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S4310 (s4310-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.7 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4310-il-1000000.txt
Download as CSV file: xf-s4310-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.3011   0.10671   0.10512  -0.0340   1.0000   0.0103
 -10.000  -0.2971   0.10337   0.10179  -0.0352   1.0000   0.0104
  -9.750  -0.2929   0.10013   0.09857  -0.0365   1.0000   0.0108
  -9.500  -0.2827   0.09432   0.09277  -0.0423   0.9777   0.0117
  -9.250  -0.2606   0.08850   0.08693  -0.0502   0.9643   0.0118
  -9.000  -0.2403   0.08285   0.08122  -0.0576   0.9464   0.0119
  -8.750  -0.2319   0.07854   0.07682  -0.0612   0.9194   0.0119
  -8.500  -0.2314   0.07502   0.07321  -0.0625   0.8963   0.0119
  -8.250  -0.2336   0.07130   0.06944  -0.0637   0.8776   0.0119
  -8.000  -0.2366   0.06781   0.06589  -0.0649   0.8609   0.0119
  -7.750  -0.2481   0.06367   0.06173  -0.0663   0.8448   0.0119
  -7.500  -0.3127   0.04039   0.03814  -0.0822   0.8258   0.0090
  -7.250  -0.3009   0.03673   0.03430  -0.0836   0.8166   0.0093
  -7.000  -0.3320   0.01690   0.01250  -0.0836   0.8072   0.0091
  -6.750  -0.3066   0.01625   0.01174  -0.0834   0.7996   0.0094
  -6.500  -0.2807   0.01565   0.01102  -0.0833   0.7927   0.0097
  -6.250  -0.2547   0.01496   0.01019  -0.0831   0.7853   0.0101
  -6.000  -0.2288   0.01413   0.00918  -0.0828   0.7787   0.0104
  -5.750  -0.2025   0.01334   0.00824  -0.0826   0.7715   0.0109
  -5.500  -0.1758   0.01272   0.00746  -0.0824   0.7649   0.0114
  -5.250  -0.1480   0.01246   0.00710  -0.0823   0.7579   0.0118
  -5.000  -0.1226   0.01141   0.00592  -0.0820   0.7514   0.0130
  -4.750  -0.0947   0.01117   0.00566  -0.0820   0.7447   0.0138
  -4.500  -0.0672   0.01084   0.00524  -0.0818   0.7381   0.0147
  -4.250  -0.0393   0.01054   0.00487  -0.0818   0.7316   0.0156
  -4.000  -0.0124   0.00994   0.00417  -0.0816   0.7250   0.0166
  -3.750   0.0148   0.00947   0.00366  -0.0815   0.7188   0.0181
  -3.500   0.0428   0.00923   0.00338  -0.0814   0.7121   0.0194
  -3.250   0.0708   0.00908   0.00317  -0.0814   0.7059   0.0208
  -3.000   0.0988   0.00881   0.00285  -0.0813   0.6992   0.0219
  -2.500   0.1546   0.00823   0.00216  -0.0812   0.6865   0.0257
  -2.250   0.1827   0.00809   0.00196  -0.0811   0.6800   0.0273
  -2.000   0.2111   0.00796   0.00179  -0.0811   0.6737   0.0285
  -1.750   0.2393   0.00778   0.00159  -0.0811   0.6670   0.0340
  -1.500   0.2672   0.00754   0.00145  -0.0811   0.6607   0.0675
  -1.250   0.2949   0.00723   0.00136  -0.0812   0.6537   0.1409
  -1.000   0.3226   0.00702   0.00131  -0.0812   0.6470   0.2051
  -0.750   0.3503   0.00677   0.00128  -0.0813   0.6396   0.2843
  -0.500   0.3777   0.00652   0.00126  -0.0813   0.6327   0.3797
  -0.250   0.4051   0.00624   0.00125  -0.0814   0.6253   0.4856
   0.000   0.4315   0.00590   0.00128  -0.0812   0.6183   0.6264
   0.250   0.4560   0.00548   0.00133  -0.0805   0.6110   0.7875
   0.500   0.4776   0.00527   0.00139  -0.0787   0.6042   0.9010
   0.750   0.5117   0.00519   0.00139  -0.0797   0.5963   0.9816
   1.000   0.5560   0.00524   0.00136  -0.0832   0.5880   0.9994
   1.250   0.5832   0.00531   0.00138  -0.0831   0.5798   1.0000
   1.500   0.6097   0.00538   0.00140  -0.0828   0.5715   1.0000
   1.750   0.6362   0.00548   0.00143  -0.0825   0.5624   1.0000
   2.000   0.6633   0.00555   0.00146  -0.0823   0.5530   1.0000
   2.250   0.6903   0.00565   0.00151  -0.0821   0.5433   1.0000
   2.500   0.7172   0.00576   0.00156  -0.0819   0.5329   1.0000
   2.750   0.7445   0.00586   0.00162  -0.0818   0.5224   1.0000
   3.000   0.7716   0.00597   0.00168  -0.0817   0.5111   1.0000
   3.250   0.7986   0.00610   0.00176  -0.0816   0.4992   1.0000
   3.500   0.8255   0.00624   0.00185  -0.0814   0.4870   1.0000
