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S4053 (s4053-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S4053 (s4053-il)
Reynolds number: 200,000
Max Cl/Cd: 80.62 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4053-il-200000.txt
Download as CSV file: xf-s4053-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4053                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3836   0.08840   0.08495  -0.0343   1.0000   0.0419
  -8.000  -0.3912   0.08547   0.08210  -0.0363   1.0000   0.0428
  -7.750  -0.4057   0.08271   0.07945  -0.0386   1.0000   0.0433
  -7.500  -0.4119   0.07883   0.07560  -0.0429   1.0000   0.0436
  -7.250  -0.4170   0.07527   0.07201  -0.0450   1.0000   0.0438
  -7.000  -0.4231   0.07225   0.06893  -0.0449   1.0000   0.0439
  -6.750  -0.4335   0.06702   0.06384  -0.0425   1.0000   0.0449
  -6.500  -0.4368   0.06535   0.06226  -0.0387   1.0000   0.0458
  -6.250  -0.4425   0.06346   0.06038  -0.0362   1.0000   0.0463
  -6.000  -0.4161   0.05997   0.05684  -0.0401   0.9957   0.0495
  -5.750  -0.3753   0.05141   0.04757  -0.0537   0.9869   0.0571
  -5.500  -0.3487   0.04841   0.04482  -0.0554   0.9840   0.0605
  -5.250  -0.3129   0.04401   0.03963  -0.0616   0.9746   0.0702
  -5.000  -0.2828   0.03976   0.03557  -0.0644   0.9715   0.0732
  -4.750  -0.2519   0.03687   0.03212  -0.0671   0.9625   0.0846
  -4.500  -0.2183   0.03360   0.02895  -0.0699   0.9589   0.0890
  -4.250  -0.1882   0.03097   0.02601  -0.0716   0.9511   0.1011
  -4.000  -0.1450   0.02233   0.01583  -0.0708   0.9470   0.0406
  -3.750  -0.1047   0.01991   0.01298  -0.0729   0.9443   0.0397
  -3.500  -0.0724   0.01834   0.01112  -0.0734   0.9369   0.0400
  -3.250  -0.0340   0.01666   0.00923  -0.0750   0.9329   0.0392
  -3.000   0.0046   0.01534   0.00781  -0.0767   0.9293   0.0399
  -2.750   0.0343   0.01445   0.00687  -0.0768   0.9207   0.0415
  -2.500   0.0706   0.01351   0.00586  -0.0783   0.9161   0.0454
  -2.250   0.0988   0.01296   0.00530  -0.0782   0.9066   0.0554
  -2.000   0.1261   0.01120   0.00456  -0.0784   0.8998   0.2965
  -1.750   0.1441   0.00996   0.00452  -0.0765   0.8902   0.6175
  -1.500   0.2278   0.00910   0.00446  -0.0859   0.8919   0.9850
  -1.250   0.2794   0.00895   0.00409  -0.0909   0.8864   1.0000
  -1.000   0.3034   0.00895   0.00393  -0.0901   0.8749   1.0000
  -0.750   0.3270   0.00899   0.00383  -0.0892   0.8638   1.0000
  -0.500   0.3515   0.00904   0.00374  -0.0884   0.8538   1.0000
  -0.250   0.3769   0.00908   0.00364  -0.0877   0.8445   1.0000
   0.000   0.4000   0.00917   0.00364  -0.0867   0.8337   1.0000
   0.250   0.4241   0.00927   0.00364  -0.0858   0.8240   1.0000
   0.500   0.4497   0.00934   0.00360  -0.0851   0.8153   1.0000
   0.750   0.4729   0.00945   0.00365  -0.0841   0.8045   1.0000
   1.000   0.4971   0.00956   0.00369  -0.0832   0.7945   1.0000
   1.250   0.5223   0.00965   0.00369  -0.0824   0.7852   1.0000
   1.500   0.5463   0.00975   0.00375  -0.0815   0.7746   1.0000
   1.750   0.5704   0.00987   0.00384  -0.0806   0.7641   1.0000
   2.000   0.5954   0.00997   0.00389  -0.0798   0.7542   1.0000
   2.250   0.6206   0.01007   0.00393  -0.0791   0.7440   1.0000
