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Joukovsky f=0% t=15% (joukowsk0015-jf) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: Joukovsky f=0% t=15% (joukowsk0015-jf)
Reynolds number: 50,000
Max Cl/Cd: 25.64 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk0015-jf-50000-n5.txt
Download as CSV file: xf-joukowsk0015-jf-50000-n5.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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.7070   0.12435   0.11594   0.0146   1.0000   0.1167
 -13.000  -0.7106   0.11897   0.11055   0.0120   1.0000   0.1201
 -12.750  -0.8741   0.08159   0.07299  -0.0119   1.0000   0.1250
 -12.500  -0.7693   0.09735   0.08893   0.0001   1.0000   0.1281
 -12.250  -0.8314   0.08153   0.07304  -0.0095   1.0000   0.1322
 -12.000  -0.9213   0.06454   0.05569  -0.0203   1.0000   0.1334
 -11.750  -0.9568   0.05755   0.04842  -0.0235   1.0000   0.1355
 -11.500  -0.9848   0.05237   0.04290  -0.0247   1.0000   0.1380
 -11.250  -0.9622   0.05175   0.04243  -0.0239   1.0000   0.1424
 -11.000  -0.9645   0.04923   0.03980  -0.0235   1.0000   0.1465
 -10.750  -0.9761   0.04623   0.03651  -0.0224   1.0000   0.1507
 -10.500  -0.9612   0.04504   0.03540  -0.0215   1.0000   0.1557
 -10.250  -0.9536   0.04329   0.03355  -0.0207   1.0000   0.1613
 -10.000  -0.9469   0.04135   0.03144  -0.0197   1.0000   0.1674
  -9.750  -0.9308   0.04026   0.03039  -0.0189   1.0000   0.1739
  -9.500  -0.9220   0.03843   0.02833  -0.0180   1.0000   0.1814
  -9.250  -0.9031   0.03756   0.02757  -0.0172   1.0000   0.1886
  -9.000  -0.8902   0.03603   0.02585  -0.0164   1.0000   0.1972
  -8.750  -0.8709   0.03518   0.02509  -0.0156   1.0000   0.2055
  -8.500  -0.8544   0.03398   0.02380  -0.0148   1.0000   0.2149
  -8.250  -0.8359   0.03304   0.02284  -0.0140   1.0000   0.2248
  -8.000  -0.8163   0.03217   0.02199  -0.0133   1.0000   0.2347
  -7.750  -0.7983   0.03113   0.02084  -0.0125   1.0000   0.2462
  -7.500  -0.7771   0.03046   0.02025  -0.0117   1.0000   0.2569
  -7.250  -0.7566   0.02971   0.01951  -0.0110   1.0000   0.2684
  -7.000  -0.7367   0.02888   0.01862  -0.0103   1.0000   0.2810
  -6.750  -0.7154   0.02828   0.01807  -0.0095   1.0000   0.2934
  -6.500  -0.6939   0.02771   0.01755  -0.0087   1.0000   0.3055
  -6.250  -0.6732   0.02709   0.01693  -0.0079   1.0000   0.3187
  -6.000  -0.6533   0.02646   0.01626  -0.0070   1.0000   0.3327
  -5.750  -0.6323   0.02608   0.01601  -0.0060   1.0000   0.3449
  -5.500  -0.6132   0.02563   0.01561  -0.0048   1.0000   0.3577
  -5.250  -0.5966   0.02516   0.01515  -0.0034   1.0000   0.3712
  -5.000  -0.5816   0.02482   0.01486  -0.0016   1.0000   0.3838
  -4.750  -0.5679   0.02455   0.01467   0.0003   1.0000   0.3956
  -4.500  -0.5437   0.02426   0.01440   0.0002   0.9917   0.4102
  -4.250  -0.5006   0.02406   0.01420  -0.0030   0.9730   0.4283
  -4.000  -0.4568   0.02387   0.01401  -0.0062   0.9562   0.4463
  -3.750  -0.4147   0.02370   0.01384  -0.0088   0.9391   0.4640
  -3.500  -0.3753   0.02354   0.01367  -0.0109   0.9218   0.4814
  -3.250  -0.3390   0.02346   0.01359  -0.0121   0.9038   0.4973
  -3.000  -0.3059   0.02340   0.01356  -0.0126   0.8857   0.5121
  -2.750  -0.2755   0.02333   0.01348  -0.0125   0.8676   0.5270
  -2.500  -0.2473   0.02324   0.01337  -0.0121   0.8499   0.5423
  -2.250  -0.2213   0.02315   0.01323  -0.0113   0.8320   0.5579
  -2.000  -0.1957   0.02315   0.01326  -0.0101   0.8145   0.5714
  -1.750  -0.1707   0.02313   0.01323  -0.0090   0.7973   0.5853
  -1.500  -0.1461   0.02308   0.01316  -0.0078   0.7807   0.6003
  -1.250  -0.1217   0.02302   0.01305  -0.0067   0.7645   0.6159
  -1.000  -0.0967   0.02303   0.01309  -0.0053   0.7492   0.6291
