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FX 60-177 AIRFOIL (fx60177-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: FX 60-177 AIRFOIL (fx60177-il)
Reynolds number: 50,000
Max Cl/Cd: 24.18 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60177-il-50000.txt
Download as CSV file: xf-fx60177-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-177 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4819   0.11925   0.11262  -0.0450   1.0001   0.1496
 -11.000  -0.5127   0.10945   0.10294  -0.0490   1.0001   0.1325
 -10.750  -0.6546   0.09177   0.08522  -0.0587   1.0001   0.1070
 -10.500  -0.6714   0.08786   0.08131  -0.0570   1.0001   0.1060
 -10.250  -0.6950   0.08436   0.07781  -0.0546   1.0001   0.1049
 -10.000  -0.7235   0.08136   0.07478  -0.0513   1.0001   0.1037
  -9.750  -0.7545   0.07851   0.07188  -0.0476   1.0001   0.1022
  -9.500  -0.7830   0.07504   0.06826  -0.0445   1.0001   0.1005
  -9.250  -0.8074   0.07134   0.06432  -0.0414   1.0001   0.0990
  -9.000  -0.8238   0.06765   0.06034  -0.0387   1.0001   0.0984
  -8.750  -0.8322   0.06414   0.05654  -0.0363   1.0001   0.0987
  -8.500  -0.8348   0.06070   0.05278  -0.0342   1.0001   0.0997
  -8.250  -0.8328   0.05731   0.04900  -0.0324   1.0001   0.1012
  -8.000  -0.8269   0.05408   0.04532  -0.0308   1.0001   0.1038
  -7.750  -0.8172   0.05107   0.04166  -0.0294   1.0001   0.1070
  -7.500  -0.8005   0.04788   0.03833  -0.0282   1.0001   0.1109
  -7.250  -0.7826   0.04572   0.03602  -0.0269   1.0001   0.1175
  -7.000  -0.7635   0.04343   0.03339  -0.0255   1.0001   0.1243
  -6.750  -0.7430   0.04168   0.03165  -0.0238   1.0001   0.1327
  -6.500  -0.7228   0.04014   0.03014  -0.0218   1.0001   0.1446
  -6.250  -0.7022   0.03889   0.02899  -0.0193   1.0001   0.1598
  -6.000  -0.6832   0.03777   0.02791  -0.0167   1.0001   0.1837
  -5.750  -0.6697   0.03622   0.02692  -0.0139   1.0001   0.2204
  -5.500  -0.6637   0.03307   0.02517  -0.0120   1.0001   0.3269
  -5.250  -0.6687   0.03600   0.03002   0.0019   1.0001   0.5701
  -5.000  -0.6562   0.04072   0.03449   0.0116   1.0001   0.6227
  -4.750  -0.6392   0.04454   0.03804   0.0194   1.0001   0.6545
  -4.500  -0.6153   0.04842   0.04165   0.0265   1.0001   0.6856
  -4.250  -0.5857   0.05203   0.04499   0.0323   1.0001   0.7233
  -4.000  -0.5232   0.05514   0.04767   0.0326   1.0001   0.7594
  -3.750  -0.4993   0.05551   0.04781   0.0341   1.0001   0.7879
  -3.500  -0.4112   0.05624   0.04808   0.0260   1.0001   0.8225
  -3.250  -0.3798   0.05586   0.04748   0.0248   1.0001   0.8485
  -3.000  -0.3330   0.05518   0.04654   0.0207   1.0001   0.8717
  -2.750  -0.3087   0.05450   0.04570   0.0197   1.0001   0.8920
  -2.500  -0.2818   0.05377   0.04480   0.0179   1.0001   0.9106
  -2.250  -0.2575   0.05305   0.04393   0.0163   1.0001   0.9247
  -2.000  -0.2358   0.05244   0.04319   0.0150   1.0001   0.9375
  -1.750  -0.2100   0.05191   0.04252   0.0128   1.0001   0.9499
  -1.500  -0.1788   0.05147   0.04195   0.0096   1.0001   0.9619
  -1.250  -0.1468   0.05114   0.04151   0.0060   1.0001   0.9725
  -1.000  -0.1152   0.05095   0.04121   0.0024   1.0001   0.9817
  -0.750  -0.0840   0.05092   0.04108  -0.0012   1.0001   0.9899
  -0.500  -0.0516   0.05107   0.04115  -0.0052   1.0001   0.9976
  -0.250  -0.0400   0.05120   0.04124  -0.0052   1.0001   0.9999
