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GOE 611 AIRFOIL (goe611-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 611 AIRFOIL (goe611-il)
Reynolds number: 500,000
Max Cl/Cd: 97.01 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe611-il-500000-n5.txt
Download as CSV file: xf-goe611-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 611 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1358   0.08925   0.08644  -0.0736   0.8327   0.0082
  -9.000  -0.1323   0.08546   0.08262  -0.0756   0.8247   0.0083
  -8.750  -0.1295   0.08157   0.07870  -0.0778   0.8172   0.0084
  -8.500  -0.1228   0.07882   0.07593  -0.0795   0.8103   0.0085
  -8.250  -0.1143   0.07650   0.07359  -0.0811   0.8035   0.0087
  -8.000  -0.1081   0.07361   0.07068  -0.0834   0.7972   0.0089
  -7.750  -0.1018   0.07048   0.06754  -0.0866   0.7907   0.0092
  -7.500  -0.0918   0.06654   0.06355  -0.0913   0.7849   0.0094
  -7.250  -0.0801   0.06189   0.05886  -0.0967   0.7791   0.0096
  -7.000  -0.0667   0.05682   0.05371  -0.1021   0.7732   0.0096
  -6.750  -0.0513   0.05159   0.04835  -0.1068   0.7680   0.0098
  -6.500  -0.0344   0.04585   0.04244  -0.1109   0.7624   0.0101
  -6.250  -0.0215   0.03499   0.03108  -0.1150   0.7575   0.0111
  -6.000   0.0019   0.03365   0.02962  -0.1155   0.7520   0.0114
  -5.500   0.0424   0.02218   0.01707  -0.1156   0.7411   0.0143
  -5.250   0.0687   0.02172   0.01651  -0.1158   0.7350   0.0146
  -5.000   0.0953   0.02127   0.01596  -0.1159   0.7280   0.0150
  -4.750   0.1218   0.02040   0.01492  -0.1160   0.7214   0.0160
  -4.500   0.1472   0.01694   0.01086  -0.1154   0.7146   0.0185
  -4.250   0.1744   0.01668   0.01050  -0.1155   0.7071   0.0190
  -4.000   0.2020   0.01637   0.01011  -0.1156   0.6987   0.0199
  -3.750   0.2294   0.01561   0.00912  -0.1155   0.6907   0.0215
  -3.500   0.2573   0.01485   0.00807  -0.1154   0.6815   0.0227
  -3.250   0.2843   0.01411   0.00722  -0.1154   0.6724   0.0237
  -3.000   0.3115   0.01383   0.00686  -0.1154   0.6625   0.0245
  -2.750   0.3391   0.01344   0.00639  -0.1155   0.6521   0.0253
  -2.500   0.3665   0.01303   0.00587  -0.1154   0.6418   0.0262
  -2.000   0.4211   0.01250   0.00510  -0.1152   0.6184   0.0281
  -1.750   0.4479   0.01228   0.00476  -0.1150   0.6033   0.0286
  -1.500   0.4743   0.01212   0.00448  -0.1148   0.5864   0.0290
  -1.250   0.5006   0.01195   0.00419  -0.1146   0.5703   0.0293
  -1.000   0.5269   0.01154   0.00371  -0.1144   0.5576   0.0301
  -0.750   0.5538   0.01134   0.00347  -0.1144   0.5476   0.0312
  -0.500   0.5807   0.01123   0.00330  -0.1143   0.5380   0.0317
  -0.250   0.6080   0.01113   0.00316  -0.1143   0.5287   0.0323
   0.000   0.6351   0.01108   0.00305  -0.1143   0.5201   0.0331
   0.250   0.6623   0.01105   0.00297  -0.1143   0.5111   0.0338
   0.500   0.6895   0.01105   0.00292  -0.1143   0.5032   0.0346
   0.750   0.7165   0.01106   0.00289  -0.1143   0.4945   0.0353
   1.000   0.7437   0.01109   0.00287  -0.1143   0.4866   0.0363
   1.250   0.7705   0.01116   0.00288  -0.1142   0.4781   0.0375
   1.500   0.7976   0.01121   0.00289  -0.1142   0.4699   0.0390
   1.750   0.8241   0.01129   0.00292  -0.1141   0.4612   0.0416
   2.000   0.8510   0.01136   0.00298  -0.1141   0.4527   0.0471
   2.250   0.8732   0.00950   0.00330  -0.1135   0.4445   1.0000
   2.500   0.8996   0.00965   0.00338  -0.1134   0.4357   1.0000
