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S4022 (s4022-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S4022 (s4022-il)
Reynolds number: 50,000
Max Cl/Cd: 39.11 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s4022-il-50000-n5.txt
Download as CSV file: xf-s4022-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4022                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3560   0.11339   0.10693  -0.0354   1.0000   0.1248
  -8.250  -0.3816   0.11286   0.10659  -0.0353   1.0000   0.1276
  -8.000  -0.4003   0.11158   0.10545  -0.0344   1.0000   0.1280
  -7.500  -0.3970   0.10017   0.09404  -0.0341   1.0000   0.0693
  -7.000  -0.4416   0.09237   0.08647  -0.0387   1.0000   0.0585
  -6.750  -0.4407   0.09005   0.08421  -0.0357   1.0000   0.0576
  -6.500  -0.4426   0.08725   0.08147  -0.0346   1.0000   0.0564
  -6.250  -0.4338   0.08243   0.07664  -0.0391   0.9966   0.0546
  -6.000  -0.4156   0.07553   0.06966  -0.0481   0.9900   0.0523
  -5.750  -0.3932   0.06747   0.06134  -0.0591   0.9835   0.0498
  -5.500  -0.3643   0.05793   0.05108  -0.0716   0.9768   0.0467
  -5.250  -0.3267   0.05230   0.04465  -0.0793   0.9724   0.0455
  -5.000  -0.2967   0.04811   0.04000  -0.0833   0.9674   0.0454
  -4.750  -0.2604   0.04425   0.03555  -0.0877   0.9634   0.0454
  -4.500  -0.2215   0.04105   0.03172  -0.0917   0.9601   0.0456
  -4.250  -0.1909   0.03842   0.02880  -0.0939   0.9552   0.0473
  -4.000  -0.1565   0.03677   0.02690  -0.0964   0.9507   0.0516
  -3.750  -0.1188   0.03507   0.02477  -0.0987   0.9471   0.0547
  -3.500  -0.0897   0.03365   0.02302  -0.0990   0.9412   0.0564
  -3.250  -0.0563   0.03253   0.02157  -0.0998   0.9366   0.0584
  -3.000  -0.0254   0.03145   0.02045  -0.1006   0.9318   0.0618
  -2.750   0.0045   0.03066   0.01948  -0.1013   0.9257   0.0670
  -2.500   0.0433   0.02981   0.01850  -0.1038   0.9215   0.0786
  -2.250   0.0781   0.02878   0.01765  -0.1062   0.9156   0.1189
  -2.000   0.1131   0.02694   0.01797  -0.1087   0.9116   0.5381
  -1.750   0.1310   0.02735   0.01860  -0.1049   0.9050   0.6758
  -1.500   0.1478   0.02752   0.01869  -0.1018   0.8969   0.7235
  -1.250   0.1699   0.02759   0.01861  -0.1000   0.8901   0.7620
  -1.000   0.1901   0.02758   0.01847  -0.0980   0.8824   0.7934
  -0.750   0.2108   0.02753   0.01830  -0.0963   0.8750   0.8229
  -0.500   0.2338   0.02741   0.01803  -0.0951   0.8678   0.8523
  -0.250   0.2544   0.02732   0.01784  -0.0937   0.8597   0.8827
   0.000   0.2854   0.02712   0.01753  -0.0944   0.8532   0.9210
   0.250   0.3187   0.02706   0.01733  -0.0963   0.8439   1.0000
   0.500   0.3625   0.02721   0.01725  -0.1001   0.8386   1.0000
   0.750   0.3941   0.02757   0.01743  -0.1019   0.8297   1.0000
   1.000   0.4364   0.02769   0.01736  -0.1051   0.8244   1.0000
   1.250   0.4653   0.02809   0.01763  -0.1063   0.8149   1.0000
   1.500   0.5070   0.02814   0.01755  -0.1090   0.8098   1.0000
   1.750   0.5335   0.02858   0.01791  -0.1096   0.7996   1.0000
   2.000   0.5720   0.02864   0.01789  -0.1117   0.7940   1.0000
   2.250   0.5999   0.02900   0.01820  -0.1122   0.7843   1.0000
   2.500   0.6289   0.02933   0.01851  -0.1128   0.7753   1.0000
   2.750   0.6657   0.02934   0.01849  -0.1144   0.7688   1.0000
   3.000   0.6909   0.02977   0.01891  -0.1144   0.7584   1.0000
   3.250   0.7320   0.02956   0.01875  -0.1163   0.7532   1.0000
   3.500   0.7550   0.03004   0.01926  -0.1159   0.7418   1.0000
