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S2062 8% (s2062-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S2062 8% (s2062-il)
Reynolds number: 100,000
Max Cl/Cd: 49.87 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2062-il-100000-n5.txt
Download as CSV file: xf-s2062-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2062 8%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5046   0.08774   0.08269  -0.0245   1.0000   0.0200
  -8.750  -0.5092   0.08276   0.07779  -0.0271   1.0000   0.0196
  -8.500  -0.5162   0.07750   0.07262  -0.0299   1.0000   0.0193
  -8.250  -0.5272   0.07180   0.06706  -0.0336   1.0000   0.0189
  -8.000  -0.5511   0.05889   0.05407  -0.0434   1.0000   0.0176
  -7.500  -0.5626   0.04754   0.04213  -0.0465   1.0000   0.0171
  -7.250  -0.5608   0.04311   0.03734  -0.0463   1.0000   0.0170
  -7.000  -0.5550   0.03886   0.03264  -0.0457   1.0000   0.0171
  -6.750  -0.5450   0.03514   0.02841  -0.0448   1.0000   0.0171
  -6.500  -0.5322   0.03185   0.02473  -0.0438   1.0000   0.0174
  -6.250  -0.5164   0.02961   0.02218  -0.0428   1.0000   0.0182
  -6.000  -0.4984   0.02798   0.02030  -0.0419   1.0000   0.0196
  -5.750  -0.4791   0.02622   0.01820  -0.0408   1.0000   0.0216
  -5.500  -0.4588   0.02423   0.01584  -0.0395   1.0000   0.0227
  -5.250  -0.4379   0.02253   0.01383  -0.0383   1.0000   0.0237
  -5.000  -0.4176   0.02082   0.01200  -0.0372   1.0000   0.0256
  -4.750  -0.3964   0.01970   0.01077  -0.0362   1.0000   0.0282
  -4.500  -0.3744   0.01865   0.00954  -0.0351   1.0000   0.0339
  -4.250  -0.3525   0.01767   0.00851  -0.0343   1.0000   0.0469
  -4.000  -0.3302   0.01691   0.00781  -0.0336   1.0000   0.0716
  -3.750  -0.3079   0.01636   0.00735  -0.0330   1.0000   0.1007
  -3.500  -0.2852   0.01584   0.00683  -0.0323   1.0000   0.1259
  -3.250  -0.2625   0.01537   0.00641  -0.0316   1.0000   0.1533
  -3.000  -0.2397   0.01494   0.00605  -0.0310   1.0000   0.1902
  -2.750  -0.2107   0.01451   0.00578  -0.0317   0.9973   0.2420
  -2.500  -0.1764   0.01406   0.00559  -0.0335   0.9919   0.3199
  -2.250  -0.1427   0.01356   0.00546  -0.0351   0.9863   0.4227
  -2.000  -0.1110   0.01305   0.00541  -0.0360   0.9806   0.5549
  -1.750  -0.0825   0.01267   0.00551  -0.0356   0.9738   0.6976
  -1.500  -0.0531   0.01254   0.00557  -0.0351   0.9672   0.8048
  -1.250  -0.0196   0.01245   0.00555  -0.0354   0.9604   0.8882
  -1.000   0.0353   0.01238   0.00538  -0.0406   0.9577   0.9681
  -0.750   0.0780   0.01235   0.00521  -0.0439   0.9505   1.0000
  -0.500   0.1180   0.01236   0.00510  -0.0465   0.9435   1.0000
  -0.250   0.1527   0.01236   0.00499  -0.0480   0.9338   1.0000
   0.000   0.1902   0.01234   0.00490  -0.0500   0.9253   1.0000
   0.250   0.2265   0.01230   0.00481  -0.0517   0.9157   1.0000
   0.500   0.2591   0.01227   0.00474  -0.0525   0.9041   1.0000
   0.750   0.2917   0.01224   0.00468  -0.0533   0.8920   1.0000
