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WORTMANN FX 77-080 (fx77080-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 77-080 (fx77080-il)
Reynolds number: 100,000
Max Cl/Cd: 33.2 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx77080-il-100000-n5.txt
Download as CSV file: xf-fx77080-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 77-080                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.7839   0.07482   0.06953  -0.0173   1.0000   0.0278
 -10.750  -0.8016   0.06747   0.06212  -0.0233   1.0000   0.0273
 -10.500  -0.8246   0.06121   0.05573  -0.0274   1.0000   0.0268
 -10.250  -0.8489   0.05647   0.05077  -0.0278   1.0000   0.0269
 -10.000  -0.8680   0.05231   0.04631  -0.0264   1.0000   0.0272
  -9.750  -0.8784   0.04826   0.04186  -0.0248   1.0000   0.0275
  -9.500  -0.8837   0.04447   0.03752  -0.0228   1.0000   0.0281
  -9.250  -0.8796   0.04118   0.03402  -0.0213   1.0000   0.0288
  -9.000  -0.8704   0.03862   0.03124  -0.0198   1.0000   0.0296
  -8.750  -0.8589   0.03627   0.02863  -0.0183   1.0000   0.0305
  -8.500  -0.8454   0.03405   0.02607  -0.0168   1.0000   0.0315
  -8.250  -0.8300   0.03209   0.02381  -0.0153   1.0000   0.0333
  -8.000  -0.8129   0.03031   0.02164  -0.0139   1.0000   0.0359
  -7.750  -0.7953   0.02831   0.01940  -0.0125   1.0000   0.0378
  -7.500  -0.7768   0.02676   0.01778  -0.0113   1.0000   0.0397
  -7.250  -0.7572   0.02545   0.01633  -0.0100   1.0000   0.0425
  -7.000  -0.7366   0.02428   0.01490  -0.0087   1.0000   0.0463
  -6.750  -0.7175   0.02300   0.01358  -0.0074   1.0000   0.0502
  -6.500  -0.6973   0.02195   0.01245  -0.0061   1.0000   0.0545
  -6.250  -0.6770   0.02095   0.01136  -0.0048   1.0000   0.0608
  -6.000  -0.6563   0.02011   0.01049  -0.0035   1.0000   0.0688
  -5.750  -0.6359   0.01926   0.00963  -0.0022   1.0000   0.0785
  -5.500  -0.6148   0.01853   0.00892  -0.0010   1.0000   0.0930
  -5.250  -0.5934   0.01788   0.00825   0.0003   1.0000   0.1095
  -5.000  -0.5719   0.01730   0.00772   0.0014   1.0000   0.1287
  -4.750  -0.5502   0.01678   0.00720   0.0025   1.0000   0.1481
  -4.500  -0.5282   0.01633   0.00673   0.0036   1.0000   0.1690
  -4.250  -0.5067   0.01582   0.00633   0.0048   1.0000   0.1908
  -4.000  -0.4850   0.01537   0.00592   0.0059   1.0000   0.2145
  -3.750  -0.4636   0.01489   0.00555   0.0071   1.0000   0.2408
  -3.500  -0.4423   0.01442   0.00519   0.0083   1.0000   0.2721
  -3.250  -0.4214   0.01393   0.00489   0.0097   1.0000   0.3116
  -3.000  -0.4008   0.01346   0.00462   0.0110   1.0000   0.3616
  -2.750  -0.3805   0.01298   0.00441   0.0125   1.0000   0.4226
  -2.500  -0.3605   0.01251   0.00423   0.0142   1.0000   0.4927
  -2.250  -0.3399   0.01208   0.00413   0.0158   1.0000   0.5725
  -2.000  -0.3172   0.01171   0.00409   0.0173   1.0000   0.6548
  -1.750  -0.2922   0.01147   0.00413   0.0185   1.0000   0.7375
  -1.500  -0.2608   0.01137   0.00420   0.0185   1.0000   0.8119
  -1.250  -0.2187   0.01141   0.00431   0.0163   1.0000   0.8755
  -1.000  -0.1713   0.01150   0.00439   0.0128   1.0000   0.9204
  -0.750  -0.1175   0.01159   0.00443   0.0078   1.0000   0.9549
