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Joukovsky f=0% t=21% (joukowsk0021-jf) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Joukovsky f=0% t=21% (joukowsk0021-jf)
Reynolds number: 50,000
Max Cl/Cd: 17.2 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk0021-jf-50000-n5.txt
Download as CSV file: xf-joukowsk0021-jf-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=21%                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.5498   0.10861   0.09923  -0.0066   1.0000   0.2021
 -12.000  -0.5291   0.10784   0.09849  -0.0063   1.0000   0.2051
 -11.500  -0.5471   0.09726   0.08788  -0.0109   1.0000   0.2173
 -11.000  -0.5725   0.08589   0.07648  -0.0158   1.0000   0.2314
 -10.750  -0.5434   0.08654   0.07716  -0.0148   1.0000   0.2338
 -10.250  -0.5670   0.07594   0.06655  -0.0190   1.0000   0.2489
  -9.750  -0.5977   0.06514   0.05573  -0.0230   1.0000   0.2654
  -9.250  -0.6413   0.05444   0.04498  -0.0264   1.0000   0.2828
  -9.000  -0.5976   0.05629   0.04696  -0.0252   1.0000   0.2855
  -8.750  -0.7112   0.04464   0.03507  -0.0266   1.0000   0.2990
  -8.500  -0.6488   0.04696   0.03759  -0.0267   1.0000   0.3027
  -8.250  -0.6276   0.04679   0.03752  -0.0262   1.0000   0.3079
  -8.000  -0.7113   0.04133   0.03188  -0.0222   0.9803   0.3163
  -7.750  -0.6528   0.04193   0.03260  -0.0256   0.9641   0.3225
  -7.500  -0.6213   0.04076   0.03134  -0.0284   0.9423   0.3311
  -7.250  -0.5996   0.03933   0.02980  -0.0301   0.9210   0.3394
  -7.000  -0.5594   0.03943   0.02993  -0.0314   0.9040   0.3462
  -6.750  -0.5687   0.03712   0.02733  -0.0300   0.8825   0.3561
  -6.500  -0.5283   0.03768   0.02799  -0.0302   0.8676   0.3614
  -6.250  -0.5122   0.03713   0.02736  -0.0290   0.8516   0.3690
  -6.000  -0.5085   0.03599   0.02607  -0.0271   0.8351   0.3773
  -5.750  -0.4797   0.03623   0.02636  -0.0262   0.8211   0.3832
  -5.500  -0.4712   0.03535   0.02534  -0.0242   0.8080   0.3921
  -5.250  -0.4531   0.03500   0.02497  -0.0230   0.7938   0.3991
  -5.000  -0.4288   0.03501   0.02497  -0.0217   0.7824   0.4059
  -4.750  -0.4244   0.03390   0.02367  -0.0199   0.7688   0.4163
  -4.500  -0.3946   0.03416   0.02400  -0.0189   0.7582   0.4217
  -4.250  -0.3745   0.03395   0.02378  -0.0177   0.7454   0.4297
  -4.000  -0.3602   0.03329   0.02298  -0.0161   0.7357   0.4390
  -3.750  -0.3339   0.03345   0.02322  -0.0153   0.7230   0.4453
  -3.500  -0.3172   0.03291   0.02254  -0.0137   0.7141   0.4551
  -3.250  -0.2953   0.03283   0.02250  -0.0129   0.7015   0.4625
  -3.000  -0.2708   0.03277   0.02242  -0.0117   0.6921   0.4700
  -2.750  -0.2554   0.03223   0.02178  -0.0107   0.6813   0.4807
  -2.500  -0.2278   0.03240   0.02201  -0.0097   0.6708   0.4870
  -2.250  -0.2058   0.03217   0.02172  -0.0086   0.6620   0.4961
  -2.000  -0.1854   0.03200   0.02154  -0.0078   0.6506   0.5051
  -1.750  -0.1591   0.03199   0.02152  -0.0065   0.6424   0.5125
  -1.500  -0.1420   0.03166   0.02112  -0.0058   0.6314   0.5238
  -1.250  -0.1151   0.03179   0.02130  -0.0048   0.6220   0.5303
  -1.000  -0.0914   0.03173   0.02122  -0.0037   0.6133   0.5393
