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REPUBLIC S-3 AIRFOIL (s3-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: REPUBLIC S-3 AIRFOIL (s3-il)
Reynolds number: 50,000
Max Cl/Cd: 28.43 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3-il-50000-n5.txt
Download as CSV file: xf-s3-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5347   0.10092   0.09422  -0.0132   1.0000   0.0455
  -9.750  -0.5309   0.09660   0.08993  -0.0141   1.0000   0.0449
  -9.500  -0.5309   0.09167   0.08504  -0.0165   1.0000   0.0443
  -9.250  -0.5353   0.08631   0.07973  -0.0200   1.0000   0.0439
  -9.000  -0.5432   0.08128   0.07473  -0.0233   1.0000   0.0435
  -8.750  -0.5544   0.07674   0.07019  -0.0255   1.0000   0.0431
  -8.500  -0.5644   0.07272   0.06613  -0.0264   1.0000   0.0426
  -8.250  -0.5726   0.06859   0.06189  -0.0272   1.0000   0.0426
  -8.000  -0.5772   0.06461   0.05774  -0.0275   1.0000   0.0425
  -7.750  -0.5790   0.06071   0.05361  -0.0274   1.0000   0.0428
  -7.500  -0.5773   0.05695   0.04956  -0.0268   1.0000   0.0432
  -7.250  -0.5723   0.05337   0.04562  -0.0260   1.0000   0.0437
  -7.000  -0.5639   0.04995   0.04183  -0.0249   1.0000   0.0441
  -6.750  -0.5528   0.04666   0.03815  -0.0237   1.0000   0.0444
  -6.500  -0.5394   0.04358   0.03466  -0.0223   1.0000   0.0447
  -6.250  -0.5238   0.04077   0.03141  -0.0208   1.0000   0.0453
  -6.000  -0.5076   0.03794   0.02834  -0.0196   1.0000   0.0471
  -5.750  -0.4898   0.03587   0.02619  -0.0185   1.0000   0.0501
  -5.500  -0.4706   0.03387   0.02394  -0.0171   1.0000   0.0531
  -5.250  -0.4496   0.03185   0.02158  -0.0156   1.0000   0.0552
  -5.000  -0.4279   0.03022   0.01960  -0.0140   1.0000   0.0588
  -4.750  -0.4080   0.02852   0.01797  -0.0127   1.0000   0.0640
  -4.500  -0.3874   0.02720   0.01656  -0.0110   1.0000   0.0693
  -4.250  -0.3684   0.02603   0.01528  -0.0091   1.0000   0.0757
  -4.000  -0.3528   0.02503   0.01429  -0.0072   1.0000   0.0853
  -3.750  -0.3384   0.02404   0.01323  -0.0051   1.0000   0.0934
  -3.500  -0.3243   0.02318   0.01236  -0.0032   1.0000   0.1078
  -3.250  -0.3093   0.02228   0.01143  -0.0015   1.0000   0.1231
  -3.000  -0.2937   0.02117   0.01051  -0.0003   0.9994   0.1562
  -2.750  -0.2716   0.01862   0.01042   0.0001   0.9859   0.5852
  -2.500  -0.2404   0.01871   0.01084   0.0018   0.9703   0.7289
  -2.250  -0.2034   0.01911   0.01126   0.0030   0.9571   0.8200
  -2.000  -0.1511   0.01964   0.01160   0.0016   0.9479   0.8869
  -1.750  -0.0954   0.01965   0.01129  -0.0035   0.9373   0.9065
  -1.500  -0.0384   0.01960   0.01094  -0.0090   0.9257   0.9217
  -1.250   0.0194   0.01946   0.01056  -0.0147   0.9109   0.9348
  -1.000   0.0771   0.01924   0.01010  -0.0201   0.8918   0.9461
  -0.750   0.1277   0.01901   0.00967  -0.0243   0.8684   0.9578
  -0.500   0.1753   0.01876   0.00923  -0.0278   0.8450   0.9696
  -0.250   0.2187   0.01854   0.00887  -0.0307   0.8209   0.9826
   0.000   0.2602   0.01832   0.00851  -0.0333   0.7960   0.9963
   0.250   0.2841   0.01822   0.00827  -0.0326   0.7718   1.0000
   0.500   0.3007   0.01821   0.00814  -0.0305   0.7463   1.0000
   0.750   0.3173   0.01822   0.00801  -0.0283   0.7200   1.0000
