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=15% (joukowsk0015-jf) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf)
Reynolds number: 200,000
Max Cl/Cd: 49.73 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-joukowsk0015-jf-200000.txt
Download as CSV file: xf-joukowsk0015-jf-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Joukovsky f=0% t=15%                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.750  -1.0499   0.12163   0.11721   0.0117   1.0000   0.0592
 -17.500  -1.1340   0.10113   0.09629  -0.0026   1.0000   0.0587
 -17.250  -1.1782   0.08973   0.08457  -0.0103   1.0000   0.0588
 -17.000  -1.2103   0.08123   0.07578  -0.0159   1.0000   0.0590
 -16.750  -1.2383   0.07406   0.06832  -0.0203   1.0000   0.0593
 -16.500  -1.2295   0.07168   0.06597  -0.0205   1.0000   0.0604
 -16.250  -1.2216   0.06951   0.06382  -0.0211   1.0000   0.0616
 -16.000  -1.2261   0.06582   0.06003  -0.0228   1.0000   0.0626
 -15.750  -1.2343   0.06179   0.05584  -0.0246   1.0000   0.0634
 -15.500  -1.2427   0.05790   0.05176  -0.0262   1.0000   0.0644
 -15.250  -1.2517   0.05416   0.04781  -0.0275   1.0000   0.0654
 -15.000  -1.2616   0.05062   0.04402  -0.0286   1.0000   0.0662
 -14.750  -1.2487   0.04881   0.04226  -0.0283   1.0000   0.0678
 -14.500  -1.2396   0.04708   0.04055  -0.0283   1.0000   0.0694
 -14.250  -1.2365   0.04491   0.03830  -0.0284   1.0000   0.0709
 -14.000  -1.2365   0.04258   0.03580  -0.0284   1.0000   0.0724
 -13.750  -1.2388   0.04028   0.03327  -0.0282   1.0000   0.0739
 -13.500  -1.2243   0.03869   0.03174  -0.0277   1.0000   0.0759
 -13.250  -1.2139   0.03728   0.03035  -0.0271   1.0000   0.0778
 -13.000  -1.2076   0.03575   0.02872  -0.0265   1.0000   0.0799
 -12.750  -1.2040   0.03418   0.02697  -0.0254   1.0000   0.0819
 -12.500  -1.1914   0.03271   0.02551  -0.0246   1.0000   0.0843
 -12.250  -1.1800   0.03158   0.02442  -0.0236   1.0000   0.0867
 -12.000  -1.1711   0.03046   0.02321  -0.0222   1.0000   0.0895
 -11.750  -1.1649   0.02943   0.02198  -0.0203   1.0000   0.0920
 -11.500  -1.1485   0.02823   0.02093  -0.0194   1.0000   0.0953
 -11.250  -1.1345   0.02735   0.02001  -0.0181   1.0000   0.0988
 -11.000  -1.1198   0.02643   0.01894  -0.0169   1.0000   0.1026
 -10.750  -1.1023   0.02540   0.01803  -0.0161   1.0000   0.1065
 -10.500  -1.0846   0.02463   0.01719  -0.0151   1.0000   0.1112
 -10.250  -1.0662   0.02366   0.01623  -0.0142   1.0000   0.1159
 -10.000  -1.0469   0.02293   0.01551  -0.0134   1.0000   0.1212
  -9.750  -1.0269   0.02212   0.01465  -0.0127   1.0000   0.1270
  -9.500  -1.0065   0.02140   0.01399  -0.0119   1.0000   0.1330
  -9.250  -0.9853   0.02068   0.01322  -0.0113   1.0000   0.1399
  -9.000  -0.9637   0.02002   0.01262  -0.0106   1.0000   0.1470
  -8.750  -0.9416   0.01934   0.01195  -0.0100   1.0000   0.1549
  -8.500  -0.9186   0.01880   0.01140  -0.0095   1.0000   0.1635
  -8.250  -0.8959   0.01815   0.01083  -0.0090   1.0000   0.1722
  -8.000  -0.8720   0.01765   0.01029  -0.0086   1.0000   0.1821
  -7.750  -0.8484   0.01711   0.00983  -0.0081   1.0000   0.1922
  -7.500  -0.8246   0.01658   0.00937  -0.0077   1.0000   0.2027
  -7.250  -0.8000   0.01615   0.00893  -0.0073   1.0000   0.2142
  -7.000  -0.7757   0.01573   0.00856  -0.0069   1.0000   0.2261