   2.750   0.9253   0.00983   0.00348  -0.1131   0.4263   1.0000
   3.000   0.9504   0.01004   0.00360  -0.1128   0.4145   1.0000
   3.250   0.9760   0.01023   0.00373  -0.1126   0.4037   1.0000
   3.500   1.0013   0.01043   0.00387  -0.1123   0.3938   1.0000
   3.750   1.0260   0.01066   0.00403  -0.1119   0.3836   1.0000
   4.000   1.0512   0.01086   0.00419  -0.1117   0.3737   1.0000
   4.250   1.0758   0.01109   0.00437  -0.1113   0.3638   1.0000
   4.500   1.0998   0.01135   0.00457  -0.1108   0.3531   1.0000
   4.750   1.1237   0.01161   0.00479  -0.1103   0.3414   1.0000
   5.000   1.1470   0.01190   0.00502  -0.1098   0.3292   1.0000
   5.250   1.1697   0.01221   0.00527  -0.1091   0.3167   1.0000
   5.500   1.1919   0.01255   0.00555  -0.1083   0.3039   1.0000
   5.750   1.2134   0.01290   0.00585  -0.1075   0.2910   1.0000
   6.000   1.2334   0.01333   0.00619  -0.1064   0.2735   1.0000
   6.250   1.2530   0.01375   0.00655  -0.1052   0.2585   1.0000
   6.500   1.2713   0.01422   0.00696  -0.1038   0.2417   1.0000
   6.750   1.2834   0.01491   0.00750  -0.1013   0.2151   1.0000
   7.000   1.2823   0.01627   0.00850  -0.0967   0.1557   1.0000
   7.250   1.2896   0.01729   0.00935  -0.0936   0.1309   1.0000
   7.500   1.3038   0.01796   0.00999  -0.0918   0.1231   1.0000
   7.750   1.3203   0.01851   0.01057  -0.0904   0.1186   1.0000
   8.000   1.3367   0.01909   0.01116  -0.0890   0.1152   1.0000
   8.250   1.3518   0.01975   0.01184  -0.0875   0.1116   1.0000
   8.500   1.3658   0.02050   0.01260  -0.0859   0.1073   1.0000
   8.750   1.3822   0.02112   0.01327  -0.0847   0.1041   1.0000
   9.000   1.3985   0.02176   0.01395  -0.0835   0.1000   1.0000
   9.250   1.4100   0.02274   0.01490  -0.0819   0.0925   1.0000
   9.500   1.4098   0.02456   0.01648  -0.0790   0.0559   1.0000
   9.750   1.3965   0.02750   0.01929  -0.0751   0.0172   1.0000
  10.000   1.4052   0.02889   0.02074  -0.0736   0.0142   1.0000
  10.250   1.4156   0.03018   0.02212  -0.0723   0.0128   1.0000
  10.500   1.4254   0.03156   0.02358  -0.0712   0.0117   1.0000
  10.750   1.4333   0.03312   0.02523  -0.0699   0.0107   1.0000
  11.000   1.4386   0.03494   0.02714  -0.0685   0.0098   1.0000
  11.250   1.4467   0.03655   0.02884  -0.0675   0.0094   1.0000
  11.500   1.4534   0.03832   0.03070  -0.0664   0.0089   1.0000
  11.750   1.4589   0.04025   0.03273  -0.0654   0.0084   1.0000
  12.000   1.4634   0.04231   0.03488  -0.0644   0.0080   1.0000
  12.250   1.4663   0.04460   0.03726  -0.0634   0.0076   1.0000
  12.500   1.4659   0.04730   0.04007  -0.0625   0.0072   1.0000
  12.750   1.4687   0.04976   0.04262  -0.0618   0.0069   1.0000
  13.000   1.4709   0.05232   0.04528  -0.0612   0.0066   1.0000
  13.250   1.4716   0.05513   0.04818  -0.0607   0.0064   1.0000
  13.500   1.4714   0.05812   0.05129  -0.0603   0.0061   1.0000
  13.750   1.4703   0.06128   0.05455  -0.0600   0.0060   1.0000
  14.000   1.4687   0.06457   0.05793  -0.0598   0.0058   1.0000
  14.250   1.4660   0.06805   0.06151  -0.0598   0.0056   1.0000
  14.500   1.4622   0.07175   0.06532  -0.0598   0.0055   1.0000
  14.750   1.4569   0.07572   0.06939  -0.0600   0.0054   1.0000
  15.000   1.4495   0.08004   0.07383  -0.0603   0.0052   1.0000
  15.250   1.4390   0.08483   0.07873  -0.0607   0.0051   1.0000
  15.500   1.4320   0.08922   0.08324  -0.0612   0.0051   1.0000
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