Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S4310 (s4310-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4310 (s4310-il)
Reynolds number: 200,000
Max Cl/Cd: 81.03 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4310-il-200000.txt
Download as CSV file: xf-s4310-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2134   0.09843   0.09540  -0.0402   1.0000   0.0389
  -9.500  -0.2244   0.09784   0.09490  -0.0367   1.0000   0.0395
  -9.250  -0.2911   0.09945   0.09615  -0.0421   1.0000   0.0378
  -9.000  -0.2814   0.09685   0.09358  -0.0408   1.0000   0.0389
  -8.750  -0.2782   0.09442   0.09121  -0.0406   1.0000   0.0397
  -8.500  -0.2821   0.09254   0.08941  -0.0395   1.0000   0.0405
  -8.250  -0.3056   0.09262   0.08961  -0.0346   0.9997   0.0407
  -8.000  -0.2853   0.08803   0.08503  -0.0410   0.9929   0.0427
  -7.750  -0.2672   0.08191   0.07892  -0.0564   0.9810   0.0463
  -7.500  -0.2380   0.07320   0.07008  -0.0782   0.9696   0.0470
  -7.250  -0.2277   0.07013   0.06712  -0.0713   0.9661   0.0490
  -7.000  -0.2028   0.06682   0.06378  -0.0750   0.9596   0.0512
  -6.250  -0.1528   0.05164   0.04827  -0.0945   0.9248   0.0622
  -6.000  -0.1379   0.04906   0.04561  -0.0950   0.9148   0.0650
  -5.750  -0.1292   0.04433   0.04017  -0.0988   0.9013   0.0731
  -5.500  -0.1131   0.04127   0.03726  -0.0980   0.8928   0.0749
  -5.250  -0.0953   0.03919   0.03511  -0.0973   0.8853   0.0780
  -5.000  -0.0789   0.03607   0.03150  -0.0979   0.8752   0.0881
  -4.750  -0.0574   0.02603   0.02024  -0.0962   0.8691   0.0434
  -4.500  -0.0349   0.02352   0.01728  -0.0953   0.8603   0.0430
  -4.250  -0.0101   0.02167   0.01501  -0.0943   0.8547   0.0441
  -4.000   0.0148   0.01991   0.01290  -0.0934   0.8461   0.0441
  -3.750   0.0411   0.01859   0.01126  -0.0925   0.8405   0.0452
  -3.500   0.0668   0.01753   0.01001  -0.0919   0.8324   0.0481
  -3.250   0.0925   0.01645   0.00888  -0.0911   0.8265   0.0511
  -3.000   0.1184   0.01576   0.00815  -0.0905   0.8189   0.0541
  -2.750   0.1450   0.01530   0.00756  -0.0898   0.8125   0.0588
  -2.500   0.1701   0.01450   0.00682  -0.0893   0.8054   0.0653
  -2.250   0.1962   0.01393   0.00621  -0.0886   0.7987   0.0762
  -2.000   0.2208   0.01289   0.00571  -0.0881   0.7921   0.1906
  -1.750   0.2449   0.01218   0.00557  -0.0877   0.7849   0.3575
  -1.500   0.2678   0.01154   0.00549  -0.0867   0.7788   0.5286
  -1.250   0.2833   0.01077   0.00560  -0.0833   0.7713   0.7800
  -1.000   0.3585   0.01031   0.00520  -0.0913   0.7668   0.9995
  -0.750   0.3823   0.01039   0.00514  -0.0906   0.7583   1.0000
  -0.500   0.4069   0.01043   0.00499  -0.0897   0.7522   1.0000
  -0.250   0.4307   0.01053   0.00498  -0.0890   0.7437   1.0000
   0.000   0.4561   0.01057   0.00485  -0.0883   0.7374   1.0000
   0.250   0.4806   0.01068   0.00488  -0.0876   0.7287   1.0000
   0.500   0.5068   0.01072   0.00476  -0.0871   0.7224   1.0000
   0.750   0.5317   0.01082   0.00481  -0.0865   0.7132   1.0000
   1.000   0.5581   0.01089   0.00474  -0.0860   0.7063   1.0000
   1.250   0.5837   0.01097   0.00477  -0.0855   0.6973   1.0000
   1.500   0.6100   0.01106   0.00476  -0.0850   0.6895   1.0000
   1.750   0.6363   0.01113   0.00476  -0.0846   0.6811   1.0000
   2.000   0.6623   0.01123   0.00481  -0.0841   0.6723   1.0000
   2.250   0.6893   0.01130   0.00478  -0.0838   0.6646   1.0000
   2.500   0.7150   0.01141   0.00488  -0.0833   0.6548   1.0000
   2.750   0.7418   0.01150   0.00490  -0.0830   0.6465   1.0000
   3.000   0.7681   0.01159   0.00495  -0.0826   0.6369   1.0000
   3.250   0.7941   0.01170   0.00506  -0.0822   0.6269   1.0000
