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S4083 (8%) (s4083-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S4083 (8%) (s4083-il)
Reynolds number: 50,000
Max Cl/Cd: 31.1 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s4083-il-50000.txt
Download as CSV file: xf-s4083-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S4083 (8%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3864   0.09992   0.09350  -0.0135   1.0000   0.1933
  -7.000  -0.3699   0.09510   0.08871  -0.0120   1.0000   0.2017
  -6.750  -0.3875   0.09495   0.08876  -0.0146   1.0000   0.2082
  -6.500  -0.3705   0.09013   0.08396  -0.0114   1.0000   0.2190
  -6.000  -0.3705   0.08496   0.07901  -0.0130   1.0000   0.2388
  -5.750  -0.3691   0.08268   0.07683  -0.0144   1.0000   0.2522
  -5.500  -0.3631   0.07961   0.07384  -0.0137   1.0000   0.2667
  -5.250  -0.3556   0.07632   0.07062  -0.0118   1.0000   0.2820
  -5.000  -0.3469   0.07313   0.06750  -0.0089   1.0000   0.2997
  -4.750  -0.3448   0.07091   0.06538  -0.0094   1.0000   0.3248
  -4.500  -0.3400   0.06856   0.06309  -0.0076   1.0000   0.3530
  -4.000  -0.3287   0.06286   0.05760   0.0018   1.0000   0.4137
  -3.750  -0.3239   0.06040   0.05523   0.0064   1.0000   0.4485
  -3.000  -0.1356   0.03547   0.02765  -0.0539   1.0000   0.1283
  -2.750  -0.1044   0.03219   0.02372  -0.0549   1.0000   0.1187
  -2.500  -0.0765   0.02959   0.02064  -0.0551   1.0000   0.1154
  -2.250  -0.0500   0.02770   0.01830  -0.0549   1.0000   0.1192
  -2.000  -0.0246   0.02600   0.01621  -0.0544   1.0000   0.1251
  -1.750  -0.0003   0.02461   0.01465  -0.0537   1.0000   0.1323
  -1.500   0.0225   0.02357   0.01343  -0.0528   1.0000   0.1516
  -1.250   0.0457   0.02248   0.01245  -0.0522   1.0000   0.1852
  -1.000   0.0730   0.02090   0.01148  -0.0523   1.0000   0.3013
  -0.750   0.0906   0.01808   0.01067  -0.0494   1.0000   1.0000
  -0.500   0.1047   0.01890   0.01102  -0.0491   1.0000   1.0000
  -0.250   0.1448   0.01994   0.01158  -0.0538   0.9878   1.0000
   0.000   0.2164   0.02075   0.01185  -0.0632   0.9613   1.0000
   0.250   0.2817   0.02116   0.01187  -0.0709   0.9347   1.0000
   0.500   0.3404   0.02134   0.01180  -0.0769   0.9086   1.0000
   0.750   0.3976   0.02135   0.01159  -0.0821   0.8843   1.0000
   1.000   0.4586   0.02116   0.01123  -0.0875   0.8635   1.0000
   1.250   0.5037   0.02118   0.01113  -0.0901   0.8398   1.0000
   1.500   0.5475   0.02121   0.01104  -0.0922   0.8179   1.0000
   1.750   0.5860   0.02137   0.01109  -0.0934   0.7962   1.0000
   2.000   0.6202   0.02167   0.01130  -0.0939   0.7756   1.0000
   2.250   0.6505   0.02211   0.01169  -0.0938   0.7552   1.0000
   2.500   0.6822   0.02252   0.01201  -0.0938   0.7371   1.0000
   2.750   0.7085   0.02315   0.01261  -0.0932   0.7187   1.0000
   3.000   0.7337   0.02385   0.01329  -0.0926   0.7010   1.0000
   3.250   0.7594   0.02454   0.01401  -0.0919   0.6844   1.0000
   3.500   0.7847   0.02527   0.01473  -0.0911   0.6685   1.0000
   3.750   0.8096   0.02603   0.01550  -0.0903   0.6531   1.0000
   4.000   0.8339   0.02683   0.01632  -0.0895   0.6379   1.0000
   4.250   0.8578   0.02767   0.01720  -0.0885   0.6231   1.0000
   4.500   0.8813   0.02855   0.01819  -0.0876   0.6083   1.0000
   4.750   0.9043   0.02947   0.01919  -0.0865   0.5937   1.0000
   5.000   0.9269   0.03043   0.02024  -0.0855   0.5792   1.0000
   5.250   0.9493   0.03142   0.02133  -0.0844   0.5647   1.0000
   5.500   0.9715   0.03243   0.02250  -0.0832   0.5500   1.0000
   5.750   0.9924   0.03353   0.02373  -0.0820   0.5350   1.0000
   6.000   1.0114   0.03476   0.02514  -0.0806   0.5194   1.0000
   6.250   1.0302   0.03603   0.02658  -0.0792   0.5035   1.0000
   6.500   1.0489   0.03727   0.02801  -0.0777   0.4872   1.0000
   6.750   1.0685   0.03841   0.02938  -0.0761   0.4706   1.0000
   7.000   1.0898   0.03938   0.03050  -0.0745   0.4538   1.0000
   7.250   1.1157   0.03985   0.03107  -0.0730   0.4365   1.0000
   7.500   1.1316   0.04121   0.03266  -0.0711   0.4183   1.0000
   7.750   1.1483   0.04235   0.03408  -0.0691   0.3988   1.0000
   8.000   1.1796   0.04192   0.03367  -0.0674   0.3782   1.0000
   8.250   1.1892   0.04364   0.03571  -0.0650   0.3578   1.0000
   8.500   1.2172   0.04322   0.03533  -0.0630   0.3343   1.0000
   8.750   1.2435   0.04260   0.03471  -0.0608   0.3077   1.0000
   9.000   1.2625   0.04238   0.03455  -0.0581   0.2791   1.0000
   9.250   1.2763   0.04234   0.03463  -0.0550   0.2477   1.0000
   9.500   1.2920   0.04164   0.03359  -0.0518   0.2100   1.0000
   9.750   1.2945   0.04292   0.03482  -0.0480   0.1766   1.0000
  10.000   1.2994   0.04466   0.03604  -0.0448   0.1438   1.0000
  10.250   1.2951   0.04743   0.03904  -0.0413   0.1238   1.0000
  10.500   1.3014   0.05019   0.04142  -0.0391   0.1048   1.0000
  10.750   1.2973   0.05342   0.04509  -0.0361   0.0958   1.0000
  11.000   1.2972   0.05713   0.04900  -0.0339   0.0889   1.0000
  11.250   1.2926   0.06082   0.05301  -0.0314   0.0848   1.0000
  11.500   1.3048   0.06545   0.05759  -0.0307   0.0799   1.0000
  11.750   1.2874   0.06928   0.06179  -0.0281   0.0794   1.0000
  12.000   1.2684   0.07351   0.06632  -0.0265   0.0793   1.0000
  12.250   1.2478   0.07827   0.07135  -0.0262   0.0793   1.0000
  12.500   1.2267   0.08364   0.07694  -0.0272   0.0795   1.0000
  12.750   1.2068   0.08958   0.08305  -0.0291   0.0799   1.0000
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