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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 500,000
Max Cl/Cd: 102.79 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4083-il-500000.txt
Download as CSV file: xf-s4083-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4083 (8%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3031   0.09305   0.09093  -0.0218   1.0000   0.0145
  -8.750  -0.3018   0.08949   0.08738  -0.0224   1.0000   0.0145
  -8.500  -0.3057   0.08409   0.08203  -0.0223   1.0000   0.0150
  -8.250  -0.3024   0.08099   0.07894  -0.0218   1.0000   0.0152
  -8.000  -0.2999   0.07792   0.07589  -0.0216   1.0000   0.0155
  -7.750  -0.2990   0.07481   0.07279  -0.0216   1.0000   0.0157
  -7.500  -0.2995   0.07166   0.06967  -0.0215   1.0000   0.0159
  -7.250  -0.3014   0.06863   0.06667  -0.0213   1.0000   0.0161
  -7.000  -0.3056   0.06574   0.06382  -0.0207   1.0000   0.0164
  -6.750  -0.3136   0.06318   0.06130  -0.0194   1.0000   0.0166
  -6.500  -0.3232   0.06066   0.05884  -0.0183   1.0000   0.0167
  -6.250  -0.3273   0.05758   0.05579  -0.0188   1.0000   0.0170
  -6.000  -0.3298   0.05429   0.05252  -0.0199   1.0000   0.0172
  -5.750  -0.3055   0.04799   0.04619  -0.0291   0.9970   0.0179
  -5.500  -0.2760   0.04089   0.03901  -0.0400   0.9939   0.0189
  -5.250  -0.2380   0.03367   0.03161  -0.0513   0.9903   0.0204
  -5.000  -0.2027   0.02751   0.02518  -0.0588   0.9871   0.0207
  -4.750  -0.1784   0.01825   0.01551  -0.0662   0.9829   0.0218
  -4.500  -0.1482   0.01568   0.01286  -0.0691   0.9779   0.0227
  -4.250  -0.1133   0.01298   0.00996  -0.0725   0.9744   0.0244
  -3.750  -0.0472   0.00757   0.00359  -0.0766   0.9625   0.0311
  -3.500  -0.0397   0.01671   0.01205  -0.0750   0.9667   0.0194
  -3.250  -0.0028   0.01375   0.00862  -0.0765   0.9622   0.0176
  -3.000   0.0287   0.01280   0.00752  -0.0769   0.9520   0.0190
  -2.750   0.0623   0.01122   0.00574  -0.0775   0.9414   0.0182
  -2.500   0.1023   0.00999   0.00435  -0.0797   0.9288   0.0180
  -2.250   0.1551   0.00904   0.00328  -0.0847   0.9108   0.0188
  -2.000   0.2112   0.00832   0.00234  -0.0906   0.8725   0.0225
  -1.750   0.2463   0.00792   0.00180  -0.0918   0.8158   0.0587
  -1.500   0.2701   0.00767   0.00165  -0.0909   0.7625   0.1646
  -1.250   0.2925   0.00749   0.00160  -0.0897   0.7169   0.2783
  -1.000   0.3140   0.00718   0.00162  -0.0885   0.6796   0.4470
  -0.750   0.3354   0.00692   0.00166  -0.0871   0.6481   0.6029
  -0.500   0.3572   0.00678   0.00167  -0.0856   0.6211   0.7073
   0.000   0.4300   0.00646   0.00162  -0.0889   0.5721   1.0000
   0.250   0.4553   0.00662   0.00161  -0.0882   0.5534   1.0000
   0.500   0.4807   0.00677   0.00162  -0.0876   0.5364   1.0000
   0.750   0.5063   0.00692   0.00165  -0.0870   0.5211   1.0000
   1.250   0.5580   0.00720   0.00172  -0.0859   0.4938   1.0000
   1.500   0.5840   0.00734   0.00177  -0.0854   0.4811   1.0000
   1.750   0.6101   0.00748   0.00183  -0.0849   0.4692   1.0000
   2.000   0.6361   0.00762   0.00190  -0.0845   0.4580   1.0000
   2.250   0.6621   0.00777   0.00198  -0.0840   0.4477   1.0000
   2.500   0.6882   0.00792   0.00207  -0.0835   0.4375   1.0000
   2.750   0.7145   0.00805   0.00216  -0.0831   0.4280   1.0000
   3.000   0.7405   0.00821   0.00228  -0.0827   0.4189   1.0000
   3.250   0.7666   0.00835   0.00239  -0.0822   0.4097   1.0000
   3.500   0.7927   0.00849   0.00251  -0.0818   0.4004   1.0000
   3.750   0.8185   0.00867   0.00264  -0.0813   0.3915   1.0000
   4.000   0.8447   0.00881   0.00279  -0.0809   0.3820   1.0000
   4.250   0.8706   0.00897   0.00294  -0.0805   0.3728   1.0000