  -6.750  -0.7519   0.01529   0.00822  -0.0065   1.0000   0.2378
  -6.500  -0.7289   0.01491   0.00790  -0.0059   1.0000   0.2501
  -6.250  -0.7090   0.01465   0.00763  -0.0048   1.0000   0.2624
  -6.000  -0.6910   0.01433   0.00743  -0.0037   0.9977   0.2739
  -5.750  -0.6449   0.01401   0.00717  -0.0075   0.9846   0.2913
  -5.500  -0.6008   0.01372   0.00694  -0.0109   0.9704   0.3084
  -5.250  -0.5597   0.01346   0.00673  -0.0134   0.9545   0.3250
  -5.000  -0.5255   0.01327   0.00656  -0.0145   0.9355   0.3404
  -4.750  -0.4985   0.01314   0.00642  -0.0139   0.9144   0.3548
  -4.500  -0.4744   0.01307   0.00629  -0.0127   0.8943   0.3692
  -4.250  -0.4514   0.01294   0.00620  -0.0113   0.8755   0.3824
  -4.000  -0.4277   0.01282   0.00609  -0.0100   0.8578   0.3958
  -3.750  -0.4033   0.01273   0.00596  -0.0089   0.8408   0.4098
  -3.500  -0.3783   0.01267   0.00583  -0.0079   0.8248   0.4244
  -3.250  -0.3532   0.01256   0.00575  -0.0069   0.8093   0.4379
  -3.000  -0.3274   0.01246   0.00565  -0.0061   0.7940   0.4515
  -2.750  -0.3008   0.01238   0.00554  -0.0055   0.7781   0.4659
  -2.500  -0.2739   0.01234   0.00545  -0.0049   0.7629   0.4807
  -2.250  -0.2473   0.01225   0.00539  -0.0043   0.7486   0.4942
  -2.000  -0.2206   0.01219   0.00531  -0.0036   0.7347   0.5078
  -1.750  -0.1930   0.01213   0.00525  -0.0032   0.7193   0.5223
  -1.500  -0.1655   0.01211   0.00519  -0.0027   0.7048   0.5369
  -1.250  -0.1384   0.01206   0.00516  -0.0022   0.6912   0.5502
  -1.000  -0.1109   0.01202   0.00511  -0.0017   0.6770   0.5640
  -0.750  -0.0829   0.01200   0.00508  -0.0013   0.6622   0.5787
  -0.500  -0.0553   0.01199   0.00507  -0.0009   0.6483   0.5926
  -0.250  -0.0280   0.01199   0.00505  -0.0003   0.6353   0.6060
   0.000   0.0000   0.01196   0.00505   0.0000   0.6202   0.6202
   0.250   0.0280   0.01199   0.00505   0.0003   0.6060   0.6353
   0.500   0.0553   0.01199   0.00507   0.0009   0.5926   0.6483
   0.750   0.0829   0.01200   0.00508   0.0013   0.5787   0.6622
   1.000   0.1109   0.01202   0.00511   0.0017   0.5640   0.6770
   1.250   0.1384   0.01206   0.00516   0.0022   0.5502   0.6912
   1.500   0.1655   0.01211   0.00519   0.0027   0.5369   0.7048
   1.750   0.1930   0.01213   0.00525   0.0032   0.5223   0.7193
   2.000   0.2206   0.01219   0.00531   0.0036   0.5078   0.7347
   2.250   0.2473   0.01225   0.00539   0.0043   0.4942   0.7486
   2.500   0.2739   0.01234   0.00545   0.0049   0.4807   0.7629
   2.750   0.3008   0.01238   0.00554   0.0055   0.4659   0.7781
   3.000   0.3274   0.01246   0.00565   0.0061   0.4515   0.7940
   3.250   0.3532   0.01256   0.00575   0.0069   0.4379   0.8094
   3.500   0.3783   0.01267   0.00583   0.0079   0.4244   0.8248
   3.750   0.4033   0.01273   0.00596   0.0089   0.4098   0.8408
   4.000   0.4277   0.01282   0.00609   0.0100   0.3958   0.8578
   4.250   0.4514   0.01294   0.00620   0.0113   0.3824   0.8755
   4.500   0.4744   0.01307   0.00629   0.0127   0.3692   0.8943
   4.750   0.4985   0.01314   0.00642   0.0139   0.3548   0.9144
   5.000   0.5255   0.01327   0.00656   0.0145   0.3404   0.9355
   5.250   0.5597   0.01346   0.00673   0.0134   0.3251   0.9545
   5.500   0.6009   0.01372   0.00693   0.0109   0.3083   0.9704
   5.750   0.6450   0.01401   0.00717   0.0075   0.2912   0.9846