   3.750   0.8523   0.00640   0.00194  -0.0813   0.4736   1.0000
   4.000   0.8790   0.00656   0.00205  -0.0811   0.4596   1.0000
   4.250   0.9056   0.00673   0.00217  -0.0810   0.4448   1.0000
   4.500   0.9321   0.00692   0.00230  -0.0808   0.4292   1.0000
   4.750   0.9584   0.00712   0.00244  -0.0806   0.4128   1.0000
   5.000   0.9844   0.00735   0.00260  -0.0804   0.3951   1.0000
   5.250   1.0101   0.00760   0.00278  -0.0802   0.3769   1.0000
   5.500   1.0354   0.00788   0.00297  -0.0798   0.3584   1.0000
   5.750   1.0609   0.00814   0.00317  -0.0796   0.3405   1.0000
   6.000   1.0860   0.00843   0.00339  -0.0792   0.3217   1.0000
   6.250   1.1107   0.00874   0.00362  -0.0789   0.3039   1.0000
   6.750   1.1597   0.00937   0.00412  -0.0781   0.2714   1.0000
   7.000   1.1840   0.00969   0.00439  -0.0776   0.2566   1.0000
   7.250   1.2080   0.01002   0.00466  -0.0772   0.2412   1.0000
   7.500   1.2314   0.01038   0.00496  -0.0766   0.2250   1.0000
   7.750   1.2544   0.01076   0.00527  -0.0760   0.2085   1.0000
   8.000   1.2769   0.01116   0.00561  -0.0754   0.1927   1.0000
   8.250   1.2992   0.01156   0.00595  -0.0747   0.1790   1.0000
   8.500   1.3204   0.01201   0.00633  -0.0738   0.1636   1.0000
   8.750   1.3409   0.01250   0.00674  -0.0729   0.1484   1.0000
   9.000   1.3613   0.01296   0.00716  -0.0719   0.1357   1.0000
   9.250   1.3807   0.01345   0.00759  -0.0708   0.1228   1.0000
   9.500   1.3996   0.01395   0.00805  -0.0696   0.1112   1.0000
   9.750   1.4175   0.01447   0.00852  -0.0683   0.1004   1.0000
  10.000   1.4338   0.01502   0.00904  -0.0667   0.0898   1.0000
  10.250   1.4468   0.01558   0.00956  -0.0645   0.0811   1.0000
  10.500   1.4578   0.01621   0.01016  -0.0621   0.0721   1.0000
  10.750   1.4693   0.01684   0.01078  -0.0599   0.0642   1.0000
  11.000   1.4789   0.01762   0.01152  -0.0575   0.0552   1.0000
  11.250   1.4873   0.01852   0.01237  -0.0552   0.0462   1.0000
  11.500   1.4930   0.01962   0.01342  -0.0527   0.0357   1.0000
  11.750   1.4916   0.02125   0.01493  -0.0497   0.0214   1.0000
  12.000   1.4898   0.02304   0.01667  -0.0469   0.0106   1.0000
  12.250   1.4917   0.02468   0.01832  -0.0447   0.0064   1.0000
  12.500   1.4984   0.02607   0.01977  -0.0432   0.0055   1.0000
  12.750   1.5053   0.02750   0.02128  -0.0417   0.0049   1.0000
  13.000   1.5128   0.02892   0.02277  -0.0405   0.0046   1.0000
  13.250   1.5188   0.03053   0.02446  -0.0393   0.0044   1.0000
  13.500   1.5231   0.03235   0.02636  -0.0382   0.0041   1.0000
  13.750   1.5251   0.03446   0.02855  -0.0371   0.0038   1.0000
  14.000   1.5272   0.03662   0.03081  -0.0362   0.0036   1.0000
  14.250   1.5252   0.03928   0.03359  -0.0353   0.0035   1.0000
  14.500   1.5256   0.04179   0.03620  -0.0347   0.0034   1.0000
  14.750   1.5264   0.04435   0.03886  -0.0343   0.0034   1.0000
  15.000   1.5274   0.04701   0.04161  -0.0341   0.0034   1.0000
  15.250   1.5261   0.05003   0.04474  -0.0341   0.0033   1.0000
  15.500   1.5252   0.05311   0.04792  -0.0342   0.0033   1.0000
  15.750   1.5205   0.05680   0.05173  -0.0346   0.0032   1.0000
  16.000   1.5157   0.06065   0.05569  -0.0352   0.0032   1.0000
  16.250   1.5103   0.06471   0.05987  -0.0361   0.0031   1.0000
  16.500   1.5059   0.06877   0.06404  -0.0371   0.0031   1.0000
  16.750   1.4973   0.07362   0.06900  -0.0385   0.0031   1.0000
  17.000   1.4880   0.07873   0.07424  -0.0402   0.0030   1.0000
  17.250   1.4782   0.08407   0.07970  -0.0421   0.0030   1.0000
  17.500   1.4675   0.08975   0.08550  -0.0443   0.0030   1.0000
  17.750   1.4559   0.09573   0.09161  -0.0468   0.0029   1.0000
  18.000   1.4448   0.10175   0.09775  -0.0494   0.0029   1.0000
  18.250   1.4293   0.10876   0.10489  -0.0526   0.0029   1.0000
  18.500   1.4170   0.11529   0.11155  -0.0557   0.0029   1.0000
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