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=5


Details Polar file
Airfoil: Joukovsky f=0% t=18% (joukowsk0018-jf)
Reynolds number: 50,000
Max Cl/Cd: 23.03 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk0018-jf-50000-n5.txt
Download as CSV file: xf-joukowsk0018-jf-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.6373   0.11884   0.10985   0.0055   1.0000   0.1580
 -12.750  -0.6760   0.10728   0.09826  -0.0008   1.0000   0.1648
 -12.250  -0.7231   0.09039   0.08130  -0.0093   1.0000   0.1778
 -12.000  -0.6898   0.09246   0.08339  -0.0071   1.0000   0.1799
 -11.750  -0.8322   0.06659   0.05726  -0.0217   1.0000   0.1923
 -11.500  -0.7594   0.07347   0.06430  -0.0166   1.0000   0.1947
 -11.250  -0.7485   0.07167   0.06251  -0.0167   1.0000   0.1995
 -11.000  -0.8911   0.05181   0.04215  -0.0263   1.0000   0.2074
 -10.750  -0.8468   0.05345   0.04398  -0.0248   1.0000   0.2127
 -10.500  -0.8675   0.04917   0.03956  -0.0254   1.0000   0.2183
 -10.250  -0.8935   0.04513   0.03532  -0.0247   1.0000   0.2235
 -10.000  -0.8647   0.04512   0.03545  -0.0241   1.0000   0.2293
  -9.750  -0.8731   0.04281   0.03302  -0.0226   1.0000   0.2354
  -9.500  -0.8677   0.04124   0.03140  -0.0214   1.0000   0.2416
  -9.250  -0.8502   0.04051   0.03073  -0.0206   1.0000   0.2483
  -9.000  -0.8551   0.03825   0.02824  -0.0191   1.0000   0.2560
  -8.750  -0.8273   0.03814   0.02831  -0.0185   1.0000   0.2625
  -8.500  -0.8194   0.03674   0.02682  -0.0174   1.0000   0.2707
  -8.250  -0.8008   0.03603   0.02617  -0.0165   1.0000   0.2779
  -8.000  -0.7855   0.03519   0.02533  -0.0155   1.0000   0.2862
  -7.750  -0.7718   0.03422   0.02434  -0.0144   1.0000   0.2943
  -7.500  -0.7534   0.03373   0.02393  -0.0134   1.0000   0.3023
  -7.250  -0.7454   0.03268   0.02281  -0.0118   1.0000   0.3111
  -7.000  -0.7293   0.03246   0.02273  -0.0101   1.0000   0.3182
  -6.750  -0.7296   0.03168   0.02189  -0.0071   1.0000   0.3264
  -6.500  -0.7101   0.03141   0.02170  -0.0065   0.9923   0.3342
  -6.250  -0.6720   0.03057   0.02070  -0.0099   0.9723   0.3477
  -6.000  -0.6269   0.03051   0.02077  -0.0128   0.9566   0.3580
  -5.750  -0.5885   0.02995   0.02013  -0.0154   0.9394   0.3704
  -5.500  -0.5509   0.02964   0.01981  -0.0174   0.9227   0.3820
  -5.250  -0.5162   0.02936   0.01953  -0.0186   0.9059   0.3928
  -5.000  -0.4877   0.02892   0.01897  -0.0191   0.8886   0.4050
  -4.750  -0.4567   0.02887   0.01897  -0.0192   0.8725   0.4144
  -4.500  -0.4337   0.02839   0.01831  -0.0187   0.8565   0.4270
  -4.250  -0.4055   0.02847   0.01849  -0.0179   0.8408   0.4354
  -4.000  -0.3854   0.02807   0.01795  -0.0170   0.8246   0.4478
  -3.750  -0.3588   0.02814   0.01809  -0.0159   0.8101   0.4562
  -3.500  -0.3375   0.02777   0.01758  -0.0148   0.7968   0.4688
  -3.250  -0.3123   0.02785   0.01774  -0.0136   0.7816   0.4773
  -3.000  -0.2911   0.02754   0.01731  -0.0126   0.7681   0.4898
  -2.750  -0.2654   0.02759   0.01741  -0.0112   0.7554   0.4986
  -2.500  -0.2439   0.02734   0.01707  -0.0104   0.7414   0.5111
  -2.250  -0.2181   0.02737   0.01713  -0.0090   0.7302   0.5201
  -2.000  -0.1961   0.02717   0.01687  -0.0082   0.7160   0.5326
  -1.750  -0.1706   0.02722   0.01696  -0.0069   0.7043   0.5417
  -1.500  -0.1479   0.02704   0.01671  -0.0060   0.6915   0.5544
  -1.250  -0.1226   0.02711   0.01683  -0.0048   0.6795   0.5638
  -1.000  -0.0992   0.02694   0.01659  -0.0039   0.6677   0.5765
