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S4310 (s4310-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 500,000
Max Cl/Cd: 112.93 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4310-il-500000.txt
Download as CSV file: xf-s4310-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4310                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3079   0.11101   0.10876  -0.0364   1.0000   0.0160
 -10.250  -0.3033   0.10748   0.10525  -0.0378   1.0000   0.0160
 -10.000  -0.3036   0.10275   0.10055  -0.0387   1.0000   0.0163
  -9.750  -0.2987   0.09967   0.09750  -0.0395   1.0000   0.0165
  -9.500  -0.2915   0.09731   0.09516  -0.0394   1.0000   0.0168
  -9.250  -0.2869   0.09448   0.09236  -0.0401   1.0000   0.0170
  -9.000  -0.2837   0.09178   0.08970  -0.0407   1.0000   0.0173
  -8.750  -0.2720   0.08809   0.08604  -0.0441   0.9875   0.0176
  -8.500  -0.2526   0.08353   0.08146  -0.0502   0.9745   0.0181
  -8.250  -0.2320   0.07853   0.07643  -0.0574   0.9608   0.0188
  -8.000  -0.2152   0.07362   0.07149  -0.0640   0.9423   0.0193
  -7.750  -0.2155   0.06923   0.06703  -0.0674   0.9162   0.0204
  -7.500  -0.2224   0.06571   0.06345  -0.0691   0.8954   0.0206
  -7.250  -0.2223   0.05918   0.05684  -0.0767   0.8776   0.0213
  -7.000  -0.2173   0.05379   0.05131  -0.0807   0.8655   0.0213
  -6.750  -0.2141   0.04717   0.04440  -0.0842   0.8546   0.0214
  -6.500  -0.2205   0.03867   0.03555  -0.0868   0.8438   0.0220
  -6.250  -0.2047   0.03665   0.03347  -0.0870   0.8356   0.0226
  -6.000  -0.1872   0.03455   0.03121  -0.0872   0.8276   0.0233
  -5.750  -0.1684   0.03213   0.02860  -0.0874   0.8197   0.0244
  -5.500  -0.1568   0.02301   0.01848  -0.0867   0.8126   0.0191
  -5.250  -0.1346   0.02005   0.01505  -0.0861   0.8055   0.0191
  -5.000  -0.1101   0.01813   0.01274  -0.0855   0.7985   0.0198
  -4.750  -0.0847   0.01627   0.01052  -0.0850   0.7919   0.0201
  -4.500  -0.0581   0.01515   0.00915  -0.0845   0.7849   0.0208
  -4.250  -0.0311   0.01437   0.00813  -0.0841   0.7786   0.0216
  -4.000  -0.0058   0.01272   0.00637  -0.0837   0.7717   0.0232
  -3.750   0.0213   0.01236   0.00594  -0.0836   0.7655   0.0255
  -3.500   0.0487   0.01186   0.00538  -0.0833   0.7584   0.0272
  -3.250   0.0761   0.01149   0.00488  -0.0830   0.7523   0.0283
  -3.000   0.1024   0.01065   0.00400  -0.0828   0.7454   0.0309
  -2.750   0.1298   0.01035   0.00365  -0.0826   0.7390   0.0336
  -2.500   0.1575   0.01007   0.00331  -0.0825   0.7324   0.0357
  -2.250   0.1852   0.00976   0.00293  -0.0823   0.7257   0.0390
  -2.000   0.2130   0.00954   0.00268  -0.0822   0.7194   0.0455
  -1.750   0.2404   0.00907   0.00241  -0.0821   0.7125   0.0997
  -1.500   0.2672   0.00867   0.00229  -0.0820   0.7065   0.1984
  -1.250   0.2944   0.00831   0.00222  -0.0821   0.6993   0.2927
  -1.000   0.3209   0.00795   0.00217  -0.0820   0.6931   0.4136
  -0.750   0.3467   0.00747   0.00217  -0.0817   0.6859   0.5652
  -0.500   0.3699   0.00699   0.00218  -0.0807   0.6794   0.7333
  -0.250   0.3886   0.00662   0.00227  -0.0779   0.6723   0.9023
   0.000   0.4351   0.00656   0.00217  -0.0814   0.6649   0.9844
   0.250   0.4778   0.00656   0.00209  -0.0846   0.6568   1.0000
   0.500   0.5032   0.00664   0.00206  -0.0840   0.6497   1.0000
   0.750   0.5291   0.00669   0.00206  -0.0836   0.6417   1.0000
   1.250   0.5816   0.00683   0.00207  -0.0829   0.6263   1.0000
   1.500   0.6080   0.00693   0.00209  -0.0825   0.6189   1.0000
   1.750   0.6348   0.00699   0.00212  -0.0823   0.6103   1.0000
   2.000   0.6615   0.00709   0.00215  -0.0820   0.6023   1.0000
   2.250   0.6883   0.00718   0.00219  -0.0818   0.5933   1.0000
   2.500   0.7153   0.00726   0.00225  -0.0816   0.5840   1.0000
   2.750   0.7420   0.00738   0.00230  -0.0814   0.5748   1.0000
   3.000   0.7688   0.00748   0.00236  -0.0812   0.5645   1.0000
