Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Joukovsky f=0% t=18% (joukowsk0018-jf) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=18% (joukowsk0018-jf)
Reynolds number: 50,000
Max Cl/Cd: 14.89 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0018-jf-50000.txt
Download as CSV file: xf-joukowsk0018-jf-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=18%                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4141   0.12701   0.11848   0.0226   1.0000   0.4085
 -10.250  -0.3827   0.12246   0.11390   0.0219   1.0000   0.4176
 -10.000  -0.4174   0.12369   0.11519   0.0220   1.0000   0.4270
  -9.750  -0.3647   0.11660   0.10806   0.0207   1.0000   0.4354
  -9.500  -0.3851   0.11667   0.10816   0.0209   1.0000   0.4469
  -9.250  -0.3477   0.11097   0.10246   0.0196   1.0000   0.4541
  -9.000  -0.3562   0.11019   0.10169   0.0198   1.0000   0.4670
  -8.750  -0.3308   0.10553   0.09704   0.0187   1.0000   0.4734
  -8.500  -0.3288   0.10405   0.09558   0.0188   1.0000   0.4871
  -8.250  -0.4047   0.09394   0.08543   0.0107   1.0000   0.4065
  -8.000  -0.3872   0.08983   0.08130   0.0093   1.0000   0.4046
  -7.750  -0.3816   0.08576   0.07723   0.0079   1.0000   0.4026
  -7.500  -0.3857   0.08162   0.07311   0.0064   1.0000   0.4025
  -7.250  -0.3982   0.07714   0.06867   0.0047   1.0000   0.4038
  -7.000  -0.4284   0.07148   0.06307   0.0027   1.0000   0.4059
  -6.750  -0.3726   0.07235   0.06396   0.0042   1.0000   0.4192
  -6.500  -0.3941   0.06778   0.05945   0.0029   1.0000   0.4235
  -6.250  -0.3857   0.06545   0.05720   0.0029   1.0000   0.4317
  -6.000  -0.3766   0.06354   0.05535   0.0031   1.0000   0.4404
  -5.750  -0.4422   0.05904   0.05106   0.0059   1.0000   0.4437
  -5.500  -0.5647   0.05338   0.04554   0.0138   1.0000   0.4437
  -5.250  -0.6266   0.04866   0.04076   0.0180   1.0000   0.4499
  -5.000  -0.6072   0.04987   0.04207   0.0210   1.0000   0.4573
  -4.750  -0.6583   0.04420   0.03616   0.0229   1.0000   0.4688
  -4.500  -0.6301   0.04588   0.03801   0.0252   0.9989   0.4757
  -4.250  -0.5848   0.04465   0.03666   0.0193   0.9828   0.4927
  -4.000  -0.5440   0.04321   0.03507   0.0137   0.9666   0.5107
  -3.750  -0.4676   0.04551   0.03751   0.0099   0.9519   0.5225
  -3.500  -0.4219   0.04494   0.03688   0.0058   0.9360   0.5379
  -3.250  -0.3944   0.04348   0.03531   0.0026   0.9200   0.5546
  -3.000  -0.3252   0.04473   0.03661  -0.0011   0.9050   0.5678
  -2.750  -0.2746   0.04448   0.03634  -0.0048   0.8903   0.5824
  -2.500  -0.2441   0.04344   0.03522  -0.0072   0.8757   0.5989
  -2.250  -0.1830   0.04398   0.03578  -0.0099   0.8605   0.6120
  -2.000  -0.1699   0.04349   0.03528  -0.0087   0.8442   0.6244
  -1.750  -0.1563   0.04302   0.03477  -0.0076   0.8288   0.6385
  -1.500  -0.1016   0.04325   0.03501  -0.0094   0.8152   0.6508
  -1.250  -0.1056   0.04250   0.03422  -0.0067   0.8002   0.6654
  -1.000  -0.0731   0.04295   0.03470  -0.0059   0.7845   0.6761
  -0.750  -0.0519   0.04251   0.03422  -0.0049   0.7721   0.6904
