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S4310 (s4310-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 500,000
Max Cl/Cd: 102.5 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4310-il-500000-n5.txt
Download as CSV file: xf-s4310-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2539   0.08158   0.07915  -0.0567   0.9009   0.0075
  -8.750  -0.2551   0.07754   0.07505  -0.0584   0.8827   0.0074
  -8.500  -0.2585   0.07347   0.07094  -0.0600   0.8664   0.0074
  -8.250  -0.2659   0.06901   0.06645  -0.0619   0.8508   0.0074
  -8.000  -0.2772   0.06471   0.06213  -0.0637   0.8362   0.0073
  -7.750  -0.2900   0.05813   0.05550  -0.0696   0.8226   0.0075
  -7.500  -0.3695   0.02329   0.01894  -0.0844   0.8082   0.0079
  -7.250  -0.3521   0.02002   0.01508  -0.0839   0.8004   0.0083
  -7.000  -0.3300   0.01823   0.01289  -0.0835   0.7935   0.0086
  -6.750  -0.3058   0.01710   0.01154  -0.0833   0.7861   0.0090
  -6.500  -0.2797   0.01672   0.01107  -0.0831   0.7794   0.0094
  -6.250  -0.2532   0.01635   0.01061  -0.0830   0.7722   0.0098
  -6.000  -0.2272   0.01569   0.00978  -0.0828   0.7656   0.0104
  -5.750  -0.2012   0.01484   0.00874  -0.0825   0.7586   0.0110
  -5.500  -0.1750   0.01411   0.00780  -0.0822   0.7521   0.0116
  -5.250  -0.1486   0.01339   0.00694  -0.0820   0.7453   0.0122
  -5.000  -0.1218   0.01294   0.00641  -0.0819   0.7387   0.0128
  -4.750  -0.0946   0.01256   0.00597  -0.0818   0.7323   0.0136
  -4.500  -0.0674   0.01218   0.00550  -0.0816   0.7257   0.0145
  -4.250  -0.0398   0.01192   0.00514  -0.0815   0.7195   0.0156
  -4.000  -0.0128   0.01144   0.00459  -0.0814   0.7129   0.0168
  -3.750   0.0144   0.01110   0.00419  -0.0812   0.7068   0.0179
  -3.500   0.0420   0.01080   0.00384  -0.0811   0.7001   0.0191
  -3.250   0.0696   0.01058   0.00354  -0.0810   0.6939   0.0205
  -3.000   0.0975   0.01037   0.00328  -0.0810   0.6875   0.0216
  -2.750   0.1250   0.01004   0.00289  -0.0809   0.6811   0.0233
  -2.500   0.1529   0.00985   0.00264  -0.0808   0.6749   0.0250
  -2.250   0.1808   0.00970   0.00244  -0.0808   0.6682   0.0274
  -2.000   0.2087   0.00955   0.00224  -0.0807   0.6620   0.0304
  -1.750   0.2367   0.00939   0.00209  -0.0806   0.6551   0.0387
  -1.500   0.2643   0.00919   0.00195  -0.0806   0.6488   0.0691
  -1.250   0.2921   0.00897   0.00186  -0.0806   0.6419   0.1128
  -1.000   0.3195   0.00876   0.00179  -0.0806   0.6352   0.1683
  -0.750   0.3471   0.00855   0.00175  -0.0807   0.6281   0.2293
  -0.500   0.3745   0.00837   0.00171  -0.0807   0.6208   0.2931
  -0.250   0.4016   0.00809   0.00170  -0.0807   0.6131   0.3909
   0.250   0.4517   0.00723   0.00177  -0.0798   0.5970   0.7081
   0.500   0.4728   0.00693   0.00184  -0.0780   0.5894   0.8464
   0.750   0.4978   0.00685   0.00187  -0.0769   0.5808   0.9263
   1.000   0.5357   0.00687   0.00185  -0.0789   0.5718   0.9722
   1.250   0.5755   0.00693   0.00183  -0.0815   0.5623   1.0000
   1.500   0.6022   0.00702   0.00186  -0.0812   0.5531   1.0000
   1.750   0.6287   0.00712   0.00189  -0.0810   0.5439   1.0000
   2.000   0.6553   0.00724   0.00194  -0.0807   0.5338   1.0000
   2.250   0.6820   0.00735   0.00199  -0.0805   0.5232   1.0000
   2.500   0.7086   0.00747   0.00206  -0.0803   0.5120   1.0000
   2.750   0.7351   0.00762   0.00213  -0.0800   0.5000   1.0000
   3.000   0.7615   0.00777   0.00222  -0.0798   0.4872   1.0000
   3.250   0.7878   0.00794   0.00233  -0.0796   0.4740   1.0000
   3.750   0.8401   0.00830   0.00256  -0.0790   0.4456   1.0000
   4.000   0.8660   0.00851   0.00270  -0.0788   0.4307   1.0000
   4.250   0.8918   0.00872   0.00286  -0.0785   0.4149   1.0000
   4.500   0.9174   0.00895   0.00303  -0.0782   0.3989   1.0000
