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12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il)
Reynolds number: 100,000
Max Cl/Cd: 37.23 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk-il-100000-n5.txt
Download as CSV file: xf-joukowsk-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 12% JOUKOWSKI AIRFOIL                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.9669   0.09262   0.08677   0.0035   1.0000   0.0442
 -14.000  -1.0040   0.08160   0.07552  -0.0042   1.0000   0.0439
 -13.750  -1.0326   0.07301   0.06668  -0.0102   1.0000   0.0440
 -13.500  -1.0550   0.06612   0.05952  -0.0148   1.0000   0.0442
 -13.250  -1.0738   0.06031   0.05341  -0.0183   1.0000   0.0446
 -13.000  -1.0724   0.05740   0.05051  -0.0192   1.0000   0.0454
 -12.750  -1.0743   0.05426   0.04729  -0.0203   1.0000   0.0461
 -12.500  -1.0767   0.05124   0.04415  -0.0211   1.0000   0.0469
 -12.250  -1.0792   0.04835   0.04110  -0.0216   1.0000   0.0478
 -12.000  -1.0809   0.04568   0.03825  -0.0216   1.0000   0.0488
 -11.750  -1.0817   0.04325   0.03559  -0.0209   1.0000   0.0501
 -11.500  -1.0813   0.04103   0.03310  -0.0198   1.0000   0.0516
 -11.250  -1.0736   0.03929   0.03131  -0.0187   1.0000   0.0530
 -11.000  -1.0626   0.03782   0.02980  -0.0179   1.0000   0.0548
 -10.750  -1.0504   0.03625   0.02812  -0.0171   1.0000   0.0568
 -10.500  -1.0368   0.03465   0.02628  -0.0162   1.0000   0.0592
 -10.250  -1.0219   0.03316   0.02469  -0.0154   1.0000   0.0616
 -10.000  -1.0057   0.03193   0.02345  -0.0147   1.0000   0.0643
  -9.750  -0.9881   0.03066   0.02205  -0.0140   1.0000   0.0677
  -9.500  -0.9699   0.02939   0.02066  -0.0133   1.0000   0.0711
  -9.250  -0.9512   0.02831   0.01957  -0.0126   1.0000   0.0749
  -9.000  -0.9309   0.02724   0.01835  -0.0120   1.0000   0.0795
  -8.750  -0.9112   0.02616   0.01729  -0.0114   1.0000   0.0840
  -8.500  -0.8899   0.02523   0.01626  -0.0108   1.0000   0.0898
  -8.250  -0.8688   0.02426   0.01529  -0.0103   1.0000   0.0956
  -8.000  -0.8465   0.02343   0.01438  -0.0098   1.0000   0.1031
  -7.750  -0.8246   0.02255   0.01354  -0.0093   1.0000   0.1105
  -7.500  -0.8016   0.02177   0.01271  -0.0088   1.0000   0.1198
  -7.250  -0.7783   0.02104   0.01196  -0.0084   1.0000   0.1300
  -7.000  -0.7551   0.02031   0.01128  -0.0080   1.0000   0.1412
  -6.750  -0.7312   0.01964   0.01062  -0.0076   1.0000   0.1537
  -6.500  -0.7071   0.01901   0.01003  -0.0072   1.0000   0.1678
  -6.250  -0.6827   0.01843   0.00948  -0.0069   1.0000   0.1831
  -6.000  -0.6580   0.01788   0.00896  -0.0065   1.0000   0.1999
  -5.750  -0.6331   0.01738   0.00850  -0.0062   1.0000   0.2177
  -5.500  -0.6081   0.01691   0.00807  -0.0059   1.0000   0.2368
  -5.250  -0.5830   0.01647   0.00769  -0.0055   1.0000   0.2561
  -5.000  -0.5580   0.01605   0.00736  -0.0051   1.0000   0.2760
  -4.750  -0.5330   0.01568   0.00705  -0.0047   1.0000   0.2967
  -4.500  -0.5079   0.01534   0.00676  -0.0043   1.0000   0.3178
  -4.250  -0.4833   0.01501   0.00652  -0.0038   1.0000   0.3383
  -4.000  -0.4592   0.01472   0.00632  -0.0033   1.0000   0.3589
  -3.750  -0.4358   0.01445   0.00615  -0.0026   1.0000   0.3795
  -3.250  -0.3693   0.01405   0.00590  -0.0051   0.9704   0.4257
  -3.000  -0.3309   0.01390   0.00579  -0.0071   0.9478   0.4500
  -2.750  -0.2942   0.01377   0.00572  -0.0086   0.9257   0.4728
  -2.500  -0.2619   0.01367   0.00566  -0.0091   0.9019   0.4946
  -2.250  -0.2321   0.01359   0.00559  -0.0089   0.8789   0.5158
  -2.000  -0.2049   0.01353   0.00553  -0.0083   0.8561   0.5362
  -1.750  -0.1790   0.01347   0.00549  -0.0073   0.8337   0.5555
  -1.500  -0.1536   0.01342   0.00544  -0.0062   0.8124   0.5749
  -1.250  -0.1282   0.01338   0.00540  -0.0051   0.7920   0.5943
  -1.000  -0.1027   0.01334   0.00537  -0.0040   0.7711   0.6138
  -0.750  -0.0771   0.01331   0.00534  -0.0030   0.7507   0.6333