  -0.750  -0.0738   0.02703   0.01674  -0.0029   0.6554   0.5862
  -0.500  -0.0496   0.02688   0.01652  -0.0020   0.6444   0.5988
  -0.250  -0.0246   0.02699   0.01669  -0.0010   0.6319   0.6089
   0.000   0.0000   0.02686   0.01650   0.0000   0.6214   0.6214
   0.250   0.0246   0.02699   0.01669   0.0010   0.6089   0.6319
   0.500   0.0495   0.02688   0.01652   0.0020   0.5988   0.6444
   0.750   0.0738   0.02703   0.01674   0.0029   0.5862   0.6554
   1.000   0.0992   0.02694   0.01659   0.0039   0.5765   0.6677
   1.250   0.1226   0.02711   0.01683   0.0048   0.5638   0.6795
   1.500   0.1478   0.02704   0.01671   0.0060   0.5545   0.6915
   1.750   0.1706   0.02722   0.01696   0.0069   0.5417   0.7043
   2.000   0.1961   0.02717   0.01687   0.0082   0.5326   0.7160
   2.250   0.2181   0.02737   0.01713   0.0090   0.5200   0.7302
   2.500   0.2439   0.02734   0.01707   0.0104   0.5111   0.7414
   2.750   0.2654   0.02759   0.01741   0.0112   0.4986   0.7554
   3.000   0.2911   0.02754   0.01731   0.0126   0.4898   0.7681
   3.250   0.3123   0.02785   0.01774   0.0136   0.4773   0.7816
   3.500   0.3375   0.02777   0.01758   0.0148   0.4688   0.7968
   3.750   0.3588   0.02814   0.01809   0.0159   0.4563   0.8102
   4.000   0.3854   0.02807   0.01795   0.0170   0.4478   0.8246
   4.250   0.4055   0.02847   0.01849   0.0179   0.4354   0.8408
   4.500   0.4337   0.02839   0.01832   0.0187   0.4270   0.8565
   4.750   0.4567   0.02888   0.01897   0.0192   0.4144   0.8726
   5.000   0.4877   0.02892   0.01897   0.0191   0.4050   0.8887
   5.250   0.5163   0.02936   0.01953   0.0186   0.3928   0.9059
   5.500   0.5509   0.02964   0.01981   0.0173   0.3820   0.9227
   5.750   0.5886   0.02994   0.02012   0.0154   0.3704   0.9395
   6.000   0.6269   0.03051   0.02077   0.0128   0.3579   0.9567
   6.250   0.6721   0.03057   0.02070   0.0099   0.3477   0.9723
   6.500   0.7102   0.03140   0.02170   0.0065   0.3343   0.9924
   6.750   0.7296   0.03168   0.02188   0.0071   0.3265   1.0000
   7.000   0.7292   0.03246   0.02273   0.0101   0.3182   1.0000
   7.250   0.7453   0.03269   0.02282   0.0118   0.3111   1.0000
   7.500   0.7535   0.03373   0.02393   0.0134   0.3023   1.0000
   7.750   0.7719   0.03422   0.02433   0.0144   0.2943   1.0000
   8.000   0.7856   0.03519   0.02532   0.0155   0.2862   1.0000
   8.250   0.8010   0.03602   0.02616   0.0165   0.2779   1.0000
   8.500   0.8194   0.03674   0.02682   0.0174   0.2706   1.0000
   8.750   0.8276   0.03813   0.02831   0.0185   0.2625   1.0000
   9.000   0.8554   0.03824   0.02822   0.0190   0.2559   1.0000
   9.250   0.8505   0.04050   0.03072   0.0205   0.2482   1.0000
   9.500   0.8683   0.04121   0.03138   0.0214   0.2416   1.0000
   9.750   0.8733   0.04281   0.03302   0.0226   0.2353   1.0000
  10.000   0.8654   0.04510   0.03543   0.0241   0.2292   1.0000
  10.250   0.8946   0.04507   0.03526   0.0247   0.2234   1.0000
  10.500   0.8679   0.04917   0.03956   0.0253   0.2182   1.0000
  10.750   0.8484   0.05335   0.04388   0.0248   0.2126   1.0000
  11.000   0.8936   0.05165   0.04198   0.0263   0.2074   1.0000
  11.250   0.7526   0.07120   0.06203   0.0169   0.1996   1.0000
  11.500   0.7627   0.07311   0.06393   0.0167   0.1948   1.0000
  11.750   0.8343   0.06642   0.05709   0.0217   0.1923   1.0000
  12.250   0.7139   0.09224   0.08315   0.0080   0.1770   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)