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

FX 78-K-140 A/20 (fx78k140a20-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 78-K-140 A/20 (fx78k140a20-il)
Reynolds number: 500,000
Max Cl/Cd: 118.88 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx78k140a20-il-500000.txt
Download as CSV file: xf-fx78k140a20-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1040   0.09327   0.08978  -0.1098   0.7499   0.0195
 -10.500  -0.1001   0.08949   0.08603  -0.1127   0.7489   0.0203
 -10.250  -0.0979   0.08564   0.08220  -0.1144   0.7480   0.0202
 -10.000  -0.0932   0.08216   0.07873  -0.1172   0.7471   0.0205
  -9.750  -0.0921   0.07820   0.07479  -0.1191   0.7461   0.0205
  -9.500  -0.0909   0.07461   0.07121  -0.1207   0.7452   0.0204
  -6.750  -0.1992   0.02798   0.02295  -0.1041   0.7315   0.0139
  -6.500  -0.1940   0.02426   0.01874  -0.1007   0.7306   0.0135
  -6.250  -0.1788   0.02195   0.01605  -0.0987   0.7298   0.0134
  -6.000  -0.1585   0.02051   0.01432  -0.0973   0.7289   0.0138
  -5.750  -0.1374   0.01946   0.01309  -0.0961   0.7273   0.0142
  -5.500  -0.1188   0.01739   0.01081  -0.0947   0.7258   0.0156
  -5.250  -0.0962   0.01685   0.01022  -0.0939   0.7244   0.0168
  -5.000  -0.0724   0.01652   0.00985  -0.0933   0.7230   0.0190
  -4.750  -0.0471   0.01643   0.00970  -0.0930   0.7218   0.0207
  -4.500  -0.0272   0.01535   0.00857  -0.0916   0.7206   0.0247
  -4.250  -0.0030   0.01501   0.00818  -0.0910   0.7195   0.0278
  -4.000   0.0198   0.01452   0.00763  -0.0902   0.7184   0.0332
  -3.750   0.0447   0.01428   0.00735  -0.0898   0.7176   0.0393
  -3.500   0.0684   0.01393   0.00700  -0.0891   0.7167   0.0485
  -3.250   0.0929   0.01367   0.00673  -0.0886   0.7159   0.0600
  -3.000   0.1170   0.01350   0.00657  -0.0881   0.7149   0.0760
  -2.750   0.1380   0.01338   0.00655  -0.0871   0.7128   0.0984
  -2.500   0.1582   0.01311   0.00654  -0.0860   0.7109   0.1573
  -2.250   0.1760   0.01260   0.00649  -0.0845   0.7092   0.2838
  -2.000   0.1894   0.01185   0.00636  -0.0821   0.7076   0.4650
  -1.750   0.1885   0.01083   0.00646  -0.0761   0.7061   0.7534
  -1.500   0.2092   0.01115   0.00685  -0.0740   0.7050   0.8420
  -1.250   0.2332   0.01134   0.00699  -0.0729   0.7040   0.8625
  -1.000   0.2593   0.01147   0.00706  -0.0723   0.7031   0.8741
  -0.750   0.2851   0.01156   0.00707  -0.0717   0.7023   0.8834
  -0.500   0.3101   0.01174   0.00721  -0.0709   0.7014   0.8942
  -0.250   0.3280   0.01206   0.00759  -0.0687   0.6986   0.9060
   0.000   0.3475   0.01227   0.00783  -0.0665   0.6963   0.9206
   0.250   0.3717   0.01237   0.00793  -0.0652   0.6946   0.9353
   0.500   0.4148   0.01249   0.00802  -0.0681   0.6935   0.9468
   0.750   0.4522   0.01250   0.00800  -0.0701   0.6923   0.9528
   1.000   0.4968   0.01247   0.00792  -0.0739   0.6913   0.9545
   1.250   0.5329   0.01237   0.00778  -0.0759   0.6902   0.9555
   1.500   0.5667   0.01226   0.00762  -0.0774   0.6892   0.9565