   4.500   0.8962   0.00916   0.00310  -0.0800   0.3640   1.0000
   4.750   0.9223   0.00930   0.00326  -0.0796   0.3550   1.0000
   5.000   0.9481   0.00948   0.00345  -0.0791   0.3453   1.0000
   5.250   0.9734   0.00967   0.00363  -0.0786   0.3349   1.0000
   5.500   0.9990   0.00985   0.00382  -0.0781   0.3242   1.0000
   5.750   1.0247   0.01003   0.00402  -0.0777   0.3141   1.0000
   6.000   1.0500   0.01023   0.00425  -0.0772   0.3028   1.0000
   6.250   1.0751   0.01046   0.00448  -0.0766   0.2908   1.0000
   6.500   1.0998   0.01070   0.00471  -0.0761   0.2740   1.0000
   6.750   1.1235   0.01104   0.00497  -0.0754   0.2487   1.0000
   7.000   1.1467   0.01145   0.00528  -0.0746   0.2218   1.0000
   7.250   1.1696   0.01191   0.00566  -0.0738   0.1967   1.0000
   7.500   1.1916   0.01246   0.00609  -0.0729   0.1694   1.0000
   7.750   1.2130   0.01307   0.00659  -0.0719   0.1417   1.0000
   8.000   1.2332   0.01379   0.00717  -0.0708   0.1112   1.0000
   8.250   1.2516   0.01471   0.00789  -0.0694   0.0776   1.0000
   8.500   1.2652   0.01611   0.00898  -0.0674   0.0323   1.0000
   8.750   1.2782   0.01756   0.01032  -0.0650   0.0127   1.0000
   9.000   1.2974   0.01831   0.01118  -0.0636   0.0111   1.0000
   9.250   1.3155   0.01913   0.01210  -0.0620   0.0099   1.0000
   9.500   1.3305   0.02020   0.01328  -0.0601   0.0090   1.0000
   9.750   1.3400   0.02167   0.01492  -0.0573   0.0084   1.0000
  10.000   1.3513   0.02286   0.01625  -0.0548   0.0082   1.0000
  10.250   1.3616   0.02404   0.01755  -0.0523   0.0079   1.0000
  10.500   1.3684   0.02529   0.01896  -0.0493   0.0078   1.0000
  10.750   1.3704   0.02663   0.02042  -0.0455   0.0077   1.0000
  11.000   1.3712   0.02808   0.02200  -0.0419   0.0076   1.0000
  11.250   1.3710   0.02966   0.02371  -0.0385   0.0075   1.0000
  11.500   1.3702   0.03140   0.02558  -0.0356   0.0074   1.0000
  11.750   1.3693   0.03331   0.02762  -0.0331   0.0073   1.0000
  12.000   1.3704   0.03516   0.02958  -0.0314   0.0070   1.0000
  12.250   1.3674   0.03765   0.03220  -0.0299   0.0068   1.0000
  12.500   1.3646   0.04038   0.03507  -0.0290   0.0067   1.0000
  12.750   1.3616   0.04338   0.03821  -0.0285   0.0067   1.0000
  13.000   1.3565   0.04689   0.04187  -0.0284   0.0067   1.0000
  13.250   1.3524   0.05046   0.04559  -0.0288   0.0066   1.0000
  13.500   1.3469   0.05439   0.04967  -0.0294   0.0066   1.0000
  13.750   1.3408   0.05855   0.05399  -0.0303   0.0066   1.0000
  14.000   1.3348   0.06281   0.05839  -0.0316   0.0065   1.0000
  14.250   1.3267   0.06753   0.06326  -0.0331   0.0065   1.0000
  14.500   1.3163   0.07275   0.06866  -0.0348   0.0065   1.0000
  14.750   1.3056   0.07817   0.07425  -0.0369   0.0066   1.0000
  15.000   1.2948   0.08380   0.08004  -0.0394   0.0065   1.0000
  15.250   1.2817   0.09010   0.08651  -0.0424   0.0066   1.0000
  15.500   1.2683   0.09669   0.09327  -0.0457   0.0066   1.0000
  15.750   1.2528   0.10403   0.10079  -0.0495   0.0067   1.0000
  16.000   1.2397   0.11114   0.10805  -0.0535   0.0066   1.0000
  16.250   1.2212   0.11977   0.11687  -0.0584   0.0068   1.0000
  16.500   1.2044   0.12841   0.12567  -0.0635   0.0068   1.0000
  16.750   1.1878   0.13736   0.13477  -0.0689   0.0069   1.0000
  17.000   1.1714   0.14663   0.14419  -0.0746   0.0070   1.0000
  17.250   1.1534   0.15684   0.15453  -0.0810   0.0072   1.0000
  17.500   1.1344   0.16794   0.16576  -0.0879   0.0073   1.0000
  17.750   1.1136   0.18042   0.17835  -0.0954   0.0075   1.0000
  18.000   1.0813   0.19857   0.19657  -0.1055   0.0080   1.0000
  18.250   1.0747   0.20728   0.20528  -0.1099   0.0084   1.0000
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