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S4320 (s4320-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4320 (s4320-il)
Reynolds number: 200,000
Max Cl/Cd: 84.42 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4320-il-200000.txt
Download as CSV file: xf-s4320-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2673   0.09109   0.08790  -0.0344   1.0000   0.0374
  -7.750  -0.2684   0.08880   0.08569  -0.0348   1.0000   0.0386
  -7.500  -0.2822   0.08779   0.08482  -0.0325   1.0000   0.0393
  -7.250  -0.2792   0.08516   0.08225  -0.0397   0.9889   0.0407
  -7.000  -0.2373   0.07805   0.07508  -0.0615   0.9758   0.0414
  -6.750  -0.2253   0.07303   0.07010  -0.0582   0.9728   0.0429
  -6.500  -0.1996   0.06967   0.06673  -0.0607   0.9662   0.0451
  -6.250  -0.1675   0.06479   0.06181  -0.0700   0.9573   0.0487
  -5.000  -0.0502   0.04218   0.03848  -0.0986   0.8946   0.0691
  -4.750  -0.0305   0.04001   0.03621  -0.0987   0.8847   0.0730
  -4.500  -0.0053   0.03588   0.03164  -0.1019   0.8738   0.0822
  -4.250   0.0160   0.03394   0.02967  -0.1016   0.8650   0.0861
  -4.000   0.0415   0.03115   0.02650  -0.1029   0.8562   0.0970
  -3.750   0.0796   0.02400   0.01790  -0.1035   0.8484   0.0533
  -3.500   0.1054   0.02079   0.01441  -0.1033   0.8409   0.0492
  -3.250   0.1334   0.01859   0.01175  -0.1030   0.8325   0.0464
  -3.000   0.1610   0.01714   0.00996  -0.1023   0.8255   0.0459
  -2.750   0.1884   0.01621   0.00886  -0.1019   0.8168   0.0472
  -2.500   0.2156   0.01554   0.00802  -0.1013   0.8101   0.0501
  -2.250   0.2429   0.01481   0.00721  -0.1008   0.8013   0.0514
  -2.000   0.2700   0.01413   0.00643  -0.1002   0.7949   0.0533
  -1.750   0.2971   0.01344   0.00577  -0.1000   0.7860   0.0584
  -1.500   0.3248   0.01301   0.00526  -0.0997   0.7794   0.0696
  -1.250   0.3517   0.01189   0.00490  -0.0998   0.7708   0.2559
  -1.000   0.3772   0.01120   0.00486  -0.0995   0.7640   0.4680
  -0.750   0.3955   0.01038   0.00495  -0.0971   0.7557   0.7495
  -0.500   0.4278   0.00995   0.00469  -0.0969   0.7487   1.0000
  -0.250   0.4556   0.01004   0.00460  -0.0967   0.7401   1.0000
   0.000   0.4833   0.01014   0.00453  -0.0965   0.7323   1.0000
   0.250   0.5110   0.01022   0.00445  -0.0963   0.7241   1.0000
   0.500   0.5385   0.01032   0.00444  -0.0961   0.7154   1.0000
   0.750   0.5663   0.01041   0.00437  -0.0958   0.7078   1.0000
   1.000   0.5937   0.01051   0.00440  -0.0956   0.6983   1.0000
   1.250   0.6213   0.01061   0.00437  -0.0953   0.6904   1.0000
   1.500   0.6487   0.01071   0.00439  -0.0951   0.6810   1.0000
   1.750   0.6761   0.01082   0.00443  -0.0949   0.6721   1.0000
   2.000   0.7037   0.01092   0.00442  -0.0946   0.6637   1.0000
   2.250   0.7309   0.01103   0.00450  -0.0944   0.6535   1.0000
   2.500   0.7582   0.01114   0.00454  -0.0941   0.6443   1.0000
   2.750   0.7855   0.01123   0.00457  -0.0938   0.6348   1.0000
   3.000   0.8125   0.01134   0.00466  -0.0935   0.6237   1.0000
   3.250   0.8395   0.01145   0.00474  -0.0933   0.6130   1.0000
   3.500   0.8665   0.01156   0.00480  -0.0929   0.6025   1.0000
