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FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-140 A/20 (fx78k140a20-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.4 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k140a20-il-1000000.txt
Download as CSV file: xf-fx78k140a20-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-140 A/20                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3442   0.02721   0.02331  -0.1127   0.7166   0.0067
  -8.500  -0.3444   0.02426   0.01998  -0.1091   0.7153   0.0066
  -8.250  -0.3271   0.02340   0.01898  -0.1078   0.7145   0.0064
  -8.000  -0.3285   0.01986   0.01497  -0.1036   0.7137   0.0067
  -7.750  -0.3117   0.01858   0.01349  -0.1021   0.7128   0.0066
  -7.500  -0.2923   0.01780   0.01263  -0.1010   0.7118   0.0072
  -7.250  -0.2715   0.01703   0.01175  -0.1001   0.7108   0.0074
  -7.000  -0.2514   0.01588   0.01040  -0.0989   0.7098   0.0075
  -6.750  -0.2301   0.01491   0.00927  -0.0979   0.7087   0.0077
  -6.500  -0.2076   0.01413   0.00837  -0.0970   0.7076   0.0082
  -6.250  -0.1850   0.01341   0.00754  -0.0962   0.7066   0.0084
  -6.000  -0.1614   0.01288   0.00691  -0.0956   0.7058   0.0091
  -5.750  -0.1368   0.01249   0.00646  -0.0951   0.7049   0.0095
  -5.500  -0.1162   0.01166   0.00548  -0.0939   0.7039   0.0106
  -5.250  -0.0918   0.01132   0.00511  -0.0934   0.7029   0.0118
  -5.000  -0.0661   0.01118   0.00494  -0.0931   0.7016   0.0135
  -4.750  -0.0413   0.01095   0.00468  -0.0927   0.7007   0.0145
  -4.500  -0.0180   0.01055   0.00427  -0.0920   0.6999   0.0183
  -4.250   0.0077   0.01041   0.00412  -0.0918   0.6990   0.0203
  -4.000   0.0317   0.01008   0.00378  -0.0911   0.6979   0.0254
  -3.750   0.0577   0.00997   0.00367  -0.0910   0.6968   0.0295
  -3.500   0.0823   0.00970   0.00343  -0.0905   0.6956   0.0393
  -3.250   0.1078   0.00952   0.00327  -0.0902   0.6946   0.0490
  -3.000   0.1335   0.00936   0.00314  -0.0899   0.6935   0.0619
  -2.750   0.1593   0.00920   0.00301  -0.0897   0.6924   0.0770
  -2.500   0.1845   0.00899   0.00288  -0.0894   0.6914   0.1056
  -2.250   0.2085   0.00872   0.00278  -0.0889   0.6904   0.1599
  -2.000   0.2304   0.00834   0.00269  -0.0881   0.6893   0.2554
  -1.750   0.2506   0.00796   0.00265  -0.0869   0.6881   0.3717
  -1.500   0.2634   0.00731   0.00258  -0.0842   0.6869   0.5520
  -1.250   0.2647   0.00657   0.00268  -0.0785   0.6857   0.7898
  -1.000   0.2885   0.00670   0.00285  -0.0775   0.6844   0.8351
  -0.750   0.3145   0.00678   0.00290  -0.0772   0.6831   0.8460
  -0.500   0.3403   0.00686   0.00294  -0.0768   0.6818   0.8545
  -0.250   0.3679   0.00692   0.00300  -0.0768   0.6806   0.8602
   0.000   0.3938   0.00701   0.00306  -0.0764   0.6793   0.8692
   0.250   0.4204   0.00714   0.00320  -0.0760   0.6781   0.8797
   0.500   0.4476   0.00726   0.00333  -0.0757   0.6770   0.8897
   0.750   0.4738   0.00734   0.00341  -0.0753   0.6757   0.8978
   1.000   0.5006   0.00750   0.00356  -0.0750   0.6739   0.9057
   1.250   0.5248   0.00749   0.00357  -0.0743   0.6723   0.9107
   1.500   0.5508   0.00745   0.00355  -0.0739   0.6705   0.9138
   1.750   0.5774   0.00743   0.00354  -0.0739   0.6687   0.9153
   2.000   0.6045   0.00740   0.00350  -0.0740   0.6669   0.9163
