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S6062 8% (s6062-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S6062 8% (s6062-il)
Reynolds number: 50,000
Max Cl/Cd: 35.56 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6062-il-50000-n5.txt
Download as CSV file: xf-s6062-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6062 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5306   0.10333   0.09642  -0.0123   1.0000   0.0464
  -9.000  -0.5207   0.09970   0.09280  -0.0114   1.0000   0.0447
  -8.750  -0.5175   0.09567   0.08881  -0.0129   1.0000   0.0436
  -8.500  -0.5162   0.09143   0.08464  -0.0149   1.0000   0.0424
  -8.250  -0.5166   0.08703   0.08031  -0.0175   1.0000   0.0414
  -8.000  -0.5184   0.08251   0.07587  -0.0206   1.0000   0.0404
  -7.750  -0.5206   0.07736   0.07079  -0.0248   1.0000   0.0394
  -7.500  -0.5213   0.07194   0.06535  -0.0288   1.0000   0.0383
  -7.250  -0.5213   0.06639   0.05972  -0.0322   1.0000   0.0371
  -7.000  -0.5202   0.06064   0.05377  -0.0351   1.0000   0.0359
  -6.750  -0.5163   0.05508   0.04781  -0.0372   1.0000   0.0348
  -6.500  -0.5061   0.05088   0.04322  -0.0377   1.0000   0.0342
  -6.250  -0.4936   0.04708   0.03902  -0.0377   1.0000   0.0339
  -6.000  -0.4794   0.04345   0.03498  -0.0373   1.0000   0.0338
  -5.750  -0.4638   0.03999   0.03109  -0.0368   1.0000   0.0339
  -5.500  -0.4469   0.03667   0.02737  -0.0360   1.0000   0.0342
  -5.250  -0.4286   0.03381   0.02416  -0.0351   1.0000   0.0350
  -5.000  -0.4096   0.03162   0.02167  -0.0342   1.0000   0.0373
  -4.750  -0.3891   0.02971   0.01946  -0.0331   1.0000   0.0407
  -4.500  -0.3672   0.02776   0.01713  -0.0318   1.0000   0.0438
  -4.250  -0.3449   0.02598   0.01500  -0.0303   1.0000   0.0461
  -4.000  -0.3243   0.02435   0.01331  -0.0288   1.0000   0.0496
  -3.750  -0.3033   0.02305   0.01184  -0.0274   1.0000   0.0558
  -3.500  -0.2821   0.02183   0.01057  -0.0262   1.0000   0.0729
  -3.250  -0.2612   0.02031   0.00933  -0.0254   1.0000   0.1264
  -3.000  -0.2430   0.01839   0.00841  -0.0246   1.0000   0.2842
  -2.750  -0.2289   0.01698   0.00804  -0.0223   1.0000   0.4939
  -2.500  -0.2183   0.01619   0.00804  -0.0174   1.0000   0.6962
  -2.250  -0.1888   0.01592   0.00791  -0.0153   1.0000   0.8796
  -2.000  -0.1131   0.01576   0.00713  -0.0242   1.0000   1.0000
  -1.750  -0.1030   0.01576   0.00685  -0.0219   1.0000   1.0000
  -1.500  -0.0899   0.01581   0.00663  -0.0200   1.0000   1.0000
  -1.250  -0.0748   0.01590   0.00648  -0.0186   1.0000   1.0000
  -1.000  -0.0583   0.01603   0.00635  -0.0173   1.0000   1.0000
  -0.750  -0.0258   0.01626   0.00634  -0.0192   0.9927   1.0000
  -0.500   0.0158   0.01655   0.00639  -0.0226   0.9812   1.0000
  -0.250   0.0579   0.01683   0.00649  -0.0261   0.9699   1.0000
   0.000   0.0993   0.01708   0.00658  -0.0293   0.9580   1.0000
   0.250   0.1395   0.01731   0.00670  -0.0322   0.9455   1.0000
