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Joukovsky f=0% t=9% (joukowsk0009-jf) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: Joukovsky f=0% t=9% (joukowsk0009-jf)
Reynolds number: 100,000
Max Cl/Cd: 34.27 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk0009-jf-100000-n5.txt
Download as CSV file: xf-joukowsk0009-jf-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=9%                             
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.8868   0.07102   0.06579  -0.0029   1.0000   0.0287
 -11.000  -0.9305   0.06086   0.05526  -0.0116   1.0000   0.0280
 -10.750  -0.9506   0.05607   0.05024  -0.0136   1.0000   0.0280
 -10.500  -0.9611   0.05251   0.04647  -0.0135   1.0000   0.0282
 -10.250  -0.9624   0.04931   0.04305  -0.0135   1.0000   0.0287
 -10.000  -0.9579   0.04656   0.04009  -0.0133   1.0000   0.0294
  -9.750  -0.9500   0.04405   0.03734  -0.0130   1.0000   0.0306
  -9.500  -0.9405   0.04129   0.03424  -0.0126   1.0000   0.0320
  -9.250  -0.9290   0.03831   0.03081  -0.0121   1.0000   0.0334
  -9.000  -0.9142   0.03549   0.02750  -0.0115   1.0000   0.0346
  -8.750  -0.8966   0.03302   0.02481  -0.0110   1.0000   0.0358
  -8.500  -0.8767   0.03145   0.02315  -0.0106   1.0000   0.0377
  -8.250  -0.8557   0.02998   0.02150  -0.0102   1.0000   0.0403
  -8.000  -0.8338   0.02832   0.01953  -0.0096   1.0000   0.0430
  -7.750  -0.8121   0.02659   0.01768  -0.0091   1.0000   0.0452
  -7.500  -0.7898   0.02538   0.01645  -0.0087   1.0000   0.0486
  -7.250  -0.7663   0.02424   0.01511  -0.0082   1.0000   0.0531
  -7.000  -0.7437   0.02294   0.01377  -0.0077   1.0000   0.0570
  -6.750  -0.7201   0.02194   0.01271  -0.0073   1.0000   0.0628
  -6.500  -0.6965   0.02091   0.01164  -0.0069   1.0000   0.0696
  -6.250  -0.6721   0.02004   0.01065  -0.0064   1.0000   0.0782
  -6.000  -0.6481   0.01913   0.00978  -0.0061   1.0000   0.0892
  -5.750  -0.6237   0.01828   0.00895  -0.0058   1.0000   0.1029
  -5.500  -0.5990   0.01749   0.00822  -0.0055   1.0000   0.1211
  -5.250  -0.5741   0.01675   0.00755  -0.0052   1.0000   0.1449
  -5.000  -0.5490   0.01607   0.00698  -0.0050   1.0000   0.1744
  -4.750  -0.5238   0.01543   0.00649  -0.0047   1.0000   0.2091
  -4.500  -0.4984   0.01487   0.00607  -0.0045   1.0000   0.2474
  -4.250  -0.4730   0.01437   0.00569  -0.0042   1.0000   0.2871
  -4.000  -0.4475   0.01392   0.00538  -0.0038   1.0000   0.3273
  -3.750  -0.4218   0.01353   0.00512  -0.0035   1.0000   0.3669
  -3.500  -0.3963   0.01317   0.00488  -0.0030   1.0000   0.4050
  -3.250  -0.3707   0.01287   0.00468  -0.0025   1.0000   0.4422
  -3.000  -0.3453   0.01258   0.00453  -0.0020   1.0000   0.4771
  -2.750  -0.3201   0.01233   0.00439  -0.0014   1.0000   0.5109
  -2.500  -0.2950   0.01210   0.00426  -0.0007   1.0000   0.5435
  -2.250  -0.2703   0.01190   0.00417   0.0000   1.0000   0.5749
  -2.000  -0.2461   0.01172   0.00411   0.0009   1.0000   0.6053
  -1.750  -0.2225   0.01156   0.00405   0.0018   1.0000   0.6348
  -1.500  -0.1997   0.01142   0.00404   0.0028   0.9995   0.6637
  -1.250  -0.1605   0.01137   0.00408   0.0008   0.9735   0.6960
  -1.000  -0.1224   0.01133   0.00412  -0.0009   0.9481   0.7267