   2.250   0.6320   0.00736   0.00345  -0.0742   0.6651   0.9173
   2.500   0.6596   0.00732   0.00340  -0.0743   0.6633   0.9185
   2.750   0.6870   0.00732   0.00339  -0.0745   0.6616   0.9198
   3.000   0.7139   0.00736   0.00342  -0.0746   0.6597   0.9209
   3.250   0.7392   0.00733   0.00343  -0.0744   0.6575   0.9216
   3.500   0.7654   0.00731   0.00344  -0.0743   0.6553   0.9221
   3.750   0.7921   0.00729   0.00345  -0.0744   0.6531   0.9225
   4.000   0.8191   0.00727   0.00343  -0.0745   0.6509   0.9230
   4.250   0.8463   0.00724   0.00340  -0.0746   0.6483   0.9235
   4.500   0.8731   0.00725   0.00342  -0.0747   0.6459   0.9240
   4.750   0.8982   0.00722   0.00348  -0.0744   0.6433   0.9246
   5.000   0.9242   0.00721   0.00350  -0.0743   0.6403   0.9251
   5.250   0.9507   0.00718   0.00351  -0.0743   0.6372   0.9256
   5.500   0.9761   0.00712   0.00346  -0.0741   0.6313   0.9261
   5.750   0.9986   0.00700   0.00335  -0.0731   0.6194   0.9268
   6.000   1.0205   0.00698   0.00335  -0.0721   0.6052   0.9275
   6.250   1.0392   0.00705   0.00339  -0.0704   0.5802   0.9286
   6.500   1.0468   0.00746   0.00360  -0.0666   0.5345   0.9302
   6.750   1.0388   0.00837   0.00419  -0.0599   0.4666   0.9325
   7.000   1.0302   0.00944   0.00498  -0.0536   0.4072   0.9349
   7.250   1.0223   0.01161   0.00670  -0.0497   0.3164   0.9370
   7.500   1.0230   0.01574   0.01024  -0.0522   0.1966   0.9391
   7.750   1.0342   0.01780   0.01203  -0.0530   0.1394   0.9402
   8.000   1.0282   0.02071   0.01445  -0.0515   0.0519   0.9420
   8.250   1.0321   0.02260   0.01614  -0.0502   0.0132   0.9437
   8.500   1.0462   0.02372   0.01730  -0.0496   0.0092   0.9451
   8.750   1.0618   0.02470   0.01833  -0.0491   0.0084   0.9464
   9.000   1.0707   0.02616   0.01986  -0.0479   0.0063   0.9478
   9.250   1.0826   0.02738   0.02116  -0.0471   0.0064   0.9492
   9.500   1.0962   0.02848   0.02233  -0.0464   0.0061   0.9505
   9.750   1.1111   0.02953   0.02343  -0.0460   0.0057   0.9521
  10.000   1.1267   0.03053   0.02447  -0.0457   0.0057   0.9541
  10.250   1.1328   0.03228   0.02633  -0.0444   0.0053   0.9567
  10.500   1.1464   0.03353   0.02762  -0.0441   0.0050   0.9594
  10.750   1.1563   0.03513   0.02930  -0.0434   0.0049   0.9628
  11.000   1.1687   0.03661   0.03084  -0.0432   0.0046   0.9678
  11.250   1.1792   0.03842   0.03273  -0.0429   0.0047   0.9748
  11.500   1.1822   0.04112   0.03554  -0.0417   0.0039   1.0000
  11.750   1.1855   0.04320   0.03769  -0.0403   0.0040   1.0000
  12.000   1.1936   0.04490   0.03946  -0.0393   0.0039   1.0000
  12.250   1.1988   0.04673   0.04136  -0.0376   0.0040   1.0000
  12.500   1.2130   0.04805   0.04276  -0.0374   0.0037   1.0000
  12.750   1.2197   0.04966   0.04444  -0.0355   0.0039   1.0000
  13.000   1.2307   0.05130   0.04618  -0.0349   0.0033   1.0000
  13.250   1.2409   0.05282   0.04780  -0.0338   0.0035   1.0000
  13.500   1.2509   0.05443   0.04954  -0.0322   0.0035   1.0000
  13.750   1.2605   0.05630   0.05159  -0.0299   0.0036   1.0000
  14.000   1.0653   0.05376   0.04955  -0.0123   0.0035   1.0000
  14.250   1.0681   0.05650   0.05240  -0.0110   0.0036   1.0000
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