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12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il)
Reynolds number: 100,000
Max Cl/Cd: 34.77 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk-il-100000.txt
Download as CSV file: xf-joukowsk-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8105   0.09726   0.09199   0.0055   1.0000   0.0929
 -11.750  -0.8146   0.09158   0.08632   0.0032   1.0000   0.0938
 -11.500  -1.0325   0.06111   0.05494  -0.0191   1.0000   0.0806
 -11.250  -1.0434   0.05632   0.04993  -0.0189   1.0000   0.0812
 -11.000  -1.0371   0.05296   0.04651  -0.0186   1.0000   0.0827
 -10.750  -1.0269   0.05037   0.04384  -0.0181   1.0000   0.0845
 -10.500  -1.0219   0.04754   0.04078  -0.0174   1.0000   0.0867
 -10.250  -1.0193   0.04429   0.03712  -0.0165   1.0000   0.0892
 -10.000  -1.0153   0.04113   0.03335  -0.0154   1.0000   0.0916
  -9.750  -0.9993   0.03823   0.03033  -0.0150   1.0000   0.0945
  -9.500  -0.9794   0.03663   0.02868  -0.0145   1.0000   0.0987
  -9.250  -0.9632   0.03458   0.02622  -0.0136   1.0000   0.1034
  -9.000  -0.9427   0.03241   0.02398  -0.0131   1.0000   0.1078
  -8.750  -0.9212   0.03104   0.02250  -0.0126   1.0000   0.1139
  -8.500  -0.9001   0.02922   0.02047  -0.0120   1.0000   0.1202
  -8.250  -0.8769   0.02801   0.01926  -0.0115   1.0000   0.1277
  -8.000  -0.8540   0.02655   0.01775  -0.0110   1.0000   0.1360
  -7.750  -0.8311   0.02548   0.01645  -0.0104   1.0000   0.1460
  -7.500  -0.8071   0.02430   0.01544  -0.0100   1.0000   0.1567
  -7.250  -0.7833   0.02321   0.01439  -0.0095   1.0000   0.1689
  -7.000  -0.7594   0.02223   0.01343  -0.0090   1.0000   0.1829
  -6.750  -0.7354   0.02133   0.01257  -0.0085   1.0000   0.1987
  -6.500  -0.7113   0.02051   0.01180  -0.0080   1.0000   0.2164
  -6.250  -0.6871   0.01978   0.01107  -0.0075   1.0000   0.2366
  -6.000  -0.6627   0.01906   0.01046  -0.0070   1.0000   0.2571
  -5.750  -0.6383   0.01845   0.00999  -0.0064   1.0000   0.2790
  -5.500  -0.6136   0.01791   0.00945  -0.0059   1.0000   0.3033
  -5.250  -0.5891   0.01740   0.00911  -0.0053   1.0000   0.3260
  -5.000  -0.5643   0.01697   0.00870  -0.0048   1.0000   0.3515
  -4.750  -0.5397   0.01655   0.00846  -0.0041   1.0000   0.3745
  -4.500  -0.5152   0.01619   0.00816  -0.0035   1.0000   0.3996
  -4.250  -0.4911   0.01585   0.00796  -0.0027   1.0000   0.4228
  -4.000  -0.4676   0.01556   0.00778  -0.0018   1.0000   0.4465
  -3.750  -0.4450   0.01529   0.00758  -0.0008   1.0000   0.4701
  -3.500  -0.4240   0.01505   0.00749   0.0004   1.0000   0.4916
  -3.250  -0.4045   0.01485   0.00739   0.0018   1.0000   0.5138
  -3.000  -0.3867   0.01470   0.00729   0.0034   1.0000   0.5361
  -2.750  -0.3703   0.01459   0.00731   0.0051   1.0000   0.5561
  -2.500  -0.3546   0.01455   0.00738   0.0067   1.0000   0.5765
  -2.250  -0.3243   0.01460   0.00750   0.0056   0.9935   0.6017
  -2.000  -0.2717   0.01466   0.00771   0.0010   0.9761   0.6295
  -1.750  -0.2181   0.01469   0.00784  -0.0037   0.9601   0.6580
  -1.500  -0.1685   0.01470   0.00796  -0.0071   0.9432   0.6838
  -1.250  -0.1260   0.01470   0.00801  -0.0091   0.9242   0.7085
  -1.000  -0.0933   0.01471   0.00811  -0.0088   0.9018   0.7299
  -0.750  -0.0653   0.01473   0.00816  -0.0075   0.8799   0.7512
  -0.500  -0.0416   0.01474   0.00818  -0.0054   0.8583   0.7729
