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REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: REPUBLIC S-3 AIRFOIL (s3-il)
Reynolds number: 50,000
Max Cl/Cd: 23.58 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s3-il-50000.txt
Download as CSV file: xf-s3-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: REPUBLIC S-3 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4489   0.09508   0.08875   0.0211   1.0000   0.4332
  -7.750  -0.4299   0.09051   0.08416   0.0207   1.0000   0.4407
  -6.500  -0.5767   0.05090   0.04352  -0.0203   1.0000   0.1522
  -6.250  -0.5652   0.04707   0.03893  -0.0193   1.0000   0.1390
  -6.000  -0.5470   0.04315   0.03487  -0.0183   1.0000   0.1349
  -5.750  -0.5304   0.03985   0.03093  -0.0167   1.0000   0.1275
  -5.500  -0.5108   0.03749   0.02797  -0.0149   1.0000   0.1236
  -5.250  -0.4905   0.03499   0.02513  -0.0134   1.0000   0.1236
  -5.000  -0.4701   0.03253   0.02243  -0.0119   1.0000   0.1267
  -4.750  -0.4475   0.03030   0.02011  -0.0106   1.0000   0.1301
  -4.500  -0.4239   0.02845   0.01806  -0.0092   1.0000   0.1336
  -4.250  -0.4007   0.02676   0.01626  -0.0077   1.0000   0.1422
  -4.000  -0.3768   0.02526   0.01477  -0.0062   1.0000   0.1520
  -3.750  -0.3557   0.02384   0.01345  -0.0045   1.0000   0.1669
  -3.500  -0.3386   0.02249   0.01227  -0.0024   1.0000   0.1862
  -3.250  -0.3247   0.02109   0.01123  -0.0004   1.0000   0.2216
  -3.000  -0.3229   0.01859   0.01064   0.0036   1.0000   0.4652
  -2.750  -0.0447   0.02233   0.01391  -0.0146   1.0000   0.9775
  -2.500   0.0162   0.02112   0.01240  -0.0228   1.0000   0.9972
  -2.250   0.0324   0.02059   0.01182  -0.0232   1.0000   1.0000
  -2.000   0.0354   0.02031   0.01155  -0.0214   1.0000   1.0000
  -1.750   0.0287   0.02022   0.01150  -0.0183   1.0000   1.0000
  -1.500   0.0115   0.02028   0.01158  -0.0137   1.0000   1.0000
  -1.250  -0.0099   0.02032   0.01162  -0.0085   1.0000   1.0000
  -1.000  -0.0308   0.02028   0.01157  -0.0034   1.0000   1.0000
  -0.750  -0.0491   0.02020   0.01147   0.0015   1.0000   1.0000
  -0.500  -0.0609   0.02021   0.01140   0.0055   1.0000   1.0000
  -0.250  -0.0294   0.02069   0.01174   0.0022   0.9898   1.0000
   0.000   0.0665   0.02153   0.01245  -0.0116   0.9597   1.0000
   0.250   0.1693   0.02189   0.01274  -0.0255   0.9287   1.0000
   0.500   0.2746   0.02156   0.01241  -0.0384   0.8942   1.0000
   0.750   0.3339   0.02110   0.01192  -0.0422   0.8537   1.0000
   1.000   0.3613   0.02091   0.01166  -0.0403   0.8123   1.0000
   1.250   0.3805   0.02081   0.01143  -0.0369   0.7743   1.0000
   1.500   0.3961   0.02086   0.01135  -0.0332   0.7365   1.0000
   1.750   0.4123   0.02094   0.01126  -0.0296   0.7019   1.0000
   2.000   0.4274   0.02120   0.01139  -0.0265   0.6654   1.0000
   2.250   0.4445   0.02140   0.01144  -0.0237   0.6327   1.0000
   2.500   0.4628   0.02163   0.01150  -0.0212   0.6026   1.0000
   2.750   0.4821   0.02193   0.01165  -0.0191   0.5748   1.0000
   3.000   0.5025   0.02231   0.01189  -0.0172   0.5502   1.0000
   3.250   0.5234   0.02277   0.01219  -0.0156   0.5274   1.0000
   3.500   0.5447   0.02337   0.01268  -0.0142   0.5066   1.0000
   3.750   0.5663   0.02411   0.01335  -0.0130   0.4877   1.0000
   4.000   0.5885   0.02496   0.01418  -0.0121   0.4720   1.0000
   4.250   0.6109   0.02592   0.01514  -0.0112   0.4582   1.0000
   4.500   0.6332   0.02695   0.01616  -0.0105   0.4457   1.0000
   4.750   0.6562   0.02795   0.01714  -0.0097   0.4344   1.0000
   5.000   0.6782   0.02913   0.01842  -0.0091   0.4236   1.0000
   5.250   0.6982   0.03071   0.02020  -0.0087   0.4148   1.0000
   5.500   0.7217   0.03196   0.02147  -0.0082   0.4075   1.0000
   5.750   0.7381   0.03398   0.02379  -0.0078   0.3994   1.0000
   6.000   0.7625   0.03513   0.02495  -0.0072   0.3918   1.0000
   6.250   0.7738   0.03780   0.02803  -0.0070   0.3847   1.0000
   6.500   0.7952   0.03937   0.02968  -0.0064   0.3779   1.0000
   6.750   0.8024   0.04242   0.03306  -0.0062   0.3698   1.0000
   7.000   0.8238   0.04360   0.03432  -0.0051   0.3594   1.0000
   7.250   0.8487   0.04417   0.03487  -0.0038   0.3466   1.0000
   7.500   0.8526   0.04701   0.03803  -0.0031   0.3351   1.0000
   7.750   0.8546   0.05026   0.04151  -0.0025   0.3252   1.0000
   8.000   0.8709   0.05191   0.04326  -0.0014   0.3142   1.0000
   8.250   0.8997   0.05236   0.04376   0.0000   0.3026   1.0000
   8.500   0.8507   0.06138   0.05308  -0.0014   0.2989   1.0000
   8.750   0.7861   0.07244   0.06408  -0.0055   0.2996   1.0000
   9.000   0.8124   0.07283   0.06459  -0.0031   0.2870   1.0000
   9.250   0.7584   0.08428   0.07588  -0.0096   0.2891   1.0000
   9.500   0.7379   0.09137   0.08291  -0.0127   0.2877   1.0000
   9.750   0.7270   0.09772   0.08923  -0.0153   0.2881   1.0000
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