0.6923   0.02817   0.01834   0.0124   1.0000   0.3888
  -5.250  -0.6755   0.02724   0.01742   0.0147   1.0000   0.4119
  -5.000  -0.6565   0.02646   0.01672   0.0167   1.0000   0.4350
  -4.750  -0.6403   0.02558   0.01579   0.0189   1.0000   0.4594
  -4.500  -0.6200   0.02487   0.01524   0.0208   1.0000   0.4834
  -4.250  -0.6030   0.02410   0.01444   0.0230   1.0000   0.5099
  -4.000  -0.5825   0.02349   0.01400   0.0250   1.0000   0.5370
  -3.750  -0.5634   0.02288   0.01350   0.0272   1.0000   0.5672
  -3.500  -0.5441   0.02233   0.01309   0.0294   1.0000   0.6006
  -3.250  -0.5244   0.02188   0.01277   0.0318   1.0000   0.6381
  -3.000  -0.5041   0.02155   0.01260   0.0343   1.0000   0.6801
  -2.750  -0.4818   0.02145   0.01265   0.0368   1.0000   0.7259
  -2.500  -0.4537   0.02169   0.01302   0.0390   1.0000   0.7742
  -2.250  -0.4122   0.02235   0.01368   0.0391   1.0000   0.8241
  -2.000  -0.3378   0.02346   0.01461   0.0334   1.0000   0.8717
  -1.750  -0.2277   0.02432   0.01519   0.0203   1.0000   0.9141
  -1.500  -0.1155   0.02428   0.01490   0.0051   1.0000   0.9525
  -1.250  -0.0075   0.02340   0.01383  -0.0110   1.0000   0.9885
  -1.000   0.0307   0.02256   0.01294  -0.0156   1.0000   1.0000
  -0.750   0.0262   0.02216   0.01257  -0.0124   1.0000   1.0000
  -0.500   0.0192   0.02189   0.01233  -0.0086   1.0000   1.0000
  -0.250   0.0101   0.02174   0.01219  -0.0044   1.0000   1.0000
   0.000   0.0000   0.02169   0.01214   0.0000   1.0000   1.0000
   0.250  -0.0102   0.02174   0.01219   0.0044   1.0000   1.0000
   0.500  -0.0192   0.02189   0.01232   0.0086   1.0000   1.0000
   0.750  -0.0263   0.02216   0.01257   0.0124   1.0000   1.0000
   1.000  -0.0307   0.02255   0.01293   0.0156   1.0000   1.0000
   1.250   0.0076   0.02340   0.01382   0.0109   0.9885   1.0000
   1.500   0.1153   0.02428   0.01490  -0.0051   0.9525   1.0000
   1.750   0.2273   0.02433   0.01520  -0.0202   0.9141   1.0000
   2.000   0.3379   0.02345   0.01462  -0.0334   0.8716   1.0000
   2.250   0.4122   0.02235   0.01367  -0.0391   0.8240   1.0000
   2.500   0.4537   0.02169   0.01301  -0.0390   0.7743   1.0000
   2.750   0.4818   0.02145   0.01265  -0.0368   0.7259   1.0000
   3.000   0.5041   0.02155   0.01260  -0.0343   0.6801   1.0000
   3.250   0.5243   0.02188   0.01278  -0.0318   0.6382   1.0000
   3.500   0.5440   0.02233   0.01308  -0.0294   0.6007   1.0000
   3.750   0.5633   0.02288   0.01350  -0.0272   0.5672   1.0000
   4.000   0.5825   0.02349   0.01400  -0.0250   0.5372   1.0000
   4.250   0.6030   0.02410   0.01445  -0.0230   0.5100   1.0000
   4.500   0.6200   0.02487   0.01523  -0.0208   0.4833   1.0000
   4.750   0.6402   0.02558   0.01579  -0.0189   0.4593   1.0000
   5.000   0.6565   0.02645   0.01671  -0.0167   0.4349   1.0000
   5.250   0.6755   0.02724   0.01742  -0.0146   0.4119   1.0000
   5.500   0.6923   0.02816   0.01833  -0.0125   0.3889   1.0000
   5.750   0.7088   0.02908   0.01927  -0.0102   0.3659   1.0000
   6.000   0.7284   0.02995   0.01995  -0.0082   0.3436   1.0000
   6.250   0.7418   0.03111   0.02126  -0.0057   0.3206   1.0000
   6.500   0.7580   0.03220   0.02233  -0.0034   0.2986   1.0000
   6.750   0.7769   0.03331   0.02326  -0.0015   0.2778   1.0000
   7.000   0.7894   0.03480   0.02488   0.0011   0.2586   1.0000
   7.250   0.8029   0.03640   0.02660   0.0035   0.2416   1.0000
   7.500   0.8172   0.03800   0.02825   0.0057   0.2264   1.0000
   7.750   0.8350   0.03960   0.02976   0.0074   0.2130   1.0000
   8.000   0.8369   0.04212   0.03278   0.0108   0.2029   1.0000
   8.250   0.8474   0.04441   0.03518   0.0130   0.1941   1.0000
   8.500   0.8498   0.04719   0.03828   0.0158   0.1868   1.0000
   8.750   0.8604   0.04956   0.04071   0.0177   0.1795   1.0000
   9.000   0.8473   0.05362   0.04522   0.0210   0.1764   1.0000
   9.250   0.8314   0.05806   0.04997   0.0237   0.1747   1.0000
   9.500   0.8048   0.06323   0.05536   0.0259   0.1750   1.0000
   9.750   0.7678   0.06917   0.06142   0.0274   0.1771   1.0000
  10.000   0.7328   0.07540   0.06766   0.0275   0.1793   1.0000
  10.250   0.7093   0.08220   0.07443   0.0254   0.1809   1.0000
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