  -0.250  -0.0205   0.01475   0.00822  -0.0029   0.8354   0.7938
   0.000   0.0000   0.01475   0.00823   0.0000   0.8140   0.8140
   0.250   0.0205   0.01475   0.00822   0.0029   0.7938   0.8354
   0.500   0.0415   0.01474   0.00818   0.0054   0.7729   0.8584
   0.750   0.0653   0.01473   0.00816   0.0075   0.7512   0.8799
   1.000   0.0933   0.01471   0.00811   0.0088   0.7299   0.9018
   1.250   0.1260   0.01469   0.00801   0.0091   0.7085   0.9242
   1.500   0.1685   0.01471   0.00796   0.0071   0.6838   0.9432
   1.750   0.2181   0.01469   0.00784   0.0037   0.6581   0.9601
   2.000   0.2717   0.01466   0.00771  -0.0010   0.6296   0.9761
   2.250   0.3243   0.01459   0.00750  -0.0056   0.6017   0.9935
   2.500   0.3546   0.01455   0.00738  -0.0067   0.5765   1.0000
   2.750   0.3702   0.01459   0.00731  -0.0051   0.5560   1.0000
   3.000   0.3866   0.01470   0.00729  -0.0034   0.5362   1.0000
   3.250   0.4045   0.01485   0.00739  -0.0018   0.5138   1.0000
   3.500   0.4239   0.01505   0.00749  -0.0004   0.4917   1.0000
   3.750   0.4450   0.01529   0.00758   0.0008   0.4701   1.0000
   4.000   0.4676   0.01556   0.00778   0.0018   0.4465   1.0000
   4.250   0.4911   0.01585   0.00796   0.0027   0.4228   1.0000
   4.500   0.5152   0.01619   0.00816   0.0035   0.3996   1.0000
   4.750   0.5398   0.01655   0.00846   0.0041   0.3745   1.0000
   5.000   0.5643   0.01697   0.00870   0.0048   0.3515   1.0000
   5.250   0.5891   0.01740   0.00911   0.0053   0.3260   1.0000
   5.500   0.6136   0.01791   0.00945   0.0059   0.3033   1.0000
   5.750   0.6383   0.01845   0.00999   0.0065   0.2790   1.0000
   6.000   0.6627   0.01906   0.01046   0.0070   0.2571   1.0000
   6.250   0.6870   0.01978   0.01108   0.0075   0.2366   1.0000
   6.500   0.7113   0.02051   0.01180   0.0080   0.2164   1.0000
   6.750   0.7354   0.02133   0.01257   0.0085   0.1987   1.0000
   7.000   0.7594   0.02222   0.01343   0.0090   0.1829   1.0000
   7.250   0.7833   0.02321   0.01439   0.0095   0.1688   1.0000
   7.500   0.8070   0.02430   0.01544   0.0100   0.1567   1.0000
   7.750   0.8311   0.02548   0.01644   0.0104   0.1460   1.0000
   8.000   0.8540   0.02655   0.01774   0.0110   0.1360   1.0000
   8.250   0.8769   0.02800   0.01925   0.0115   0.1277   1.0000
   8.500   0.9000   0.02922   0.02047   0.0120   0.1202   1.0000
   8.750   0.9212   0.03104   0.02251   0.0126   0.1139   1.0000
   9.000   0.9427   0.03241   0.02398   0.0131   0.1079   1.0000
   9.250   0.9632   0.03458   0.02622   0.0136   0.1033   1.0000
   9.500   0.9794   0.03663   0.02868   0.0145   0.0987   1.0000
   9.750   0.9993   0.03823   0.03033   0.0150   0.0945   1.0000
  10.000   1.0153   0.04114   0.03336   0.0154   0.0915   1.0000
  10.250   1.0193   0.04428   0.03711   0.0165   0.0891   1.0000
  10.500   1.0220   0.04752   0.04075   0.0174   0.0867   1.0000
  10.750   1.0272   0.05034   0.04379   0.0181   0.0844   1.0000
  11.000   1.0382   0.05285   0.04637   0.0186   0.0825   1.0000
  11.250   1.0447   0.05633   0.04993   0.0189   0.0810   1.0000
  11.500   1.0319   0.06107   0.05491   0.0192   0.0805   1.0000
  11.750   1.0072   0.06545   0.05952   0.0196   0.0806   1.0000
  12.000   0.6972   0.13784   0.13250  -0.0296   0.1607   1.0000
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