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S4320 (s4320-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 500,000
Max Cl/Cd: 117.16 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4320-il-500000.txt
Download as CSV file: xf-s4320-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4320                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2781   0.09182   0.08972  -0.0335   1.0000   0.0144
  -8.250  -0.2733   0.08931   0.08724  -0.0340   1.0000   0.0149
  -8.000  -0.2709   0.08665   0.08463  -0.0346   1.0000   0.0155
  -7.750  -0.2566   0.08270   0.08070  -0.0390   0.9845   0.0158
  -7.500  -0.2307   0.07720   0.07517  -0.0482   0.9645   0.0173
  -7.250  -0.2066   0.07113   0.06904  -0.0599   0.9333   0.0181
  -7.000  -0.1963   0.06693   0.06476  -0.0649   0.9060   0.0182
  -6.750  -0.1876   0.06271   0.06043  -0.0691   0.8853   0.0183
  -6.500  -0.1870   0.05780   0.05547  -0.0717   0.8694   0.0190
  -6.250  -0.1738   0.05525   0.05284  -0.0735   0.8557   0.0195
  -6.000  -0.1582   0.05173   0.04923  -0.0768   0.8430   0.0201
  -5.750  -0.1400   0.04763   0.04500  -0.0808   0.8316   0.0208
  -5.500  -0.1189   0.04261   0.03980  -0.0854   0.8214   0.0222
  -5.250  -0.0908   0.03324   0.02972  -0.0919   0.8122   0.0248
  -5.000  -0.0717   0.02997   0.02639  -0.0933   0.8033   0.0261
  -4.750  -0.0479   0.02859   0.02487  -0.0938   0.7952   0.0277
  -4.500  -0.0202   0.02429   0.01988  -0.0954   0.7869   0.0334
  -4.250   0.0045   0.02304   0.01863  -0.0956   0.7794   0.0350
  -4.000   0.0351   0.02470   0.02005  -0.0949   0.7707   0.0413
  -3.750   0.0637   0.01555   0.00971  -0.0954   0.7652   0.0249
  -3.500   0.0919   0.01439   0.00835  -0.0953   0.7572   0.0248
  -3.250   0.1192   0.01272   0.00643  -0.0952   0.7507   0.0255
  -3.000   0.1472   0.01178   0.00542  -0.0951   0.7429   0.0263
  -2.500   0.2032   0.01061   0.00408  -0.0949   0.7286   0.0277
  -2.250   0.2312   0.01023   0.00359  -0.0947   0.7220   0.0287
  -2.000   0.2596   0.00990   0.00323  -0.0947   0.7145   0.0301
  -1.750   0.2878   0.00967   0.00291  -0.0946   0.7077   0.0317
  -1.500   0.3163   0.00935   0.00254  -0.0946   0.7003   0.0335
  -1.250   0.3447   0.00915   0.00227  -0.0945   0.6934   0.0379
  -1.000   0.3732   0.00889   0.00208  -0.0945   0.6859   0.0638
  -0.750   0.4010   0.00837   0.00199  -0.0948   0.6788   0.2135
  -0.500   0.4289   0.00797   0.00198  -0.0950   0.6710   0.3508
  -0.250   0.4560   0.00752   0.00200  -0.0950   0.6638   0.5303
   0.000   0.4814   0.00704   0.00207  -0.0945   0.6560   0.7178
   0.250   0.5073   0.00649   0.00200  -0.0933   0.6488   1.0000
   0.500   0.5357   0.00654   0.00199  -0.0934   0.6406   1.0000
   0.750   0.5638   0.00663   0.00196  -0.0933   0.6332   1.0000
   1.000   0.5922   0.00669   0.00197  -0.0933   0.6247   1.0000
   1.250   0.6203   0.00678   0.00197  -0.0932   0.6170   1.0000
   1.500   0.6484   0.00685   0.00199  -0.0932   0.6081   1.0000
   1.750   0.6765   0.00694   0.00202  -0.0932   0.5994   1.0000
   2.000   0.7043   0.00705   0.00204  -0.0931   0.5904   1.0000
   2.250   0.7323   0.00713   0.00209  -0.0931   0.5804   1.0000
   2.500   0.7601   0.00723   0.00214  -0.0930   0.5705   1.0000
   2.750   0.7877   0.00735   0.00220  -0.0929   0.5605   1.0000
   3.000   0.8155   0.00745   0.00227  -0.0928   0.5492   1.0000
   3.250   0.8431   0.00757   0.00235  -0.0928   0.5378   1.0000