   0.000  -0.0385   0.05128   0.04130  -0.0033   1.0001   0.9999
   0.250  -0.0372   0.05139   0.04140  -0.0014   1.0001   0.9999
   0.500  -0.0359   0.05155   0.04155   0.0004   1.0001   0.9999
   0.750  -0.0348   0.05176   0.04174   0.0023   1.0001   0.9999
   1.000  -0.0338   0.05200   0.04198   0.0041   1.0001   0.9999
   1.250   0.0361   0.05330   0.04325  -0.0071   0.9756   0.9999
   1.500   0.0865   0.05408   0.04400  -0.0139   0.9509   0.9999
   1.750   0.1290   0.05477   0.04466  -0.0189   0.9309   0.9999
   2.000   0.1577   0.05510   0.04498  -0.0213   0.9106   0.9999
   2.250   0.1866   0.05540   0.04529  -0.0234   0.8909   0.9999
   2.500   0.2189   0.05574   0.04562  -0.0259   0.8727   0.9999
   2.750   0.2517   0.05604   0.04593  -0.0282   0.8555   0.9999
   3.000   0.2721   0.05627   0.04618  -0.0285   0.8382   0.9999
   3.250   0.2885   0.05648   0.04642  -0.0281   0.8204   0.9999
   3.500   0.3080   0.05665   0.04661  -0.0280   0.8026   0.9999
   3.750   0.3304   0.05673   0.04672  -0.0281   0.7849   0.9999
   4.000   0.3540   0.05674   0.04676  -0.0282   0.7676   0.9999
   4.250   0.3751   0.05680   0.04686  -0.0280   0.7512   0.9999
   4.500   0.3931   0.05692   0.04703  -0.0272   0.7353   0.9999
   4.750   0.4093   0.05707   0.04722  -0.0262   0.7196   0.9999
   5.000   0.4249   0.05720   0.04740  -0.0250   0.7040   0.9999
   5.250   0.4429   0.05714   0.04739  -0.0239   0.6879   0.9999
   5.500   0.4612   0.05698   0.04728  -0.0226   0.6718   0.9999
   5.750   0.4773   0.05687   0.04723  -0.0210   0.6558   0.9999
   6.000   0.4922   0.05678   0.04719  -0.0192   0.6402   0.9999
   6.250   0.5040   0.05686   0.04732  -0.0172   0.6249   0.9999
   6.500   0.5129   0.05713   0.04764  -0.0149   0.6100   0.9999
   6.750   0.5222   0.05743   0.04801  -0.0127   0.5952   0.9999
   7.000   0.5364   0.05765   0.04829  -0.0111   0.5809   0.9999
   7.250   0.6047   0.05454   0.04533  -0.0130   0.5717   0.9999
   7.500   0.6235   0.05442   0.04529  -0.0116   0.5566   0.9999
   7.750   0.6469   0.05410   0.04505  -0.0107   0.5414   0.9999
   8.000   0.6695   0.05407   0.04513  -0.0099   0.5262   0.9999
   8.250   0.6945   0.05404   0.04521  -0.0094   0.5112   0.9999
   9.000   0.9934   0.04108   0.03251  -0.0254   0.4583   0.9999
   9.250   1.0096   0.04186   0.03337  -0.0241   0.4417   0.9999
   9.500   1.0295   0.04274   0.03431  -0.0234   0.4253   0.9999
   9.750   1.0537   0.04367   0.03530  -0.0233   0.4091   0.9999
  10.000   1.0791   0.04469   0.03638  -0.0235   0.3933   0.9999
  10.250   1.0511   0.04777   0.03971  -0.0184   0.3840   0.9999
  10.500   1.0550   0.04997   0.04204  -0.0168   0.3720   0.9999
  10.750   0.7682   0.08192   0.07409  -0.0122   0.3756   0.9999
  11.000   0.7129   0.09374   0.08589  -0.0158   0.3674   0.9999
  11.250   0.7133   0.09825   0.09048  -0.0173   0.3585   0.9999
  11.500   0.6878   0.10624   0.09850  -0.0203   0.3540   0.9999
  11.750   0.7181   0.10760   0.10001  -0.0208   0.3451   0.9999
  12.000   0.6901   0.11606   0.10850  -0.0244   0.3434   0.9999
  12.250   0.6751   0.12273   0.11522  -0.0275   0.3416   0.9999
  12.500   0.6691   0.12874   0.12131  -0.0305   0.3421   0.9999
  12.750   0.6701   0.13441   0.12706  -0.0334   0.3439   0.9999
  13.000   0.6852   0.13983   0.13261  -0.0361   0.3462   0.9999
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