  -0.750  -0.0723   0.02300   0.01304  -0.0038   0.7345   0.6433
  -0.500  -0.0484   0.02299   0.01302  -0.0027   0.7182   0.6586
  -0.250  -0.0244   0.02298   0.01299  -0.0015   0.7026   0.6741
   0.000   0.0000   0.02300   0.01304   0.0000   0.6878   0.6878
   0.250   0.0244   0.02298   0.01299   0.0015   0.6741   0.7026
   0.500   0.0484   0.02299   0.01302   0.0027   0.6586   0.7182
   0.750   0.0723   0.02300   0.01304   0.0038   0.6433   0.7345
   1.000   0.0967   0.02303   0.01309   0.0053   0.6291   0.7492
   1.250   0.1217   0.02302   0.01305   0.0067   0.6159   0.7645
   1.500   0.1461   0.02308   0.01316   0.0078   0.6002   0.7807
   1.750   0.1707   0.02313   0.01323   0.0090   0.5854   0.7973
   2.000   0.1957   0.02315   0.01326   0.0101   0.5714   0.8145
   2.250   0.2213   0.02315   0.01323   0.0113   0.5579   0.8320
   2.500   0.2474   0.02324   0.01337   0.0121   0.5423   0.8499
   2.750   0.2755   0.02332   0.01348   0.0125   0.5270   0.8677
   3.000   0.3059   0.02340   0.01356   0.0126   0.5122   0.8857
   3.250   0.3390   0.02345   0.01359   0.0121   0.4973   0.9039
   3.500   0.3753   0.02354   0.01367   0.0109   0.4814   0.9218
   3.750   0.4148   0.02370   0.01384   0.0088   0.4640   0.9391
   4.000   0.4569   0.02387   0.01401   0.0062   0.4463   0.9562
   4.250   0.5007   0.02406   0.01420   0.0030   0.4282   0.9731
   4.500   0.5438   0.02426   0.01439  -0.0002   0.4102   0.9918
   4.750   0.5679   0.02455   0.01467  -0.0003   0.3956   1.0000
   5.000   0.5816   0.02482   0.01486   0.0016   0.3838   1.0000
   5.250   0.5966   0.02516   0.01515   0.0034   0.3712   1.0000
   5.500   0.6132   0.02563   0.01561   0.0048   0.3577   1.0000
   5.750   0.6323   0.02608   0.01601   0.0060   0.3449   1.0000
   6.000   0.6533   0.02646   0.01626   0.0070   0.3327   1.0000
   6.250   0.6732   0.02709   0.01693   0.0079   0.3187   1.0000
   6.500   0.6939   0.02771   0.01755   0.0087   0.3055   1.0000
   6.750   0.7154   0.02828   0.01807   0.0095   0.2933   1.0000
   7.000   0.7367   0.02888   0.01862   0.0103   0.2811   1.0000
   7.250   0.7566   0.02971   0.01951   0.0110   0.2684   1.0000
   7.500   0.7771   0.03046   0.02025   0.0117   0.2569   1.0000
   7.750   0.7983   0.03113   0.02084   0.0125   0.2462   1.0000
   8.000   0.8163   0.03217   0.02199   0.0132   0.2346   1.0000
   8.250   0.8360   0.03304   0.02284   0.0140   0.2248   1.0000
   8.500   0.8545   0.03398   0.02380   0.0148   0.2149   1.0000
   8.750   0.8711   0.03518   0.02509   0.0156   0.2055   1.0000
   9.000   0.8904   0.03603   0.02586   0.0164   0.1972   1.0000
   9.250   0.9032   0.03755   0.02757   0.0172   0.1886   1.0000
   9.500   0.9222   0.03843   0.02833   0.0180   0.1814   1.0000
   9.750   0.9310   0.04026   0.03039   0.0189   0.1738   1.0000
  10.000   0.9472   0.04134   0.03143   0.0197   0.1674   1.0000
  10.250   0.9539   0.04329   0.03355   0.0206   0.1613   1.0000
  10.500   0.9615   0.04502   0.03538   0.0215   0.1556   1.0000
  10.750   0.9762   0.04625   0.03652   0.0223   0.1506   1.0000
  11.000   0.9649   0.04923   0.03979   0.0234   0.1464   1.0000
  11.250   0.9631   0.05172   0.04240   0.0239   0.1423   1.0000
  11.500   0.9849   0.05242   0.04293   0.0246   0.1379   1.0000
  11.750   0.9570   0.05761   0.04847   0.0234   0.1354   1.0000
  12.000   0.9219   0.06457   0.05571   0.0202   0.1333   1.0000
  12.250   0.8338   0.08129   0.07279   0.0096   0.1321   1.0000
  12.500   0.7736   0.09670   0.08828   0.0002   0.1280   1.0000
  12.750   0.8722   0.08208   0.07349   0.0114   0.1250   1.0000
  13.000   0.7117   0.11903   0.11061  -0.0122   0.1199   1.0000
  13.250   0.7087   0.12430   0.11588  -0.0147   0.1166   1.0000
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