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S2060 8% (s2060-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2060 8% (s2060-il)
Reynolds number: 50,000
Max Cl/Cd: 36.89 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2060-il-50000-n5.txt
Download as CSV file: xf-s2060-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2060 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5041   0.09280   0.08569  -0.0270   1.0000   0.0461
  -8.750  -0.5062   0.08840   0.08138  -0.0291   1.0000   0.0460
  -8.500  -0.5105   0.08379   0.07686  -0.0316   1.0000   0.0459
  -8.250  -0.5164   0.07896   0.07212  -0.0346   1.0000   0.0457
  -8.000  -0.5202   0.07371   0.06690  -0.0381   1.0000   0.0455
  -7.750  -0.5240   0.06860   0.06178  -0.0408   1.0000   0.0452
  -7.500  -0.5277   0.06343   0.05652  -0.0431   1.0000   0.0451
  -7.250  -0.5294   0.05832   0.05125  -0.0448   1.0000   0.0450
  -7.000  -0.5280   0.05334   0.04600  -0.0458   1.0000   0.0452
  -6.750  -0.5235   0.04826   0.04050  -0.0465   1.0000   0.0457
  -6.500  -0.5147   0.04339   0.03502  -0.0466   1.0000   0.0466
  -6.250  -0.5007   0.04112   0.03271  -0.0460   1.0000   0.0503
  -6.000  -0.4849   0.03829   0.02948  -0.0455   1.0000   0.0550
  -5.750  -0.4668   0.03439   0.02469  -0.0450   1.0000   0.0590
  -5.500  -0.4485   0.03279   0.02307  -0.0442   1.0000   0.0664
  -5.250  -0.4273   0.03015   0.01986  -0.0434   1.0000   0.0732
  -5.000  -0.4064   0.02862   0.01812  -0.0425   1.0000   0.0827
  -4.750  -0.3846   0.02693   0.01623  -0.0416   1.0000   0.0906
  -4.500  -0.3623   0.02557   0.01462  -0.0406   1.0000   0.1014
  -4.250  -0.3398   0.02437   0.01321  -0.0395   1.0000   0.1118
  -4.000  -0.3178   0.02330   0.01205  -0.0384   1.0000   0.1236
  -3.750  -0.2954   0.02240   0.01104  -0.0375   1.0000   0.1399
  -3.500  -0.2729   0.02149   0.01011  -0.0365   1.0000   0.1566
  -3.250  -0.2505   0.02070   0.00937  -0.0358   1.0000   0.1847
  -3.000  -0.2280   0.01986   0.00866  -0.0352   1.0000   0.2208
  -2.750  -0.2056   0.01901   0.00807  -0.0347   1.0000   0.2840
  -2.500  -0.1843   0.01807   0.00768  -0.0339   1.0000   0.3915
  -2.250  -0.1674   0.01722   0.00761  -0.0315   1.0000   0.5510
  -2.000  -0.1548   0.01676   0.00765  -0.0274   1.0000   0.7077
  -1.750  -0.1380   0.01645   0.00758  -0.0238   1.0000   0.8479
  -1.500  -0.0962   0.01620   0.00712  -0.0265   1.0000   1.0000
  -1.250  -0.0752   0.01628   0.00691  -0.0260   1.0000   1.0000
  -1.000  -0.0539   0.01640   0.00679  -0.0255   1.0000   1.0000
  -0.750  -0.0326   0.01655   0.00670  -0.0251   1.0000   1.0000
  -0.500  -0.0113   0.01674   0.00670  -0.0246   1.0000   1.0000
  -0.250   0.0102   0.01697   0.00677  -0.0242   0.9999   1.0000
   0.000   0.0517   0.01736   0.00700  -0.0277   0.9893   1.0000
   0.250   0.0928   0.01775   0.00724  -0.0309   0.9786   1.0000