   3.250   0.7957   0.00758   0.00245  -0.0810   0.5542   1.0000
   3.500   0.8223   0.00771   0.00253  -0.0808   0.5436   1.0000
   3.750   0.8488   0.00786   0.00262  -0.0805   0.5323   1.0000
   4.000   0.8754   0.00798   0.00272  -0.0803   0.5202   1.0000
   4.250   0.9018   0.00813   0.00285  -0.0801   0.5075   1.0000
   4.500   0.9280   0.00829   0.00298  -0.0798   0.4942   1.0000
   4.750   0.9540   0.00848   0.00312  -0.0796   0.4799   1.0000
   5.000   0.9797   0.00868   0.00329  -0.0792   0.4649   1.0000
   5.250   1.0051   0.00890   0.00346  -0.0789   0.4490   1.0000
   5.500   1.0301   0.00916   0.00366  -0.0785   0.4322   1.0000
   5.750   1.0549   0.00942   0.00387  -0.0781   0.4144   1.0000
   6.000   1.0794   0.00971   0.00411  -0.0776   0.3956   1.0000
   6.250   1.1034   0.01003   0.00437  -0.0771   0.3764   1.0000
   6.500   1.1268   0.01039   0.00465  -0.0765   0.3575   1.0000
   6.750   1.1503   0.01074   0.00495  -0.0759   0.3381   1.0000
   7.000   1.1731   0.01113   0.00528  -0.0753   0.3194   1.0000
   7.250   1.1952   0.01156   0.00564  -0.0745   0.3011   1.0000
   7.500   1.2176   0.01196   0.00600  -0.0738   0.2849   1.0000
   7.750   1.2396   0.01238   0.00637  -0.0731   0.2688   1.0000
   8.000   1.2609   0.01282   0.00678  -0.0722   0.2526   1.0000
   8.250   1.2819   0.01327   0.00720  -0.0713   0.2380   1.0000
   8.500   1.3021   0.01374   0.00763  -0.0703   0.2229   1.0000
   8.750   1.3212   0.01426   0.00810  -0.0692   0.2067   1.0000
   9.000   1.3396   0.01480   0.00859  -0.0679   0.1917   1.0000
   9.250   1.3559   0.01542   0.00914  -0.0664   0.1750   1.0000
   9.500   1.3717   0.01602   0.00969  -0.0648   0.1610   1.0000
   9.750   1.3857   0.01658   0.01024  -0.0628   0.1492   1.0000
  10.000   1.3987   0.01718   0.01083  -0.0608   0.1389   1.0000
  10.250   1.4106   0.01785   0.01149  -0.0586   0.1295   1.0000
  10.500   1.4213   0.01863   0.01224  -0.0565   0.1187   1.0000
  10.750   1.4323   0.01943   0.01304  -0.0546   0.1085   1.0000
  11.000   1.4436   0.02025   0.01387  -0.0528   0.0996   1.0000
  11.250   1.4536   0.02119   0.01481  -0.0509   0.0918   1.0000
  11.750   1.4709   0.02338   0.01697  -0.0474   0.0736   1.0000
  12.000   1.4794   0.02456   0.01816  -0.0459   0.0662   1.0000
  12.250   1.4856   0.02596   0.01955  -0.0442   0.0583   1.0000
  12.500   1.4923   0.02739   0.02098  -0.0428   0.0508   1.0000
  12.750   1.4949   0.02920   0.02277  -0.0413   0.0406   1.0000
  13.000   1.4940   0.03138   0.02490  -0.0397   0.0295   1.0000
  13.250   1.4876   0.03417   0.02763  -0.0381   0.0182   1.0000
  13.500   1.4819   0.03706   0.03052  -0.0368   0.0119   1.0000
  13.750   1.4790   0.03982   0.03334  -0.0359   0.0097   1.0000
  14.000   1.4801   0.04226   0.03589  -0.0352   0.0089   1.0000
  14.250   1.4785   0.04508   0.03881  -0.0348   0.0082   1.0000
  14.500   1.4750   0.04825   0.04209  -0.0345   0.0076   1.0000
  14.750   1.4708   0.05164   0.04561  -0.0344   0.0073   1.0000
  15.000   1.4689   0.05489   0.04898  -0.0346   0.0071   1.0000
  15.250   1.4653   0.05848   0.05269  -0.0350   0.0068   1.0000
  15.500   1.4625   0.06209   0.05643  -0.0356   0.0066   1.0000
  15.750   1.4559   0.06636   0.06083  -0.0365   0.0064   1.0000
  16.000   1.4487   0.07089   0.06550  -0.0376   0.0063   1.0000
  16.250   1.4416   0.07554   0.07027  -0.0390   0.0061   1.0000
  16.500   1.4339   0.08042   0.07529  -0.0406   0.0059   1.0000
  16.750   1.4241   0.08582   0.08082  -0.0425   0.0059   1.0000
  17.000   1.4109   0.09197   0.08711  -0.0449   0.0057   1.0000
  17.250   1.3996   0.09792   0.09319  -0.0473   0.0057   1.0000
  17.500   1.3871   0.10427   0.09967  -0.0501   0.0056   1.0000
  17.750   1.3750   0.11067   0.10620  -0.0530   0.0056   1.0000
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