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S3014-095-85 (s3014-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S3014-095-85 (s3014-il)
Reynolds number: 500,000
Max Cl/Cd: 82.62 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3014-il-500000-n5.txt
Download as CSV file: xf-s3014-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3014-095-85                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4738   0.08139   0.07924  -0.0244   1.0000   0.0088
  -9.000  -0.4824   0.07547   0.07336  -0.0279   1.0000   0.0090
  -8.750  -0.4939   0.06953   0.06748  -0.0319   1.0000   0.0089
  -8.500  -0.5097   0.06186   0.05985  -0.0398   0.9852   0.0088
  -8.250  -0.5432   0.03905   0.03639  -0.0554   0.9328   0.0089
  -8.000  -0.5527   0.03155   0.02821  -0.0545   0.9150   0.0091
  -7.750  -0.5422   0.02817   0.02435  -0.0535   0.9043   0.0095
  -7.500  -0.5236   0.02660   0.02242  -0.0526   0.8962   0.0099
  -7.250  -0.5116   0.02303   0.01835  -0.0514   0.8878   0.0103
  -7.000  -0.4919   0.02117   0.01622  -0.0506   0.8808   0.0106
  -6.750  -0.4699   0.01993   0.01479  -0.0500   0.8741   0.0109
  -6.500  -0.4467   0.01882   0.01349  -0.0494   0.8680   0.0112
  -6.250  -0.4228   0.01781   0.01230  -0.0489   0.8616   0.0115
  -6.000  -0.3985   0.01686   0.01116  -0.0483   0.8558   0.0118
  -5.750  -0.3735   0.01595   0.01008  -0.0478   0.8494   0.0121
  -5.250  -0.3226   0.01448   0.00834  -0.0469   0.8376   0.0130
  -5.000  -0.2968   0.01386   0.00759  -0.0465   0.8317   0.0135
  -4.750  -0.2710   0.01316   0.00678  -0.0460   0.8258   0.0138
  -4.500  -0.2451   0.01255   0.00606  -0.0456   0.8196   0.0141
  -4.250  -0.2190   0.01204   0.00546  -0.0452   0.8140   0.0144
  -4.000  -0.1924   0.01160   0.00495  -0.0448   0.8074   0.0147
  -3.750  -0.1659   0.01124   0.00451  -0.0445   0.8013   0.0149
  -3.500  -0.1399   0.01065   0.00384  -0.0441   0.7946   0.0156
  -3.250  -0.1134   0.01027   0.00337  -0.0437   0.7879   0.0162
  -3.000  -0.0863   0.00998   0.00302  -0.0435   0.7809   0.0169
  -2.750  -0.0592   0.00974   0.00273  -0.0432   0.7738   0.0180
  -2.500  -0.0317   0.00954   0.00248  -0.0431   0.7663   0.0192
  -2.250  -0.0044   0.00937   0.00223  -0.0428   0.7588   0.0201
  -2.000   0.0233   0.00922   0.00203  -0.0427   0.7505   0.0213
  -1.750   0.0507   0.00905   0.00185  -0.0424   0.7422   0.0288
  -1.500   0.0772   0.00871   0.00169  -0.0422   0.7323   0.0812
  -1.250   0.1036   0.00837   0.00156  -0.0420   0.7214   0.1503
  -1.000   0.1302   0.00812   0.00146  -0.0418   0.7096   0.2105
  -0.750   0.1564   0.00782   0.00138  -0.0415   0.6970   0.2922
  -0.500   0.1807   0.00729   0.00134  -0.0411   0.6836   0.4503
  -0.250   0.2031   0.00672   0.00132  -0.0401   0.6692   0.6272
   0.000   0.2267   0.00644   0.00132  -0.0391   0.6547   0.7261
   0.250   0.2502   0.00621   0.00133  -0.0378   0.6401   0.8147
   0.500   0.2810   0.00606   0.00136  -0.0380   0.6245   0.9104
   0.750   0.3316   0.00614   0.00137  -0.0428   0.6059   0.9591
   1.000   0.3704   0.00625   0.00138  -0.0451   0.5877   0.9805
   1.250   0.4074   0.00637   0.00139  -0.0471   0.5684   0.9932
   1.500   0.4447   0.00649   0.00141  -0.0492   0.5483   1.0000
   1.750   0.4699   0.00663   0.00145  -0.0487   0.5283   1.0000
   2.000   0.4951   0.00678   0.00150  -0.0482   0.5083   1.0000
   2.250   0.5203   0.00695   0.00157  -0.0476   0.4866   1.0000
   2.500   0.5453   0.00714   0.00165  -0.0471   0.4637   1.0000