   6.000   0.6910   0.01433   0.00743   0.0037   0.2739   0.9977
   6.250   0.7091   0.01465   0.00763   0.0048   0.2624   1.0000
   6.500   0.7289   0.01491   0.00790   0.0059   0.2501   1.0000
   6.750   0.7520   0.01529   0.00822   0.0065   0.2378   1.0000
   7.000   0.7757   0.01573   0.00856   0.0069   0.2261   1.0000
   7.250   0.8000   0.01615   0.00893   0.0073   0.2142   1.0000
   7.500   0.8246   0.01658   0.00937   0.0077   0.2027   1.0000
   7.750   0.8485   0.01711   0.00983   0.0081   0.1922   1.0000
   8.000   0.8720   0.01765   0.01029   0.0086   0.1821   1.0000
   8.250   0.8960   0.01814   0.01082   0.0090   0.1722   1.0000
   8.500   0.9186   0.01880   0.01140   0.0095   0.1635   1.0000
   8.750   0.9416   0.01933   0.01195   0.0100   0.1549   1.0000
   9.000   0.9638   0.02002   0.01262   0.0106   0.1470   1.0000
   9.250   0.9853   0.02068   0.01322   0.0112   0.1399   1.0000
   9.500   1.0066   0.02140   0.01399   0.0119   0.1330   1.0000
   9.750   1.0270   0.02212   0.01465   0.0126   0.1269   1.0000
  10.000   1.0469   0.02293   0.01551   0.0134   0.1211   1.0000
  10.250   1.0662   0.02365   0.01623   0.0142   0.1159   1.0000
  10.500   1.0846   0.02463   0.01719   0.0151   0.1112   1.0000
  10.750   1.1023   0.02540   0.01802   0.0161   0.1065   1.0000
  11.000   1.1198   0.02643   0.01894   0.0169   0.1025   1.0000
  11.250   1.1346   0.02735   0.02001   0.0181   0.0988   1.0000
  11.500   1.1486   0.02823   0.02093   0.0193   0.0953   1.0000
  11.750   1.1653   0.02944   0.02198   0.0202   0.0920   1.0000
  12.000   1.1714   0.03046   0.02321   0.0222   0.0895   1.0000
  12.250   1.1803   0.03158   0.02441   0.0236   0.0868   1.0000
  12.500   1.1917   0.03271   0.02550   0.0246   0.0843   1.0000
  12.750   1.2043   0.03417   0.02696   0.0254   0.0819   1.0000
  13.000   1.2077   0.03574   0.02872   0.0264   0.0798   1.0000
  13.250   1.2143   0.03727   0.03033   0.0271   0.0777   1.0000
  13.500   1.2249   0.03866   0.03170   0.0276   0.0758   1.0000
  13.750   1.2389   0.04029   0.03328   0.0281   0.0738   1.0000
  14.000   1.2373   0.04255   0.03576   0.0284   0.0725   1.0000
  14.250   1.2373   0.04489   0.03827   0.0284   0.0709   1.0000
  14.500   1.2406   0.04705   0.04051   0.0282   0.0694   1.0000
  14.750   1.2498   0.04879   0.04224   0.0282   0.0679   1.0000
  15.000   1.2627   0.05061   0.04401   0.0285   0.0662   1.0000
  15.250   1.2525   0.05416   0.04781   0.0274   0.0653   1.0000
  15.500   1.2440   0.05787   0.05173   0.0261   0.0644   1.0000
  15.750   1.2354   0.06177   0.05582   0.0245   0.0634   1.0000
  16.000   1.2276   0.06577   0.05997   0.0227   0.0625   1.0000
  16.250   1.2232   0.06946   0.06377   0.0210   0.0616   1.0000
  16.500   1.2334   0.07135   0.06561   0.0206   0.0603   1.0000
  16.750   1.2375   0.07430   0.06857   0.0199   0.0593   1.0000
  17.000   1.2104   0.08137   0.07592   0.0155   0.0589   1.0000
  17.250   1.1782   0.08994   0.08478   0.0099   0.0587   1.0000
  17.500   1.1327   0.10160   0.09677   0.0020   0.0587   1.0000
  17.750   1.0428   0.12346   0.11907  -0.0132   0.0593   1.0000
<< Back to Joukovsky f=0% t=15% (joukowsk0015-jf)

Polar data table (+)

Polar graphs


<< Back to Joukovsky f=0% t=15% (joukowsk0015-jf)