   1.000   0.3339   0.01825   0.00790  -0.0261   0.6917   1.0000
   1.250   0.3506   0.01831   0.00783  -0.0239   0.6608   1.0000
   1.500   0.3676   0.01838   0.00778  -0.0217   0.6274   1.0000
   1.750   0.3854   0.01846   0.00771  -0.0197   0.5934   1.0000
   2.000   0.4039   0.01859   0.00764  -0.0178   0.5605   1.0000
   2.250   0.4230   0.01879   0.00763  -0.0160   0.5282   1.0000
   2.500   0.4426   0.01906   0.00769  -0.0144   0.4988   1.0000
   2.750   0.4627   0.01941   0.00783  -0.0129   0.4724   1.0000
   3.000   0.4839   0.01982   0.00804  -0.0118   0.4486   1.0000
   3.250   0.5056   0.02028   0.00834  -0.0108   0.4280   1.0000
   3.500   0.5280   0.02080   0.00869  -0.0099   0.4100   1.0000
   3.750   0.5510   0.02133   0.00912  -0.0091   0.3939   1.0000
   4.000   0.5743   0.02189   0.00965  -0.0085   0.3792   1.0000
   4.250   0.5977   0.02244   0.01020  -0.0078   0.3653   1.0000
   4.500   0.6212   0.02301   0.01078  -0.0073   0.3524   1.0000
   4.750   0.6449   0.02360   0.01141  -0.0067   0.3408   1.0000
   5.000   0.6687   0.02420   0.01200  -0.0061   0.3310   1.0000
   5.250   0.6927   0.02484   0.01270  -0.0056   0.3219   1.0000
   5.500   0.7170   0.02554   0.01347  -0.0052   0.3143   1.0000
   5.750   0.7412   0.02625   0.01428  -0.0048   0.3071   1.0000
   6.000   0.7653   0.02701   0.01514  -0.0043   0.3001   1.0000
   6.250   0.7890   0.02779   0.01603  -0.0039   0.2930   1.0000
   6.500   0.8129   0.02859   0.01691  -0.0034   0.2868   1.0000
   6.750   0.8359   0.02958   0.01817  -0.0030   0.2805   1.0000
   7.000   0.8601   0.03045   0.01912  -0.0026   0.2754   1.0000
   7.250   0.8816   0.03156   0.02048  -0.0021   0.2688   1.0000
   7.500   0.9040   0.03228   0.02129  -0.0015   0.2605   1.0000
   7.750   0.9229   0.03322   0.02248  -0.0007   0.2508   1.0000
   8.000   0.9444   0.03381   0.02315   0.0001   0.2416   1.0000
   8.250   0.9625   0.03472   0.02433   0.0009   0.2319   1.0000
   8.500   0.9814   0.03573   0.02555   0.0017   0.2243   1.0000
   8.750   1.0001   0.03675   0.02679   0.0025   0.2168   1.0000
   9.000   1.0160   0.03774   0.02803   0.0035   0.2078   1.0000
   9.250   1.0334   0.03800   0.02835   0.0046   0.1975   1.0000
   9.500   1.0468   0.03836   0.02885   0.0059   0.1859   1.0000
   9.750   1.0558   0.03910   0.02988   0.0074   0.1738   1.0000
  10.000   1.0646   0.04001   0.03099   0.0087   0.1633   1.0000
  10.250   1.0761   0.04077   0.03184   0.0100   0.1560   1.0000
  10.500   1.0802   0.04258   0.03403   0.0113   0.1482   1.0000
  10.750   1.0854   0.04369   0.03526   0.0127   0.1413   1.0000
  11.000   1.0813   0.04606   0.03798   0.0142   0.1351   1.0000
  11.250   1.0779   0.04837   0.04052   0.0151   0.1298   1.0000
  11.500   1.0736   0.05101   0.04333   0.0153   0.1256   1.0000
  11.750   1.0573   0.05563   0.04826   0.0142   0.1213   1.0000
  12.000   1.0396   0.06083   0.05366   0.0121   0.1175   1.0000
  12.250   1.0276   0.06552   0.05844   0.0099   0.1135   1.0000
  12.500   0.9997   0.07364   0.06669   0.0057   0.1131   1.0000
  12.750   0.9609   0.08457   0.07764  -0.0002   0.1128   1.0000
  13.000   0.9153   0.09787   0.09082  -0.0071   0.1123   1.0000
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