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S4320 (s4320-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 100,000
Max Cl/Cd: 61.67 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4320-il-100000-n5.txt
Download as CSV file: xf-s4320-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4320                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2091   0.09347   0.08919  -0.0357   1.0000   0.0505
  -8.500  -0.2172   0.09142   0.08724  -0.0371   1.0000   0.0518
  -8.250  -0.2260   0.08950   0.08543  -0.0381   0.9970   0.0523
  -8.000  -0.2184   0.08517   0.08112  -0.0444   0.9834   0.0526
  -7.750  -0.1989   0.07914   0.07510  -0.0436   0.9771   0.0546
  -7.500  -0.1791   0.07506   0.07100  -0.0451   0.9687   0.0579
  -7.250  -0.1664   0.07070   0.06665  -0.0490   0.9574   0.0599
  -7.000  -0.1560   0.06635   0.06230  -0.0529   0.9445   0.0611
  -6.750  -0.1477   0.06214   0.05807  -0.0565   0.9308   0.0613
  -6.500  -0.1406   0.05779   0.05371  -0.0600   0.9174   0.0601
  -6.250  -0.1843   0.06307   0.05867  -0.0749   0.9326   0.0422
  -6.000  -0.1597   0.05517   0.05055  -0.0825   0.9204   0.0319
  -5.750  -0.1382   0.05113   0.04640  -0.0860   0.9099   0.0312
  -5.500  -0.1149   0.04616   0.04121  -0.0905   0.8990   0.0305
  -5.250  -0.0918   0.04115   0.03587  -0.0943   0.8875   0.0299
  -5.000  -0.0662   0.03608   0.03026  -0.0977   0.8773   0.0307
  -4.750  -0.0380   0.03189   0.02531  -0.0999   0.8690   0.0319
  -4.500  -0.0120   0.02888   0.02175  -0.1007   0.8591   0.0320
  -4.250   0.0156   0.02642   0.01875  -0.1011   0.8511   0.0322
  -4.000   0.0422   0.02425   0.01622  -0.1013   0.8425   0.0328
  -3.750   0.0690   0.02282   0.01456  -0.1013   0.8342   0.0343
  -3.500   0.0964   0.02183   0.01334  -0.1012   0.8263   0.0371
  -3.250   0.1237   0.02067   0.01190  -0.1009   0.8179   0.0388
  -3.000   0.1514   0.01961   0.01060  -0.1004   0.8107   0.0400
  -2.750   0.1782   0.01880   0.00962  -0.1000   0.8022   0.0414
  -2.500   0.2051   0.01794   0.00872  -0.0996   0.7954   0.0439
  -2.250   0.2317   0.01747   0.00818  -0.0993   0.7866   0.0493
  -2.000   0.2591   0.01691   0.00750  -0.0989   0.7800   0.0553
  -1.750   0.2861   0.01647   0.00698  -0.0986   0.7712   0.0657
  -1.500   0.3134   0.01582   0.00651  -0.0983   0.7645   0.1112
  -1.250   0.3394   0.01519   0.00637  -0.0983   0.7559   0.2465
  -1.000   0.3639   0.01428   0.00637  -0.0977   0.7491   0.5044
  -0.750   0.3801   0.01343   0.00638  -0.0943   0.7410   0.7919
  -0.500   0.4163   0.01317   0.00603  -0.0952   0.7338   1.0000
  -0.250   0.4438   0.01329   0.00592  -0.0950   0.7253   1.0000
   0.000   0.4713   0.01340   0.00582  -0.0948   0.7174   1.0000
   0.250   0.4988   0.01352   0.00574  -0.0945   0.7094   1.0000
   0.500   0.5260   0.01365   0.00572  -0.0943   0.7008   1.0000
   0.750   0.5535   0.01376   0.00565  -0.0940   0.6931   1.0000
   1.000   0.5804   0.01391   0.00569  -0.0938   0.6836   1.0000
   1.250   0.6077   0.01403   0.00567  -0.0934   0.6755   1.0000
   1.500   0.6346   0.01417   0.00572  -0.0931   0.6659   1.0000
   1.750   0.6615   0.01432   0.00579  -0.0928   0.6564   1.0000
   2.000   0.6887   0.01443   0.00578  -0.0925   0.6479   1.0000
   2.250   0.7152   0.01459   0.00590  -0.0922   0.6373   1.0000
   2.500   0.7419   0.01475   0.00601  -0.0918   0.6272   1.0000