  -0.750  -0.0866   0.01130   0.00416  -0.0020   0.9220   0.7560
  -0.500  -0.0545   0.01128   0.00419  -0.0021   0.8948   0.7841
  -0.250  -0.0260   0.01128   0.00421  -0.0013   0.8672   0.8116
   0.000   0.0000   0.01128   0.00421   0.0000   0.8391   0.8392
   0.250   0.0260   0.01128   0.00421   0.0013   0.8115   0.8672
   0.500   0.0545   0.01128   0.00419   0.0021   0.7841   0.8948
   0.750   0.0866   0.01130   0.00416   0.0019   0.7560   0.9220
   1.000   0.1225   0.01133   0.00412   0.0009   0.7268   0.9481
   1.250   0.1606   0.01137   0.00408  -0.0008   0.6960   0.9734
   1.500   0.1997   0.01142   0.00404  -0.0029   0.6637   0.9995
   1.750   0.2226   0.01156   0.00405  -0.0018   0.6348   1.0000
   2.000   0.2462   0.01172   0.00411  -0.0009   0.6053   1.0000
   2.250   0.2704   0.01190   0.00417  -0.0001   0.5749   1.0000
   2.500   0.2951   0.01210   0.00426   0.0007   0.5435   1.0000
   2.750   0.3202   0.01233   0.00439   0.0013   0.5109   1.0000
   3.000   0.3454   0.01258   0.00453   0.0020   0.4771   1.0000
   3.250   0.3708   0.01287   0.00469   0.0025   0.4421   1.0000
   3.500   0.3964   0.01318   0.00488   0.0030   0.4049   1.0000
   3.750   0.4219   0.01353   0.00512   0.0034   0.3669   1.0000
   4.000   0.4475   0.01392   0.00539   0.0038   0.3273   1.0000
   4.250   0.4730   0.01437   0.00569   0.0042   0.2871   1.0000
   4.500   0.4984   0.01487   0.00607   0.0045   0.2474   1.0000
   4.750   0.5238   0.01543   0.00649   0.0047   0.2091   1.0000
   5.000   0.5490   0.01607   0.00698   0.0050   0.1744   1.0000
   5.250   0.5741   0.01675   0.00755   0.0052   0.1450   1.0000
   5.500   0.5990   0.01749   0.00822   0.0055   0.1211   1.0000
   5.750   0.6236   0.01828   0.00895   0.0058   0.1029   1.0000
   6.000   0.6481   0.01913   0.00977   0.0061   0.0892   1.0000
   6.250   0.6721   0.02003   0.01064   0.0064   0.0781   1.0000
   6.500   0.6964   0.02091   0.01164   0.0069   0.0696   1.0000
   6.750   0.7199   0.02194   0.01271   0.0073   0.0627   1.0000
   7.000   0.7435   0.02293   0.01377   0.0078   0.0571   1.0000
   7.250   0.7661   0.02424   0.01511   0.0083   0.0531   1.0000
   7.500   0.7896   0.02539   0.01646   0.0088   0.0487   1.0000
   7.750   0.8119   0.02658   0.01767   0.0091   0.0452   1.0000
   8.000   0.8335   0.02831   0.01953   0.0097   0.0430   1.0000
   8.250   0.8553   0.02997   0.02149   0.0103   0.0404   1.0000
   8.500   0.8760   0.03144   0.02315   0.0108   0.0377   1.0000
   8.750   0.8957   0.03299   0.02478   0.0111   0.0358   1.0000
   9.000   0.9132   0.03545   0.02745   0.0117   0.0346   1.0000
   9.250   0.9281   0.03826   0.03075   0.0123   0.0334   1.0000
   9.500   0.9396   0.04122   0.03416   0.0128   0.0320   1.0000
   9.750   0.9492   0.04395   0.03723   0.0132   0.0306   1.0000
  10.000   0.9563   0.04663   0.04017   0.0135   0.0295   1.0000
  10.250   0.9616   0.04919   0.04292   0.0137   0.0287   1.0000
  10.500   0.9601   0.05244   0.04640   0.0138   0.0282   1.0000
  10.750   0.9487   0.05609   0.05027   0.0138   0.0281   1.0000
  11.000   0.9290   0.06087   0.05528   0.0117   0.0281   1.0000
  11.250   0.8873   0.07073   0.06549   0.0033   0.0286   1.0000
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