   1.750   0.5979   0.01217   0.00749  -0.0784   0.6882   0.9576
   2.000   0.6182   0.01225   0.00761  -0.0773   0.6855   0.9600
   2.250   0.6191   0.01225   0.00765  -0.0720   0.6821   0.9645
   2.500   0.6498   0.01222   0.00763  -0.0731   0.6802   0.9653
   2.750   0.6820   0.01211   0.00751  -0.0743   0.6786   0.9659
   3.000   0.7157   0.01196   0.00736  -0.0758   0.6772   0.9664
   3.250   0.7493   0.01184   0.00723  -0.0773   0.6759   0.9670
   3.500   0.7830   0.01174   0.00714  -0.0788   0.6748   0.9676
   3.750   0.8104   0.01176   0.00720  -0.0792   0.6723   0.9686
   4.000   0.8331   0.01182   0.00734  -0.0786   0.6686   0.9700
   4.250   0.8607   0.01175   0.00730  -0.0790   0.6662   0.9711
   4.500   0.8878   0.01163   0.00723  -0.0791   0.6643   0.9719
   4.750   0.9162   0.01146   0.00707  -0.0795   0.6626   0.9727
   5.000   0.9464   0.01129   0.00691  -0.0802   0.6609   0.9732
   5.250   0.9641   0.01135   0.00708  -0.0785   0.6570   0.9755
   5.500   0.9830   0.01129   0.00709  -0.0770   0.6534   0.9772
   5.750   1.0138   0.01118   0.00705  -0.0780   0.6507   0.9776
   6.000   1.0486   0.01063   0.00649  -0.0793   0.6458   0.9777
   6.250   1.0778   0.01004   0.00594  -0.0795   0.6342   0.9784
   6.500   1.1024   0.00961   0.00557  -0.0790   0.6119   0.9796
   6.750   1.1258   0.00947   0.00536  -0.0783   0.5773   0.9810
   7.000   1.1364   0.01005   0.00561  -0.0755   0.5100   0.9842
   7.250   1.1253   0.01196   0.00699  -0.0702   0.4118   0.9907
   7.500   1.1018   0.01372   0.00849  -0.0630   0.3580   1.0000
   7.750   1.0955   0.01586   0.01048  -0.0605   0.3202   1.0000
   8.000   1.0724   0.01922   0.01336  -0.0564   0.2382   1.0000
   8.250   1.0569   0.02212   0.01581  -0.0529   0.1593   1.0000
   8.500   1.0324   0.02568   0.01872  -0.0487   0.0548   1.0000
   8.750   1.0275   0.02806   0.02086  -0.0462   0.0172   1.0000
   9.000   1.0392   0.02930   0.02216  -0.0452   0.0132   1.0000
   9.250   1.0503   0.03059   0.02353  -0.0442   0.0123   1.0000
   9.500   1.0578   0.03216   0.02516  -0.0430   0.0110   1.0000
   9.750   1.0604   0.03413   0.02726  -0.0412   0.0103   1.0000
  10.000   1.0761   0.03516   0.02834  -0.0409   0.0109   1.0000
  10.250   1.0743   0.03764   0.03093  -0.0389   0.0097   1.0000
  10.500   1.0808   0.03946   0.03283  -0.0377   0.0096   1.0000
  10.750   1.0878   0.04125   0.03470  -0.0365   0.0094   1.0000
  11.000   1.1006   0.04256   0.03605  -0.0361   0.0086   1.0000
  11.250   1.1065   0.04441   0.03800  -0.0347   0.0088   1.0000
  11.500   1.1190   0.04579   0.03938  -0.0343   0.0076   1.0000
  11.750   1.1262   0.04754   0.04121  -0.0330   0.0076   1.0000
  12.000   1.1351   0.04913   0.04288  -0.0317   0.0075   1.0000
  12.250   1.1466   0.05042   0.04426  -0.0302   0.0076   1.0000
<< Back to FX 78-K-140 A/20 (fx78k140a20-il)

Polar data table (+)

Polar graphs


<< Back to FX 78-K-140 A/20 (fx78k140a20-il)