   2.750   0.7688   0.01488   0.00608  -0.0915   0.6177   1.0000
   3.000   0.7952   0.01505   0.00621  -0.0911   0.6068   1.0000
   3.250   0.8215   0.01522   0.00637  -0.0907   0.5955   1.0000
   3.500   0.8478   0.01539   0.00651  -0.0903   0.5842   1.0000
   3.750   0.8740   0.01556   0.00666  -0.0899   0.5727   1.0000
   4.000   0.9001   0.01573   0.00680  -0.0895   0.5606   1.0000
   4.250   0.9259   0.01593   0.00699  -0.0890   0.5473   1.0000
   4.500   0.9514   0.01613   0.00720  -0.0885   0.5334   1.0000
   4.750   0.9767   0.01635   0.00744  -0.0880   0.5190   1.0000
   5.000   1.0019   0.01659   0.00768  -0.0875   0.5040   1.0000
   5.250   1.0267   0.01685   0.00793  -0.0869   0.4883   1.0000
   5.500   1.0511   0.01714   0.00823  -0.0863   0.4715   1.0000
   5.750   1.0753   0.01746   0.00859  -0.0857   0.4542   1.0000
   6.000   1.0990   0.01782   0.00894  -0.0850   0.4363   1.0000
   6.250   1.1222   0.01821   0.00931  -0.0843   0.4182   1.0000
   6.500   1.1450   0.01864   0.00973  -0.0835   0.3995   1.0000
   6.750   1.1672   0.01912   0.01024  -0.0827   0.3804   1.0000
   7.000   1.1888   0.01965   0.01075  -0.0818   0.3614   1.0000
   7.250   1.2099   0.02022   0.01130  -0.0809   0.3432   1.0000
   7.500   1.2305   0.02082   0.01192  -0.0799   0.3244   1.0000
   7.750   1.2503   0.02148   0.01261  -0.0789   0.3068   1.0000
   8.000   1.2693   0.02218   0.01331  -0.0778   0.2896   1.0000
   8.250   1.2877   0.02292   0.01406  -0.0767   0.2736   1.0000
   8.500   1.3052   0.02371   0.01486  -0.0754   0.2581   1.0000
   8.750   1.3222   0.02452   0.01572  -0.0742   0.2431   1.0000
   9.000   1.3381   0.02538   0.01665  -0.0728   0.2292   1.0000
   9.500   1.3669   0.02723   0.01861  -0.0697   0.2033   1.0000
   9.750   1.3796   0.02821   0.01968  -0.0681   0.1913   1.0000
  10.000   1.3898   0.02924   0.02079  -0.0661   0.1805   1.0000
  10.500   1.4054   0.03164   0.02333  -0.0620   0.1616   1.0000
  10.750   1.4136   0.03292   0.02475  -0.0602   0.1522   1.0000
  11.000   1.4194   0.03441   0.02630  -0.0584   0.1441   1.0000
  11.250   1.4251   0.03598   0.02798  -0.0568   0.1361   1.0000
  11.500   1.4307   0.03765   0.02977  -0.0554   0.1285   1.0000
  11.750   1.4335   0.03956   0.03175  -0.0541   0.1216   1.0000
  12.000   1.4382   0.04147   0.03383  -0.0530   0.1141   1.0000
  12.250   1.4378   0.04381   0.03619  -0.0520   0.1076   1.0000
  12.500   1.4396   0.04612   0.03873  -0.0513   0.0987   1.0000
  12.750   1.4382   0.04882   0.04153  -0.0509   0.0902   1.0000
  13.000   1.4335   0.05199   0.04472  -0.0508   0.0824   1.0000
  13.250   1.4305   0.05520   0.04806  -0.0509   0.0729   1.0000
  13.500   1.4268   0.05863   0.05161  -0.0512   0.0646   1.0000
  13.750   1.4194   0.06266   0.05570  -0.0518   0.0592   1.0000
  14.000   1.4149   0.06648   0.05972  -0.0524   0.0534   1.0000
  14.250   1.4044   0.07131   0.06464  -0.0536   0.0494   1.0000
  14.500   1.3969   0.07595   0.06948  -0.0548   0.0441   1.0000
  14.750   1.3842   0.08162   0.07525  -0.0568   0.0405   1.0000
  15.000   1.3721   0.08747   0.08126  -0.0589   0.0367   1.0000
  15.250   1.3583   0.09384   0.08777  -0.0615   0.0337   1.0000
  15.500   1.3424   0.10086   0.09490  -0.0647   0.0319   1.0000
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