   2.750   0.5704   0.00734   0.00175  -0.0466   0.4404   1.0000
   3.000   0.5952   0.00756   0.00186  -0.0460   0.4164   1.0000
   3.250   0.6200   0.00779   0.00199  -0.0455   0.3920   1.0000
   3.500   0.6448   0.00803   0.00213  -0.0450   0.3681   1.0000
   3.750   0.6694   0.00829   0.00229  -0.0444   0.3448   1.0000
   4.000   0.6940   0.00856   0.00246  -0.0439   0.3222   1.0000
   4.250   0.7186   0.00882   0.00264  -0.0433   0.3016   1.0000
   4.500   0.7432   0.00909   0.00283  -0.0428   0.2817   1.0000
   5.000   0.7922   0.00965   0.00327  -0.0417   0.2470   1.0000
   5.250   0.8169   0.00992   0.00349  -0.0412   0.2320   1.0000
   5.500   0.8414   0.01020   0.00372  -0.0407   0.2168   1.0000
   5.750   0.8659   0.01048   0.00397  -0.0402   0.2038   1.0000
   6.000   0.8903   0.01078   0.00425  -0.0397   0.1903   1.0000
   6.250   0.9144   0.01110   0.00452  -0.0392   0.1756   1.0000
   6.500   0.9379   0.01148   0.00483  -0.0386   0.1566   1.0000
   6.750   0.9609   0.01192   0.00517  -0.0379   0.1368   1.0000
   7.000   0.9841   0.01232   0.00551  -0.0373   0.1208   1.0000
   7.250   1.0070   0.01274   0.00590  -0.0366   0.1062   1.0000
   7.500   1.0288   0.01327   0.00633  -0.0359   0.0878   1.0000
   7.750   1.0506   0.01379   0.00677  -0.0351   0.0721   1.0000
   8.000   1.0722   0.01431   0.00724  -0.0343   0.0587   1.0000
   8.250   1.0930   0.01490   0.00776  -0.0334   0.0448   1.0000
   8.500   1.1117   0.01568   0.00845  -0.0323   0.0276   1.0000
   8.750   1.1288   0.01658   0.00925  -0.0309   0.0119   1.0000
   9.000   1.1471   0.01734   0.01001  -0.0296   0.0075   1.0000
   9.250   1.1664   0.01797   0.01070  -0.0285   0.0064   1.0000
   9.500   1.1846   0.01866   0.01145  -0.0272   0.0056   1.0000
   9.750   1.2014   0.01942   0.01231  -0.0258   0.0049   1.0000
  10.000   1.2186   0.02011   0.01309  -0.0244   0.0047   1.0000
  10.250   1.2346   0.02083   0.01392  -0.0229   0.0045   1.0000
  10.500   1.2481   0.02161   0.01481  -0.0211   0.0044   1.0000
  10.750   1.2587   0.02242   0.01571  -0.0188   0.0042   1.0000
  11.000   1.2680   0.02333   0.01672  -0.0165   0.0041   1.0000
  11.250   1.2763   0.02435   0.01784  -0.0143   0.0040   1.0000
  11.500   1.2835   0.02550   0.01910  -0.0122   0.0039   1.0000
  11.750   1.2900   0.02676   0.02047  -0.0103   0.0037   1.0000
  12.000   1.2958   0.02813   0.02194  -0.0086   0.0037   1.0000
  12.250   1.2990   0.02978   0.02371  -0.0069   0.0035   1.0000
  12.500   1.3021   0.03153   0.02557  -0.0054   0.0035   1.0000
  12.750   1.3024   0.03362   0.02778  -0.0041   0.0034   1.0000
  13.000   1.3031   0.03579   0.03009  -0.0032   0.0033   1.0000
  13.250   1.3008   0.03839   0.03281  -0.0024   0.0032   1.0000
  13.500   1.2980   0.04121   0.03577  -0.0021   0.0032   1.0000
  13.750   1.2914   0.04463   0.03932  -0.0021   0.0031   1.0000
  14.000   1.2833   0.04848   0.04330  -0.0026   0.0031   1.0000
  14.250   1.2751   0.05257   0.04754  -0.0035   0.0031   1.0000
  14.500   1.2697   0.05651   0.05161  -0.0046   0.0031   1.0000
  14.750   1.2598   0.06132   0.05655  -0.0063   0.0030   1.0000
  15.000   1.2500   0.06638   0.06176  -0.0083   0.0030   1.0000
  15.250   1.2352   0.07246   0.06798  -0.0109   0.0030   1.0000
  15.500   1.2308   0.07714   0.07277  -0.0131   0.0031   1.0000
  15.750   1.2128   0.08423   0.08001  -0.0164   0.0030   1.0000
  16.000   1.2054   0.08972   0.08562  -0.0191   0.0030   1.0000
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