   4.750   0.9427   0.00921   0.00322  -0.0778   0.3816   1.0000
   5.000   0.9678   0.00948   0.00342  -0.0775   0.3647   1.0000
   5.250   0.9925   0.00978   0.00365  -0.0771   0.3472   1.0000
   5.500   1.0170   0.01009   0.00389  -0.0766   0.3305   1.0000
   5.750   1.0412   0.01041   0.00414  -0.0762   0.3134   1.0000
   6.000   1.0653   0.01073   0.00442  -0.0757   0.2969   1.0000
   6.250   1.0891   0.01108   0.00471  -0.0752   0.2808   1.0000
   6.500   1.1127   0.01143   0.00500  -0.0747   0.2659   1.0000
   6.750   1.1359   0.01179   0.00532  -0.0741   0.2509   1.0000
   7.000   1.1590   0.01216   0.00565  -0.0735   0.2373   1.0000
   7.250   1.1815   0.01255   0.00600  -0.0728   0.2230   1.0000
   7.500   1.2039   0.01294   0.00636  -0.0721   0.2111   1.0000
   7.750   1.2257   0.01334   0.00673  -0.0713   0.1993   1.0000
   8.000   1.2468   0.01379   0.00714  -0.0705   0.1864   1.0000
   8.250   1.2677   0.01422   0.00756  -0.0696   0.1750   1.0000
   8.500   1.2881   0.01466   0.00798  -0.0686   0.1642   1.0000
   8.750   1.3068   0.01518   0.00846  -0.0674   0.1512   1.0000
   9.000   1.3247   0.01571   0.00896  -0.0661   0.1393   1.0000
   9.250   1.3399   0.01635   0.00954  -0.0644   0.1240   1.0000
   9.500   1.3532   0.01695   0.01010  -0.0624   0.1123   1.0000
   9.750   1.3654   0.01760   0.01072  -0.0602   0.1017   1.0000
  10.000   1.3774   0.01829   0.01139  -0.0582   0.0931   1.0000
  10.250   1.3906   0.01894   0.01206  -0.0563   0.0859   1.0000
  10.500   1.4017   0.01974   0.01285  -0.0544   0.0777   1.0000
  10.750   1.4114   0.02067   0.01377  -0.0525   0.0687   1.0000
  11.000   1.4211   0.02164   0.01473  -0.0506   0.0608   1.0000
  11.250   1.4317   0.02260   0.01571  -0.0490   0.0550   1.0000
  11.500   1.4392   0.02381   0.01690  -0.0472   0.0471   1.0000
  11.750   1.4450   0.02520   0.01826  -0.0455   0.0384   1.0000
  12.000   1.4513   0.02662   0.01968  -0.0439   0.0315   1.0000
  12.250   1.4544   0.02835   0.02139  -0.0423   0.0238   1.0000
  12.500   1.4582   0.03011   0.02316  -0.0409   0.0180   1.0000
  12.750   1.4587   0.03222   0.02528  -0.0394   0.0114   1.0000
  13.000   1.4588   0.03446   0.02756  -0.0382   0.0073   1.0000
  13.250   1.4614   0.03656   0.02973  -0.0372   0.0059   1.0000
  13.500   1.4637   0.03877   0.03203  -0.0364   0.0051   1.0000
  13.750   1.4672   0.04094   0.03429  -0.0358   0.0047   1.0000
  14.000   1.4700   0.04323   0.03668  -0.0353   0.0044   1.0000
  14.250   1.4712   0.04577   0.03933  -0.0349   0.0041   1.0000
  14.500   1.4712   0.04857   0.04223  -0.0347   0.0039   1.0000
  14.750   1.4712   0.05144   0.04522  -0.0347   0.0038   1.0000
  15.000   1.4699   0.05460   0.04849  -0.0348   0.0037   1.0000
  15.250   1.4659   0.05822   0.05223  -0.0352   0.0035   1.0000
  15.500   1.4646   0.06160   0.05574  -0.0357   0.0034   1.0000
  15.750   1.4610   0.06541   0.05968  -0.0365   0.0033   1.0000
  16.000   1.4572   0.06937   0.06379  -0.0374   0.0033   1.0000
  16.250   1.4523   0.07363   0.06817  -0.0386   0.0032   1.0000
  16.500   1.4477   0.07795   0.07262  -0.0399   0.0031   1.0000
  16.750   1.4401   0.08288   0.07768  -0.0416   0.0031   1.0000
  17.000   1.4316   0.08811   0.08305  -0.0435   0.0029   1.0000
  17.250   1.4228   0.09352   0.08859  -0.0456   0.0029   1.0000
  17.500   1.4129   0.09924   0.09444  -0.0480   0.0028   1.0000
  17.750   1.4025   0.10521   0.10056  -0.0507   0.0028   1.0000
  18.000   1.3922   0.11127   0.10674  -0.0534   0.0028   1.0000
  18.250   1.3790   0.11800   0.11362  -0.0567   0.0028   1.0000
  18.500   1.3678   0.12446   0.12021  -0.0599   0.0028   1.0000
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