   0.500   0.1341   0.01811   0.00751  -0.0342   0.9675   1.0000
   0.750   0.1762   0.01845   0.00778  -0.0374   0.9561   1.0000
   1.000   0.2158   0.01872   0.00802  -0.0401   0.9433   1.0000
   1.250   0.2552   0.01894   0.00825  -0.0427   0.9298   1.0000
   1.500   0.2949   0.01913   0.00847  -0.0451   0.9159   1.0000
   1.750   0.3352   0.01927   0.00868  -0.0475   0.9016   1.0000
   2.000   0.3761   0.01935   0.00884  -0.0498   0.8868   1.0000
   2.250   0.4141   0.01938   0.00897  -0.0514   0.8706   1.0000
   2.500   0.4473   0.01941   0.00913  -0.0520   0.8515   1.0000
   2.750   0.4827   0.01936   0.00921  -0.0527   0.8324   1.0000
   3.000   0.5160   0.01929   0.00928  -0.0529   0.8115   1.0000
   3.250   0.5479   0.01921   0.00938  -0.0528   0.7883   1.0000
   3.500   0.5775   0.01916   0.00946  -0.0522   0.7619   1.0000
   3.750   0.6069   0.01909   0.00953  -0.0514   0.7328   1.0000
   4.000   0.6356   0.01906   0.00959  -0.0504   0.7001   1.0000
   4.250   0.6625   0.01911   0.00976  -0.0491   0.6620   1.0000
   4.500   0.6885   0.01925   0.00992  -0.0476   0.6194   1.0000
   4.750   0.7129   0.01951   0.01015  -0.0460   0.5719   1.0000
   5.000   0.7353   0.01993   0.01050  -0.0442   0.5196   1.0000
   5.250   0.7563   0.02051   0.01101  -0.0424   0.4642   1.0000
   5.500   0.7758   0.02125   0.01159  -0.0406   0.4063   1.0000
   5.750   0.7937   0.02216   0.01229  -0.0388   0.3445   1.0000
   6.000   0.8101   0.02326   0.01314  -0.0370   0.2781   1.0000
   6.250   0.8254   0.02464   0.01417  -0.0355   0.2076   1.0000
   6.500   0.8399   0.02641   0.01540  -0.0342   0.1335   1.0000
   6.750   0.8561   0.02838   0.01714  -0.0330   0.0918   1.0000
   7.000   0.8731   0.03023   0.01888  -0.0317   0.0721   1.0000
   7.250   0.8918   0.03203   0.02080  -0.0303   0.0624   1.0000
   7.500   0.9110   0.03399   0.02283  -0.0290   0.0573   1.0000
   7.750   0.9337   0.03605   0.02519  -0.0279   0.0533   1.0000
   8.000   0.9551   0.03818   0.02750  -0.0270   0.0499   1.0000
   8.250   0.9745   0.04062   0.02998  -0.0262   0.0466   1.0000
   8.500   0.9935   0.04318   0.03313  -0.0251   0.0437   1.0000
   8.750   1.0097   0.04620   0.03659  -0.0238   0.0421   1.0000
   9.000   1.0221   0.04954   0.04038  -0.0224   0.0411   1.0000
   9.250   1.0300   0.05312   0.04440  -0.0209   0.0404   1.0000
   9.500   1.0328   0.05690   0.04861  -0.0193   0.0400   1.0000
   9.750   1.0301   0.06087   0.05297  -0.0176   0.0397   1.0000
  10.000   1.0216   0.06496   0.05741  -0.0161   0.0396   1.0000
  10.250   1.0060   0.06899   0.06172  -0.0144   0.0397   1.0000
  10.500   0.9864   0.07346   0.06642  -0.0138   0.0399   1.0000
  10.750   0.9636   0.07880   0.07195  -0.0151   0.0402   1.0000
  11.000   0.9386   0.08545   0.07876  -0.0187   0.0407   1.0000
  11.250   0.9132   0.09378   0.08718  -0.0245   0.0414   1.0000
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