   1.000   0.3239   0.01220   0.00463  -0.0539   0.8791   1.0000
   1.250   0.3551   0.01216   0.00460  -0.0543   0.8648   1.0000
   1.500   0.3854   0.01212   0.00456  -0.0544   0.8492   1.0000
   1.750   0.4153   0.01209   0.00453  -0.0544   0.8324   1.0000
   2.000   0.4436   0.01208   0.00453  -0.0541   0.8133   1.0000
   2.250   0.4712   0.01209   0.00458  -0.0536   0.7922   1.0000
   2.500   0.4985   0.01211   0.00461  -0.0531   0.7692   1.0000
   2.750   0.5256   0.01215   0.00465  -0.0524   0.7435   1.0000
   3.000   0.5521   0.01224   0.00472  -0.0517   0.7141   1.0000
   3.250   0.5780   0.01236   0.00484  -0.0508   0.6809   1.0000
   3.500   0.6033   0.01254   0.00496  -0.0498   0.6433   1.0000
   3.750   0.6279   0.01279   0.00512  -0.0488   0.6015   1.0000
   4.000   0.6516   0.01312   0.00533  -0.0477   0.5557   1.0000
   4.250   0.6747   0.01353   0.00564  -0.0465   0.5074   1.0000
   4.500   0.6972   0.01400   0.00597  -0.0453   0.4567   1.0000
   4.750   0.7192   0.01455   0.00636  -0.0442   0.4038   1.0000
   5.000   0.7397   0.01526   0.00679  -0.0429   0.3405   1.0000
   5.250   0.7591   0.01613   0.00730  -0.0417   0.2648   1.0000
   5.500   0.7782   0.01716   0.00794  -0.0406   0.1868   1.0000
   5.750   0.7983   0.01819   0.00865  -0.0397   0.1239   1.0000
   6.000   0.8175   0.01945   0.00960  -0.0386   0.0706   1.0000
   6.250   0.8366   0.02078   0.01074  -0.0374   0.0455   1.0000
   6.500   0.8569   0.02191   0.01197  -0.0362   0.0379   1.0000
   6.750   0.8764   0.02312   0.01327  -0.0350   0.0341   1.0000
   7.000   0.8945   0.02450   0.01478  -0.0335   0.0319   1.0000
   7.250   0.9139   0.02583   0.01634  -0.0322   0.0304   1.0000
   7.500   0.9334   0.02732   0.01800  -0.0309   0.0292   1.0000
   7.750   0.9536   0.02895   0.01979  -0.0298   0.0280   1.0000
   8.000   0.9735   0.03049   0.02148  -0.0288   0.0262   1.0000
   8.250   0.9917   0.03226   0.02332  -0.0279   0.0243   1.0000
   8.500   1.0100   0.03485   0.02611  -0.0269   0.0234   1.0000
   8.750   1.0280   0.03725   0.02887  -0.0257   0.0229   1.0000
   9.000   1.0431   0.04001   0.03204  -0.0242   0.0225   1.0000
   9.250   1.0543   0.04307   0.03559  -0.0225   0.0222   1.0000
   9.500   1.0607   0.04644   0.03941  -0.0206   0.0220   1.0000
   9.750   1.0622   0.04999   0.04341  -0.0185   0.0218   1.0000
  10.000   1.0582   0.05367   0.04749  -0.0162   0.0217   1.0000
  10.250   1.0484   0.05721   0.05137  -0.0138   0.0215   1.0000
  10.500   1.0333   0.06070   0.05514  -0.0114   0.0214   1.0000
  10.750   1.0155   0.06463   0.05931  -0.0103   0.0213   1.0000
  11.000   0.9963   0.06921   0.06411  -0.0108   0.0214   1.0000
  11.250   0.9754   0.07475   0.06983  -0.0130   0.0216   1.0000
  11.500   0.9545   0.08136   0.07659  -0.0171   0.0219   1.0000
  11.750   0.9331   0.08944   0.08479  -0.0230   0.0222   1.0000
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