   3.500   0.8705   0.00770   0.00245  -0.0927   0.5258   1.0000
   3.750   0.8978   0.00785   0.00255  -0.0925   0.5131   1.0000
   4.000   0.9249   0.00801   0.00266  -0.0924   0.4995   1.0000
   4.250   0.9518   0.00818   0.00279  -0.0923   0.4849   1.0000
   4.500   0.9786   0.00837   0.00295  -0.0921   0.4693   1.0000
   4.750   1.0052   0.00858   0.00310  -0.0919   0.4528   1.0000
   5.000   1.0315   0.00882   0.00328  -0.0917   0.4354   1.0000
   5.250   1.0574   0.00909   0.00348  -0.0914   0.4170   1.0000
   5.500   1.0833   0.00937   0.00372  -0.0912   0.3977   1.0000
   5.750   1.1088   0.00967   0.00396  -0.0909   0.3777   1.0000
   6.000   1.1338   0.01003   0.00423  -0.0905   0.3580   1.0000
   6.250   1.1589   0.01037   0.00451  -0.0902   0.3378   1.0000
   6.500   1.1835   0.01075   0.00483  -0.0898   0.3180   1.0000
   6.750   1.2078   0.01115   0.00517  -0.0894   0.2994   1.0000
   7.000   1.2322   0.01154   0.00551  -0.0890   0.2824   1.0000
   7.250   1.2562   0.01195   0.00588  -0.0885   0.2652   1.0000
   7.500   1.2798   0.01239   0.00628  -0.0880   0.2483   1.0000
   7.750   1.3031   0.01283   0.00668  -0.0875   0.2332   1.0000
   8.000   1.3256   0.01334   0.00713  -0.0869   0.2164   1.0000
   8.250   1.3481   0.01383   0.00757  -0.0863   0.1994   1.0000
   8.500   1.3701   0.01434   0.00806  -0.0856   0.1839   1.0000
   8.750   1.3914   0.01489   0.00856  -0.0848   0.1682   1.0000
   9.000   1.4118   0.01548   0.00909  -0.0839   0.1521   1.0000
   9.250   1.4318   0.01609   0.00965  -0.0830   0.1378   1.0000
   9.500   1.4513   0.01669   0.01024  -0.0820   0.1255   1.0000
   9.750   1.4699   0.01734   0.01087  -0.0809   0.1133   1.0000
  10.000   1.4873   0.01803   0.01153  -0.0796   0.1010   1.0000
  10.250   1.5038   0.01873   0.01222  -0.0783   0.0909   1.0000
  10.500   1.5182   0.01951   0.01297  -0.0766   0.0799   1.0000
  10.750   1.5288   0.02034   0.01376  -0.0743   0.0701   1.0000
  11.000   1.5367   0.02128   0.01467  -0.0718   0.0596   1.0000
  11.250   1.5422   0.02242   0.01577  -0.0692   0.0466   1.0000
  11.500   1.5402   0.02416   0.01738  -0.0661   0.0290   1.0000
  11.750   1.5343   0.02636   0.01948  -0.0631   0.0152   1.0000
  12.000   1.5332   0.02840   0.02155  -0.0608   0.0109   1.0000
  12.250   1.5358   0.03027   0.02351  -0.0592   0.0095   1.0000
  12.500   1.5392   0.03217   0.02552  -0.0578   0.0086   1.0000
  12.750   1.5404   0.03437   0.02782  -0.0565   0.0080   1.0000
  13.000   1.5397   0.03687   0.03044  -0.0554   0.0075   1.0000
  13.250   1.5371   0.03967   0.03337  -0.0545   0.0071   1.0000
  13.500   1.5373   0.04232   0.03615  -0.0539   0.0069   1.0000
  13.750   1.5365   0.04516   0.03911  -0.0536   0.0066   1.0000
  14.000   1.5331   0.04842   0.04251  -0.0534   0.0064   1.0000
  14.250   1.5300   0.05177   0.04598  -0.0535   0.0060   1.0000
  14.500   1.5245   0.05555   0.04990  -0.0538   0.0058   1.0000
  14.750   1.5175   0.05974   0.05421  -0.0545   0.0057   1.0000
  15.000   1.5081   0.06447   0.05908  -0.0555   0.0056   1.0000
  15.250   1.4985   0.06945   0.06420  -0.0568   0.0055   1.0000
  15.500   1.4863   0.07506   0.06994  -0.0586   0.0054   1.0000
  15.750   1.4745   0.08084   0.07586  -0.0606   0.0053   1.0000
  16.000   1.4588   0.08749   0.08266  -0.0631   0.0052   1.0000
  16.250   1.4451   0.09401   0.08932  -0.0658   0.0052   1.0000
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