   3.750   0.8933   0.01167   0.00487  -0.0926   0.5910   1.0000
   4.000   0.9199   0.01179   0.00499  -0.0923   0.5783   1.0000
   4.250   0.9464   0.01192   0.00511  -0.0919   0.5654   1.0000
   4.500   0.9727   0.01206   0.00525  -0.0916   0.5519   1.0000
   4.750   0.9988   0.01222   0.00539  -0.0912   0.5378   1.0000
   5.000   1.0247   0.01238   0.00554  -0.0907   0.5227   1.0000
   5.250   1.0504   0.01258   0.00571  -0.0903   0.5068   1.0000
   5.500   1.0757   0.01280   0.00591  -0.0898   0.4901   1.0000
   5.750   1.1007   0.01305   0.00614  -0.0893   0.4721   1.0000
   6.000   1.1253   0.01333   0.00641  -0.0887   0.4527   1.0000
   6.250   1.1493   0.01367   0.00669  -0.0881   0.4330   1.0000
   6.500   1.1730   0.01404   0.00705  -0.0875   0.4124   1.0000
   6.750   1.1961   0.01446   0.00742  -0.0868   0.3915   1.0000
   7.000   1.2188   0.01493   0.00784  -0.0860   0.3710   1.0000
   7.250   1.2410   0.01542   0.00830  -0.0853   0.3499   1.0000
   7.500   1.2623   0.01600   0.00882  -0.0844   0.3303   1.0000
   7.750   1.2836   0.01655   0.00938  -0.0836   0.3104   1.0000
   8.000   1.3042   0.01717   0.00997  -0.0826   0.2919   1.0000
   8.250   1.3239   0.01784   0.01060  -0.0816   0.2746   1.0000
   8.500   1.3429   0.01856   0.01127  -0.0805   0.2579   1.0000
   8.750   1.3618   0.01925   0.01200  -0.0794   0.2416   1.0000
   9.000   1.3798   0.01999   0.01276  -0.0782   0.2262   1.0000
   9.250   1.3967   0.02076   0.01354  -0.0768   0.2115   1.0000
   9.500   1.4124   0.02159   0.01438  -0.0753   0.1977   1.0000
   9.750   1.4267   0.02246   0.01526  -0.0737   0.1845   1.0000
  10.000   1.4393   0.02336   0.01619  -0.0719   0.1715   1.0000
  10.250   1.4481   0.02428   0.01711  -0.0696   0.1592   1.0000
  10.500   1.4557   0.02527   0.01811  -0.0672   0.1476   1.0000
  10.750   1.4647   0.02625   0.01917  -0.0652   0.1364   1.0000
  11.000   1.4727   0.02738   0.02038  -0.0633   0.1266   1.0000
  11.250   1.4787   0.02870   0.02172  -0.0614   0.1173   1.0000
  11.500   1.4833   0.03019   0.02322  -0.0597   0.1080   1.0000
  11.750   1.4915   0.03152   0.02464  -0.0584   0.0980   1.0000
  12.000   1.4979   0.03307   0.02630  -0.0572   0.0888   1.0000
  12.250   1.5013   0.03495   0.02823  -0.0559   0.0810   1.0000
  12.500   1.5046   0.03697   0.03029  -0.0549   0.0717   1.0000
  12.750   1.5061   0.03927   0.03262  -0.0541   0.0593   1.0000
  13.000   1.4999   0.04251   0.03582  -0.0532   0.0418   1.0000
  13.250   1.4845   0.04694   0.04019  -0.0525   0.0314   1.0000
  13.500   1.4739   0.05109   0.04442  -0.0522   0.0260   1.0000
  13.750   1.4596   0.05585   0.04925  -0.0524   0.0238   1.0000
  14.000   1.4532   0.05983   0.05341  -0.0528   0.0220   1.0000
  14.250   1.4454   0.06416   0.05788  -0.0534   0.0203   1.0000
  14.500   1.4356   0.06899   0.06283  -0.0545   0.0192   1.0000
  14.750   1.4230   0.07443   0.06838  -0.0560   0.0184   1.0000
  15.000   1.4101   0.08010   0.07417  -0.0577   0.0177   1.0000
  15.250   1.4040   0.08492   0.07917  -0.0592   0.0171   1.0000
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