  -0.500  -0.0514   0.01329   0.00532  -0.0020   0.7308   0.6529
  -0.250  -0.0257   0.01328   0.00530  -0.0010   0.7111   0.6727
   0.000   0.0000   0.01327   0.00529   0.0000   0.6918   0.6917
   0.250   0.0257   0.01328   0.00530   0.0010   0.6726   0.7111
   0.500   0.0514   0.01329   0.00532   0.0020   0.6529   0.7307
   0.750   0.0771   0.01331   0.00534   0.0030   0.6334   0.7507
   1.000   0.1027   0.01334   0.00537   0.0040   0.6138   0.7711
   1.250   0.1282   0.01338   0.00540   0.0051   0.5943   0.7920
   1.500   0.1536   0.01342   0.00544   0.0062   0.5750   0.8124
   1.750   0.1790   0.01347   0.00549   0.0073   0.5556   0.8337
   2.000   0.2049   0.01353   0.00553   0.0083   0.5362   0.8561
   2.250   0.2321   0.01359   0.00559   0.0089   0.5158   0.8789
   2.500   0.2619   0.01367   0.00566   0.0091   0.4945   0.9019
   2.750   0.2942   0.01377   0.00572   0.0086   0.4728   0.9257
   3.000   0.3309   0.01390   0.00579   0.0071   0.4501   0.9478
   3.250   0.3693   0.01405   0.00590   0.0051   0.4256   0.9705
   3.750   0.4358   0.01445   0.00615   0.0026   0.3795   1.0000
   4.000   0.4592   0.01472   0.00632   0.0033   0.3589   1.0000
   4.250   0.4833   0.01501   0.00652   0.0038   0.3383   1.0000
   4.500   0.5079   0.01534   0.00676   0.0043   0.3178   1.0000
   4.750   0.5330   0.01568   0.00705   0.0047   0.2967   1.0000
   5.000   0.5580   0.01605   0.00736   0.0051   0.2760   1.0000
   5.250   0.5830   0.01647   0.00769   0.0055   0.2561   1.0000
   5.500   0.6080   0.01691   0.00807   0.0059   0.2368   1.0000
   5.750   0.6331   0.01738   0.00850   0.0062   0.2177   1.0000
   6.000   0.6580   0.01788   0.00896   0.0065   0.1999   1.0000
   6.250   0.6826   0.01843   0.00948   0.0069   0.1831   1.0000
   6.500   0.7071   0.01901   0.01003   0.0072   0.1678   1.0000
   6.750   0.7312   0.01964   0.01062   0.0076   0.1537   1.0000
   7.000   0.7550   0.02031   0.01128   0.0080   0.1412   1.0000
   7.250   0.7783   0.02104   0.01196   0.0084   0.1300   1.0000
   7.500   0.8015   0.02177   0.01271   0.0088   0.1198   1.0000
   7.750   0.8246   0.02255   0.01354   0.0093   0.1106   1.0000
   8.000   0.8465   0.02342   0.01438   0.0098   0.1031   1.0000
   8.250   0.8688   0.02426   0.01528   0.0103   0.0956   1.0000
   8.500   0.8899   0.02523   0.01626   0.0108   0.0898   1.0000
   8.750   0.9111   0.02616   0.01728   0.0114   0.0839   1.0000
   9.000   0.9308   0.02724   0.01835   0.0120   0.0795   1.0000
   9.250   0.9511   0.02830   0.01956   0.0127   0.0748   1.0000
   9.500   0.9698   0.02939   0.02065   0.0133   0.0711   1.0000
   9.750   0.9880   0.03066   0.02204   0.0140   0.0677   1.0000
  10.000   1.0056   0.03193   0.02345   0.0147   0.0643   1.0000
  10.250   1.0219   0.03316   0.02469   0.0154   0.0617   1.0000
  10.500   1.0367   0.03464   0.02628   0.0162   0.0592   1.0000
  10.750   1.0503   0.03624   0.02811   0.0171   0.0568   1.0000
  11.000   1.0624   0.03780   0.02978   0.0179   0.0547   1.0000
  11.250   1.0733   0.03927   0.03128   0.0188   0.0530   1.0000
  11.500   1.0811   0.04101   0.03308   0.0198   0.0516   1.0000
  11.750   1.0813   0.04324   0.03559   0.0210   0.0501   1.0000
  12.000   1.0807   0.04566   0.03822   0.0216   0.0488   1.0000
  12.250   1.0791   0.04832   0.04106   0.0217   0.0478   1.0000
  12.500   1.0767   0.05120   0.04411   0.0212   0.0469   1.0000
  12.750   1.0746   0.05419   0.04720   0.0203   0.0461   1.0000
  13.000   1.0733   0.05724   0.05033   0.0193   0.0454   1.0000
  13.250   1.0733   0.06034   0.05344   0.0182   0.0446   1.0000
  13.500   1.0550   0.06606   0.05946   0.0149   0.0442   1.0000
  13.750   1.0324   0.07299   0.06666   0.0103   0.0440   1.0000
  14.000   1.0039   0.08154   0.07547   0.0043   0.0439   1.0000
  14.250   0.9658   0.09275   0.08691  -0.0037   0.0441   1.0000
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