   3.750   0.7813   0.03039   0.01964  -0.1158   0.7315   1.0000
   4.000   0.8216   0.03013   0.01945  -0.1175   0.7254   1.0000
   4.250   0.8447   0.03055   0.01998  -0.1169   0.7136   1.0000
   4.500   0.8706   0.03085   0.02037  -0.1167   0.7026   1.0000
   4.750   0.9056   0.03073   0.02034  -0.1174   0.6939   1.0000
   5.000   0.9377   0.03069   0.02042  -0.1178   0.6837   1.0000
   5.250   0.9626   0.03094   0.02085  -0.1172   0.6713   1.0000
   5.500   0.9893   0.03109   0.02113  -0.1168   0.6588   1.0000
   5.750   1.0173   0.03114   0.02132  -0.1164   0.6460   1.0000
   6.000   1.0461   0.03112   0.02145  -0.1161   0.6327   1.0000
   6.250   1.0745   0.03107   0.02156  -0.1156   0.6184   1.0000
   6.500   1.1029   0.03098   0.02170  -0.1151   0.6028   1.0000
   6.750   1.1325   0.03078   0.02166  -0.1146   0.5859   1.0000
   7.000   1.1585   0.03073   0.02175  -0.1135   0.5670   1.0000
   7.250   1.1776   0.03097   0.02213  -0.1117   0.5459   1.0000
   7.500   1.1997   0.03105   0.02232  -0.1100   0.5231   1.0000
   7.750   1.2202   0.03120   0.02261  -0.1082   0.4978   1.0000
   8.000   1.2340   0.03169   0.02318  -0.1056   0.4705   1.0000
   8.250   1.2471   0.03226   0.02379  -0.1030   0.4412   1.0000
   8.500   1.2564   0.03310   0.02466  -0.1001   0.4105   1.0000
   8.750   1.2636   0.03412   0.02569  -0.0972   0.3784   1.0000
   9.000   1.2692   0.03534   0.02686  -0.0942   0.3453   1.0000
   9.250   1.2732   0.03680   0.02823  -0.0913   0.3128   1.0000
   9.500   1.2750   0.03855   0.02992  -0.0886   0.2804   1.0000
   9.750   1.2761   0.04052   0.03186  -0.0860   0.2507   1.0000
  10.000   1.2766   0.04270   0.03395  -0.0836   0.2238   1.0000
  10.250   1.2767   0.04507   0.03622  -0.0815   0.2009   1.0000
  10.500   1.2782   0.04750   0.03866  -0.0797   0.1801   1.0000
  10.750   1.2785   0.05011   0.04122  -0.0780   0.1624   1.0000
  11.000   1.2794   0.05278   0.04385  -0.0765   0.1469   1.0000
  11.250   1.2822   0.05545   0.04655  -0.0751   0.1331   1.0000
  11.500   1.2836   0.05827   0.04941  -0.0740   0.1201   1.0000
  11.750   1.2845   0.06122   0.05246  -0.0729   0.1080   1.0000
  12.000   1.2856   0.06429   0.05566  -0.0720   0.0966   1.0000
  12.250   1.2833   0.06772   0.05922  -0.0715   0.0858   1.0000
  12.500   1.2801   0.07135   0.06295  -0.0712   0.0765   1.0000
  12.750   1.2750   0.07517   0.06672  -0.0712   0.0690   1.0000
  13.000   1.2732   0.07905   0.07090  -0.0712   0.0611   1.0000
  13.250   1.2707   0.08298   0.07496  -0.0713   0.0555   1.0000
  13.500   1.2705   0.08697   0.07924  -0.0714   0.0502   1.0000
  13.750   1.2682   0.09093   0.08321  -0.0719   0.0466   1.0000
  14.000   1.2663   0.09546   0.08805  -0.0724   0.0432   1.0000
  14.250   1.2619   0.10036   0.09327  -0.0736   0.0406   1.0000
  14.500   1.2568   0.10532   0.09845  -0.0751   0.0386   1.0000
  14.750   1.2525   0.11018   0.10346  -0.0767   0.0371   1.0000
  15.000   1.2494   0.11496   0.10836  -0.0783   0.0359   1.0000
  15.250   1.2428   0.12070   0.11426  -0.0806   0.0352   1.0000
  15.500   1.2302   0.12795   0.12180  -0.0845   0.0349   1.0000
  15.750   1.2161   0.13588   0.12999  -0.0891   0.0348   1.0000
  16.000   1.2006   0.14458   0.13891  -0.0946   0.0348   1.0000
  16.250   1.1848   0.15402   0.14852  -0.1008   0.0350   1.0000
  16.500   1.1690   0.16416   0.15879  -0.1075   0.0352   1.0000
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