   3.500   0.8206   0.01179   0.00509  -0.0818   0.6174   1.0000
   3.750   0.8468   0.01189   0.00515  -0.0814   0.6068   1.0000
   4.000   0.8725   0.01200   0.00526  -0.0809   0.5954   1.0000
   4.250   0.8983   0.01212   0.00538  -0.0805   0.5840   1.0000
   4.500   0.9242   0.01224   0.00547  -0.0800   0.5725   1.0000
   4.750   0.9499   0.01237   0.00556  -0.0795   0.5605   1.0000
   5.000   0.9752   0.01251   0.00568  -0.0790   0.5474   1.0000
   5.250   1.0001   0.01267   0.00585  -0.0785   0.5333   1.0000
   5.500   1.0248   0.01285   0.00602  -0.0779   0.5187   1.0000
   5.750   1.0492   0.01305   0.00620  -0.0772   0.5034   1.0000
   6.000   1.0730   0.01328   0.00645  -0.0766   0.4866   1.0000
   6.250   1.0964   0.01353   0.00670  -0.0758   0.4689   1.0000
   6.500   1.1193   0.01383   0.00697  -0.0750   0.4506   1.0000
   6.750   1.1416   0.01417   0.00725  -0.0741   0.4321   1.0000
   7.000   1.1633   0.01454   0.00762  -0.0732   0.4125   1.0000
   7.250   1.1843   0.01496   0.00801  -0.0722   0.3926   1.0000
   7.500   1.2044   0.01545   0.00842  -0.0710   0.3734   1.0000
   7.750   1.2242   0.01593   0.00889  -0.0699   0.3536   1.0000
   8.000   1.2430   0.01648   0.00940  -0.0686   0.3345   1.0000
   8.250   1.2608   0.01708   0.00996  -0.0673   0.3165   1.0000
   8.500   1.2781   0.01771   0.01056  -0.0658   0.2992   1.0000
   8.750   1.2947   0.01834   0.01119  -0.0643   0.2825   1.0000
   9.000   1.3102   0.01902   0.01186  -0.0627   0.2666   1.0000
   9.250   1.3245   0.01973   0.01256  -0.0609   0.2514   1.0000
   9.500   1.3370   0.02047   0.01332  -0.0588   0.2375   1.0000
   9.750   1.3473   0.02125   0.01409  -0.0564   0.2246   1.0000
  10.000   1.3565   0.02212   0.01494  -0.0541   0.2126   1.0000
  10.250   1.3649   0.02308   0.01586  -0.0518   0.2009   1.0000
  10.500   1.3743   0.02400   0.01685  -0.0497   0.1893   1.0000
  10.750   1.3830   0.02504   0.01793  -0.0477   0.1782   1.0000
  11.000   1.3905   0.02619   0.01911  -0.0458   0.1676   1.0000
  11.250   1.3965   0.02748   0.02041  -0.0439   0.1576   1.0000
  11.500   1.4021   0.02883   0.02178  -0.0422   0.1474   1.0000
  11.750   1.4089   0.03016   0.02320  -0.0408   0.1371   1.0000
  12.000   1.4144   0.03170   0.02478  -0.0394   0.1279   1.0000
  12.250   1.4168   0.03350   0.02655  -0.0380   0.1195   1.0000
  12.500   1.4243   0.03501   0.02820  -0.0370   0.1111   1.0000
  12.750   1.4276   0.03694   0.03017  -0.0360   0.1042   1.0000
  13.000   1.4317   0.03885   0.03215  -0.0351   0.0969   1.0000
  13.250   1.4352   0.04090   0.03432  -0.0344   0.0902   1.0000
  13.500   1.4366   0.04321   0.03667  -0.0338   0.0836   1.0000
  13.750   1.4400   0.04542   0.03901  -0.0333   0.0775   1.0000
  14.000   1.4391   0.04814   0.04178  -0.0330   0.0716   1.0000
  14.250   1.4412   0.05066   0.04444  -0.0328   0.0645   1.0000
  14.500   1.4386   0.05384   0.04767  -0.0329   0.0562   1.0000
  14.750   1.4320   0.05765   0.05150  -0.0333   0.0476   1.0000
  15.000   1.4212   0.06219   0.05606  -0.0339   0.0371   1.0000
  15.250   1.4051   0.06767   0.06154  -0.0350   0.0300   1.0000
  15.500   1.3934   0.07279   0.06677  -0.0362   0.0261   1.0000
  15.750   1.3750   0.07912   0.07315  -0.0381   0.0237   1.0000
  16.000   1.3657   0.08429   0.07849  -0.0397   0.0219   1.0000
  16.250   1.3548   0.08988   0.08423  -0.0417   0.0205   1.0000
  16.500   1.3447   0.09547   0.08994  -0.0438   0.0198   1.0000
  16.750   1.3327   0.10152   0.09610  -0.0463   0.0190   1.0000
<< Back to S4310 (s4310-il)

Polar data table (+)

Polar graphs


<< Back to S4310 (s4310-il)