  -0.500  -0.0602   0.01165   0.00445   0.0019   1.0000   0.9829
  -0.250  -0.0117   0.01168   0.00444  -0.0026   1.0000   1.0000
   0.000   0.0000   0.01166   0.00442   0.0000   1.0000   1.0000
   0.250   0.0118   0.01168   0.00444   0.0026   1.0000   1.0000
   0.500   0.0614   0.01165   0.00445  -0.0021   0.9824   1.0000
   0.750   0.1178   0.01159   0.00443  -0.0078   0.9547   1.0000
   1.000   0.1714   0.01150   0.00438  -0.0128   0.9204   1.0000
   1.250   0.2185   0.01141   0.00432  -0.0163   0.8761   1.0000
   1.500   0.2602   0.01137   0.00421  -0.0185   0.8140   1.0000
   1.750   0.2923   0.01147   0.00412  -0.0185   0.7364   1.0000
   2.000   0.3173   0.01172   0.00408  -0.0173   0.6528   1.0000
   2.250   0.3398   0.01209   0.00412  -0.0158   0.5710   1.0000
   2.500   0.3605   0.01251   0.00423  -0.0142   0.4929   1.0000
   2.750   0.3806   0.01297   0.00441  -0.0125   0.4234   1.0000
   3.000   0.4007   0.01346   0.00462  -0.0110   0.3607   1.0000
   3.250   0.4214   0.01394   0.00489  -0.0096   0.3113   1.0000
   3.500   0.4423   0.01442   0.00519  -0.0083   0.2719   1.0000
   3.750   0.4636   0.01490   0.00555  -0.0071   0.2405   1.0000
   4.000   0.4850   0.01537   0.00592  -0.0059   0.2143   1.0000
   4.250   0.5067   0.01582   0.00633  -0.0048   0.1907   1.0000
   4.500   0.5282   0.01633   0.00674  -0.0036   0.1693   1.0000
   4.750   0.5502   0.01679   0.00721  -0.0025   0.1486   1.0000
   5.000   0.5719   0.01731   0.00773  -0.0014   0.1289   1.0000
   5.250   0.5934   0.01788   0.00826  -0.0002   0.1097   1.0000
   5.500   0.6149   0.01852   0.00891   0.0010   0.0926   1.0000
   5.750   0.6359   0.01924   0.00961   0.0022   0.0781   1.0000
   6.000   0.6563   0.02011   0.01049   0.0035   0.0688   1.0000
   6.250   0.6769   0.02095   0.01137   0.0048   0.0607   1.0000
   6.500   0.6973   0.02195   0.01245   0.0061   0.0544   1.0000
   6.750   0.7175   0.02299   0.01358   0.0074   0.0501   1.0000
   7.000   0.7367   0.02426   0.01490   0.0087   0.0461   1.0000
   7.250   0.7572   0.02545   0.01633   0.0100   0.0422   1.0000
   7.500   0.7768   0.02676   0.01777   0.0113   0.0396   1.0000
   7.750   0.7952   0.02833   0.01942   0.0125   0.0377   1.0000
   8.000   0.8128   0.03030   0.02167   0.0139   0.0355   1.0000
   8.250   0.8299   0.03211   0.02384   0.0154   0.0333   1.0000
   8.500   0.8454   0.03403   0.02606   0.0168   0.0315   1.0000
   8.750   0.8590   0.03625   0.02859   0.0183   0.0303   1.0000
   9.000   0.8706   0.03858   0.03118   0.0198   0.0295   1.0000
   9.250   0.8794   0.04124   0.03407   0.0213   0.0287   1.0000
   9.500   0.8829   0.04456   0.03765   0.0229   0.0280   1.0000
   9.750   0.8795   0.04826   0.04182   0.0247   0.0277   1.0000
  10.000   0.8679   0.05236   0.04636   0.0264   0.0272   1.0000
  10.250   0.8500   0.05644   0.05073   0.0278   0.0270   1.0000
  10.500   0.8264   0.06110   0.05560   0.0275   0.0270   1.0000
  10.750   0.8054   0.06691   0.06153   0.0239   0.0274   1.0000
  11.000   0.7808   0.07583   0.07056   0.0161   0.0277   1.0000
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