  -0.500  -0.0349   0.04251   0.03422  -0.0032   0.7571   0.7036
  -0.250  -0.0205   0.04261   0.03434  -0.0014   0.7426   0.7156
   0.000   0.0000   0.04206   0.03373   0.0000   0.7319   0.7319
   0.250   0.0206   0.04261   0.03434   0.0014   0.7155   0.7427
   0.500   0.0351   0.04251   0.03422   0.0032   0.7036   0.7572
   0.750   0.0518   0.04252   0.03422   0.0050   0.6905   0.7722
   1.000   0.0731   0.04295   0.03470   0.0059   0.6760   0.7845
   1.250   0.1055   0.04250   0.03422   0.0067   0.6654   0.8002
   1.500   0.1014   0.04325   0.03501   0.0094   0.6509   0.8153
   1.750   0.1562   0.04302   0.03477   0.0076   0.6385   0.8288
   2.000   0.1702   0.04348   0.03527   0.0087   0.6244   0.8442
   2.250   0.1830   0.04397   0.03578   0.0099   0.6119   0.8605
   2.500   0.2434   0.04345   0.03524   0.0072   0.5990   0.8757
   2.750   0.2744   0.04447   0.03633   0.0048   0.5824   0.8903
   3.000   0.3254   0.04472   0.03660   0.0011   0.5679   0.9051
   3.250   0.3946   0.04348   0.03531  -0.0027   0.5546   0.9201
   3.500   0.4217   0.04498   0.03693  -0.0058   0.5380   0.9361
   3.750   0.4678   0.04551   0.03750  -0.0099   0.5226   0.9519
   4.000   0.5440   0.04323   0.03509  -0.0137   0.5107   0.9667
   4.250   0.5847   0.04466   0.03667  -0.0193   0.4927   0.9829
   4.500   0.6302   0.04587   0.03799  -0.0252   0.4757   0.9990
   4.750   0.6582   0.04419   0.03614  -0.0228   0.4688   1.0000
   5.000   0.6070   0.04986   0.04206  -0.0210   0.4574   1.0000
   5.250   0.6251   0.04878   0.04088  -0.0180   0.4500   1.0000
   5.500   0.5657   0.05331   0.04546  -0.0138   0.4437   1.0000
   5.750   0.4427   0.05900   0.05102  -0.0059   0.4437   1.0000
   6.000   0.3771   0.06351   0.05533  -0.0031   0.4404   1.0000
   6.250   0.3849   0.06552   0.05727  -0.0030   0.4318   1.0000
   6.500   0.3947   0.06775   0.05942  -0.0030   0.4234   1.0000
   6.750   0.3733   0.07233   0.06393  -0.0043   0.4192   1.0000
   7.000   0.4290   0.07146   0.06305  -0.0027   0.4059   1.0000
   7.250   0.3991   0.07711   0.06864  -0.0048   0.4038   1.0000
   7.500   0.3864   0.08159   0.07309  -0.0064   0.4024   1.0000
   7.750   0.3819   0.08575   0.07722  -0.0080   0.4025   1.0000
   8.000   0.3872   0.08982   0.08129  -0.0095   0.4045   1.0000
   8.250   0.4046   0.09394   0.08542  -0.0108   0.4065   1.0000
   8.500   0.3287   0.10396   0.09549  -0.0189   0.4869   1.0000
   8.750   0.3326   0.10557   0.09708  -0.0188   0.4732   1.0000
   9.000   0.3560   0.11009   0.10159  -0.0199   0.4668   1.0000
   9.250   0.3492   0.11099   0.10248  -0.0198   0.4539   1.0000
   9.500   0.3847   0.11656   0.10806  -0.0210   0.4468   1.0000
   9.750   0.3661   0.11663   0.10809  -0.0209   0.4352   1.0000
  10.000   0.4179   0.12367   0.11516  -0.0222   0.4270   1.0000
  10.250   0.3840   0.12247   0.11392  -0.0221   0.4173   1.0000
  10.500   0.4161   0.12712   0.11860  -0.0228   0.4084   1.0000
<< Back to Joukovsky f=0% t=18% (joukowsk0018-jf)

Polar data table (+)

Polar graphs


<< Back to Joukovsky f=0% t=18% (joukowsk0018-jf)