  -0.750  -0.0713   0.03159   0.02107  -0.0030   0.6025   0.5492
  -0.500  -0.0443   0.03160   0.02108  -0.0018   0.5950   0.5566
  -0.250  -0.0250   0.03156   0.02102  -0.0011   0.5842   0.5676
   0.000   0.0000   0.03158   0.02106   0.0000   0.5752   0.5753
   0.250   0.0250   0.03156   0.02102   0.0010   0.5676   0.5842
   0.500   0.0443   0.03160   0.02107   0.0018   0.5566   0.5950
   0.750   0.0713   0.03159   0.02107   0.0030   0.5492   0.6026
   1.000   0.0914   0.03173   0.02122   0.0037   0.5393   0.6133
   1.250   0.1151   0.03179   0.02131   0.0047   0.5303   0.6220
   1.500   0.1420   0.03166   0.02112   0.0058   0.5238   0.6314
   1.750   0.1591   0.03198   0.02152   0.0065   0.5125   0.6423
   2.000   0.1854   0.03200   0.02154   0.0078   0.5050   0.6506
   2.250   0.2058   0.03217   0.02172   0.0086   0.4961   0.6620
   2.500   0.2278   0.03240   0.02201   0.0097   0.4870   0.6708
   2.750   0.2554   0.03223   0.02178   0.0107   0.4807   0.6813
   3.000   0.2708   0.03277   0.02242   0.0117   0.4700   0.6921
   3.250   0.2953   0.03283   0.02250   0.0129   0.4625   0.7015
   3.500   0.3173   0.03291   0.02254   0.0137   0.4551   0.7141
   3.750   0.3340   0.03345   0.02321   0.0153   0.4453   0.7230
   4.000   0.3603   0.03329   0.02298   0.0161   0.4390   0.7356
   4.250   0.3745   0.03395   0.02378   0.0177   0.4297   0.7455
   4.500   0.3947   0.03416   0.02399   0.0189   0.4217   0.7582
   4.750   0.4244   0.03390   0.02367   0.0199   0.4163   0.7689
   5.000   0.4289   0.03500   0.02496   0.0217   0.4058   0.7824
   5.250   0.4532   0.03500   0.02496   0.0230   0.3991   0.7939
   5.500   0.4713   0.03535   0.02533   0.0242   0.3921   0.8081
   5.750   0.4799   0.03622   0.02636   0.0262   0.3832   0.8211
   6.000   0.5087   0.03598   0.02606   0.0270   0.3773   0.8351
   6.250   0.5125   0.03712   0.02735   0.0290   0.3690   0.8517
   6.500   0.5285   0.03768   0.02799   0.0302   0.3614   0.8677
   6.750   0.5690   0.03710   0.02731   0.0300   0.3561   0.8825
   7.000   0.5599   0.03941   0.02990   0.0314   0.3461   0.9040
   7.250   0.6000   0.03931   0.02979   0.0301   0.3394   0.9210
   7.500   0.6218   0.04074   0.03133   0.0284   0.3311   0.9424
   7.750   0.6535   0.04189   0.03256   0.0255   0.3224   0.9641
   8.000   0.7113   0.04135   0.03191   0.0222   0.3162   0.9807
   8.250   0.6285   0.04673   0.03747   0.0261   0.3079   1.0000
   8.500   0.6496   0.04693   0.03756   0.0266   0.3027   1.0000
   8.750   0.7123   0.04459   0.03502   0.0266   0.2990   1.0000
   9.000   0.5990   0.05619   0.04685   0.0252   0.2855   1.0000
   9.250   0.6432   0.05428   0.04482   0.0264   0.2828   1.0000
   9.750   0.5989   0.06507   0.05566   0.0230   0.2654   1.0000
  10.750   0.5448   0.08647   0.07709   0.0147   0.2338   1.0000
  11.000   0.5739   0.08579   0.07638   0.0157   0.2314   1.0000
  11.500   0.5487   0.09715   0.08777   0.0109   0.2173   1.0000
  12.000   0.5306   0.10776   0.09841   0.0062   0.2051   1.0000
  12.250   0.5516   0.10849   0.09911   0.0065   0.2021   1.0000
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