   2.500   0.6446   0.01018   0.00403  -0.0781   0.7322   1.0000
   2.750   0.6689   0.01028   0.00413  -0.0772   0.7204   1.0000
   3.000   0.6936   0.01038   0.00421  -0.0764   0.7085   1.0000
   3.250   0.7184   0.01047   0.00428  -0.0755   0.6963   1.0000
   3.500   0.7431   0.01056   0.00436  -0.0747   0.6835   1.0000
   3.750   0.7674   0.01065   0.00446  -0.0737   0.6693   1.0000
   4.000   0.7913   0.01073   0.00455  -0.0727   0.6533   1.0000
   4.250   0.8150   0.01081   0.00464  -0.0717   0.6358   1.0000
   4.500   0.8387   0.01089   0.00472  -0.0706   0.6174   1.0000
   4.750   0.8621   0.01100   0.00485  -0.0695   0.5971   1.0000
   5.000   0.8850   0.01113   0.00497  -0.0683   0.5733   1.0000
   5.250   0.9072   0.01129   0.00511  -0.0670   0.5458   1.0000
   5.500   0.9287   0.01152   0.00527  -0.0656   0.5131   1.0000
   5.750   0.9488   0.01184   0.00551  -0.0641   0.4728   1.0000
   6.000   0.9676   0.01230   0.00580  -0.0623   0.4259   1.0000
   6.250   0.9848   0.01291   0.00620  -0.0604   0.3738   1.0000
   6.500   1.0012   0.01363   0.00669  -0.0585   0.3205   1.0000
   6.750   1.0165   0.01448   0.00731  -0.0565   0.2669   1.0000
   7.000   1.0307   0.01545   0.00800  -0.0545   0.2139   1.0000
   7.250   1.0447   0.01648   0.00878  -0.0525   0.1680   1.0000
   7.500   1.0581   0.01759   0.00968  -0.0503   0.1352   1.0000
   7.750   1.0726   0.01863   0.01062  -0.0483   0.1125   1.0000
   8.000   1.0867   0.01968   0.01159  -0.0463   0.0972   1.0000
   8.250   1.1013   0.02070   0.01264  -0.0443   0.0862   1.0000
   8.500   1.1151   0.02179   0.01374  -0.0423   0.0773   1.0000
   8.750   1.1276   0.02302   0.01491  -0.0402   0.0690   1.0000
   9.000   1.1442   0.02373   0.01577  -0.0386   0.0619   1.0000
   9.250   1.1548   0.02512   0.01713  -0.0363   0.0557   1.0000
   9.500   1.1682   0.02597   0.01812  -0.0342   0.0497   1.0000
   9.750   1.1786   0.02769   0.01987  -0.0321   0.0442   1.0000
  10.000   1.1902   0.02866   0.02099  -0.0299   0.0392   1.0000
  10.250   1.2023   0.03102   0.02333  -0.0283   0.0348   1.0000
  10.500   1.2153   0.03243   0.02497  -0.0264   0.0321   1.0000
  10.750   1.2257   0.03384   0.02652  -0.0244   0.0295   1.0000
  11.000   1.2359   0.03581   0.02851  -0.0229   0.0271   1.0000
  11.250   1.2460   0.03865   0.03162  -0.0212   0.0255   1.0000
  11.500   1.2522   0.04084   0.03411  -0.0191   0.0244   1.0000
  11.750   1.2559   0.04342   0.03698  -0.0170   0.0236   1.0000
  12.000   1.2558   0.04619   0.04003  -0.0149   0.0229   1.0000
  12.250   1.2523   0.04920   0.04334  -0.0129   0.0224   1.0000
  12.500   1.2455   0.05248   0.04689  -0.0112   0.0221   1.0000
  12.750   1.2348   0.05623   0.05092  -0.0099   0.0220   1.0000
  13.000   1.2246   0.05982   0.05473  -0.0092   0.0216   1.0000
  13.250   1.2084   0.06440   0.05957  -0.0090   0.0215   1.0000
  13.500   1.2002   0.06788   0.06318  -0.0094   0.0210   1.0000
  13.750   1.1806   0.07342   0.06896  -0.0107   0.0210   1.0000
  14.000   1.1392   0.08293   0.07889  -0.0145   0.0221   1.0000
  14.250   1.1098   0.09138   0.08758  -0.0190   0.0225   1.0000
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