   0.500   0.1796   0.01753   0.00685  -0.0350   0.9330   1.0000
   0.750   0.2196   0.01773   0.00702  -0.0376   0.9202   1.0000
   1.000   0.2574   0.01791   0.00718  -0.0397   0.9066   1.0000
   1.250   0.2935   0.01808   0.00736  -0.0413   0.8924   1.0000
   1.500   0.3280   0.01822   0.00756  -0.0425   0.8775   1.0000
   1.750   0.3612   0.01835   0.00773  -0.0433   0.8621   1.0000
   2.000   0.3931   0.01846   0.00789  -0.0438   0.8462   1.0000
   2.250   0.4217   0.01859   0.00809  -0.0435   0.8286   1.0000
   2.500   0.4491   0.01871   0.00833  -0.0430   0.8099   1.0000
   2.750   0.4771   0.01878   0.00849  -0.0424   0.7914   1.0000
   3.000   0.5032   0.01887   0.00868  -0.0414   0.7711   1.0000
   3.250   0.5291   0.01894   0.00885  -0.0403   0.7499   1.0000
   3.500   0.5539   0.01903   0.00911  -0.0390   0.7268   1.0000
   3.750   0.5791   0.01909   0.00927  -0.0376   0.7029   1.0000
   4.000   0.6038   0.01917   0.00946  -0.0361   0.6767   1.0000
   4.250   0.6276   0.01930   0.00970  -0.0346   0.6473   1.0000
   4.500   0.6509   0.01946   0.01003  -0.0330   0.6145   1.0000
   4.750   0.6743   0.01963   0.01027  -0.0312   0.5791   1.0000
   5.000   0.6966   0.01991   0.01060  -0.0295   0.5381   1.0000
   5.250   0.7181   0.02027   0.01101  -0.0277   0.4914   1.0000
   5.500   0.7386   0.02077   0.01147  -0.0259   0.4389   1.0000
   5.750   0.7570   0.02147   0.01212  -0.0240   0.3740   1.0000
   6.000   0.7711   0.02261   0.01279  -0.0220   0.2804   1.0000
   6.250   0.7824   0.02448   0.01384  -0.0205   0.1656   1.0000
   6.500   0.7959   0.02672   0.01550  -0.0193   0.0934   1.0000
   6.750   0.8114   0.02878   0.01739  -0.0181   0.0662   1.0000
   7.000   0.8280   0.03066   0.01931  -0.0167   0.0569   1.0000
   7.250   0.8464   0.03244   0.02130  -0.0153   0.0515   1.0000
   7.500   0.8647   0.03438   0.02332  -0.0141   0.0480   1.0000
   7.750   0.8868   0.03657   0.02581  -0.0129   0.0457   1.0000
   8.000   0.9099   0.03898   0.02859  -0.0119   0.0437   1.0000
   8.250   0.9302   0.04154   0.03151  -0.0109   0.0412   1.0000
   8.500   0.9467   0.04403   0.03430  -0.0100   0.0385   1.0000
   8.750   0.9608   0.04681   0.03730  -0.0091   0.0366   1.0000
   9.000   0.9724   0.05051   0.04129  -0.0082   0.0356   1.0000
   9.250   0.9795   0.05423   0.04541  -0.0070   0.0353   1.0000
   9.500   0.9819   0.05804   0.04967  -0.0058   0.0352   1.0000
   9.750   0.9793   0.06199   0.05401  -0.0046   0.0351   1.0000
  10.000   0.9720   0.06599   0.05833  -0.0037   0.0351   1.0000
  10.250   0.9592   0.06985   0.06243  -0.0027   0.0351   1.0000
  10.500   0.9438   0.07404   0.06682  -0.0027   0.0352   1.0000
  10.750   0.9277   0.07876   0.07170  -0.0040   0.0353   1.0000
  11.000   0.9109   0.08419   0.07726  -0.0066   0.0355   1.0000
  11.250   0.8915   0.09064   0.08389  -0.0111   0.0358   1.0000
  11.500   0.8626   0.10098   0.09436  -0.0195   0.0368   1.0000
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