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GOE 775 AIRFOIL (goe775-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 775 AIRFOIL (goe775-il)
Reynolds number: 50,000
Max Cl/Cd: 25.14 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe775-il-50000-n5.txt
Download as CSV file: xf-goe775-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 775 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.6653   0.09971   0.08982  -0.0394   1.0000   0.1813
 -13.250  -0.6352   0.10156   0.09169  -0.0376   1.0000   0.1833
 -13.000  -0.7842   0.07535   0.06518  -0.0483   1.0000   0.1963
 -12.750  -0.7253   0.08051   0.07048  -0.0452   1.0000   0.1989
 -12.500  -0.7792   0.07049   0.06030  -0.0481   1.0000   0.2059
 -12.250  -0.8670   0.05873   0.04813  -0.0495   1.0000   0.2114
 -12.000  -0.8297   0.05996   0.04954  -0.0485   1.0000   0.2164
 -11.750  -0.8470   0.05624   0.04570  -0.0476   1.0000   0.2218
 -11.500  -0.8882   0.05123   0.04039  -0.0452   1.0000   0.2268
 -11.250  -0.8599   0.05140   0.04075  -0.0445   1.0000   0.2324
 -11.000  -0.8651   0.04942   0.03872  -0.0424   1.0000   0.2382
 -10.750  -0.8918   0.04645   0.03552  -0.0385   1.0000   0.2437
 -10.500  -0.8700   0.04622   0.03546  -0.0374   1.0000   0.2497
 -10.250  -0.8746   0.04485   0.03405  -0.0342   1.0000   0.2558
 -10.000  -0.8984   0.04292   0.03194  -0.0287   1.0000   0.2615
  -9.750  -0.8798   0.04266   0.03187  -0.0272   1.0000   0.2677
  -9.500  -0.8869   0.04168   0.03087  -0.0227   1.0000   0.2738
  -9.250  -0.9080   0.04041   0.02946  -0.0163   1.0000   0.2797
  -9.000  -0.8937   0.04013   0.02935  -0.0141   1.0000   0.2862
  -8.750  -0.8980   0.03930   0.02847  -0.0096   1.0000   0.2931
  -8.500  -0.9011   0.03846   0.02759  -0.0053   1.0000   0.3000
  -8.250  -0.8934   0.03804   0.02726  -0.0023   1.0000   0.3071
  -8.000  -0.8988   0.03717   0.02627   0.0024   1.0000   0.3150
  -7.750  -0.8896   0.03679   0.02600   0.0052   1.0000   0.3222
  -7.500  -0.8869   0.03621   0.02540   0.0088   1.0000   0.3304
  -7.250  -0.8832   0.03564   0.02481   0.0123   1.0000   0.3385
  -7.000  -0.8752   0.03528   0.02451   0.0152   1.0000   0.3469
  -6.750  -0.8733   0.03467   0.02382   0.0188   1.0000   0.3561
  -6.500  -0.8622   0.03446   0.02371   0.0213   1.0000   0.3646
  -6.250  -0.8473   0.03392   0.02310   0.0225   0.9967   0.3761
  -6.000  -0.8096   0.03372   0.02296   0.0201   0.9883   0.3892
  -5.750  -0.7726   0.03347   0.02274   0.0177   0.9794   0.4025
  -5.500  -0.7410   0.03302   0.02223   0.0161   0.9689   0.4169
  -5.250  -0.7024   0.03288   0.02215   0.0138   0.9601   0.4300
  -5.000  -0.6676   0.03263   0.02193   0.0121   0.9498   0.4430
  -4.750  -0.6382   0.03220   0.02142   0.0111   0.9385   0.4573
  -4.500  -0.5955   0.03214   0.02147   0.0084   0.9300   0.4698
  -4.250  -0.5665   0.03185   0.02118   0.0078   0.9178   0.4826
  -4.000  -0.5257   0.03156   0.02086   0.0052   0.9096   0.4975
  -3.750  -0.4961   0.03148   0.02086   0.0050   0.8967   0.5089
  -3.500  -0.4534   0.03115   0.02050   0.0022   0.8891   0.5238
  -3.250  -0.4280   0.03103   0.02043   0.0027   0.8751   0.5361
  -3.000  -0.3845   0.03080   0.02022   0.0002   0.8676   0.5500
  -2.750  -0.3661   0.03051   0.01990   0.0017   0.8527   0.5641
  -2.500  -0.3284   0.03047   0.01994   0.0005   0.8426   0.5763
  -2.250  -0.2993   0.03024   0.01972   0.0005   0.8306   0.5901
  -2.000  -0.2729   0.03007   0.01956   0.0010   0.8181   0.6041
  -1.750  -0.2345   0.02992   0.01946  -0.0001   0.8082   0.6172
  -1.500  -0.2131   0.02972   0.01925   0.0011   0.7946   0.6317
  -1.250  -0.1710   0.02954   0.01911  -0.0005   0.7858   0.6451
  -1.000  -0.1469   0.02949   0.01909   0.0006   0.7717   0.6582
  -0.750  -0.1138   0.02920   0.01877   0.0002   0.7618   0.6734
  -0.500  -0.0806   0.02928   0.01892   0.0001   0.7485   0.6847
  -0.250  -0.0532   0.02909   0.01870   0.0006   0.7367   0.6996
   0.000  -0.0141   0.02914   0.01878  -0.0004   0.7246   0.7108
   0.250   0.0130   0.02913   0.01877   0.0002   0.7114   0.7242
   0.500   0.0522   0.02910   0.01872  -0.0008   0.7000   0.7362
   0.750   0.0795   0.02928   0.01892  -0.0003   0.6854   0.7482
   1.000   0.1148   0.02918   0.01875  -0.0007   0.6743   0.7612
   1.250   0.1458   0.02950   0.01910  -0.0007   0.6589   0.7715
   1.500   0.1705   0.02953   0.01909   0.0002   0.6460   0.7857
   1.750   0.2117   0.02973   0.01927  -0.0013   0.6324   0.7944
   2.000   0.2338   0.02992   0.01946  -0.0001   0.6181   0.8081
   2.250   0.2732   0.03004   0.01952  -0.0014   0.6053   0.8179
   2.500   0.2983   0.03025   0.01973  -0.0007   0.5910   0.8305
   2.750   0.3280   0.03045   0.01993  -0.0008   0.5774   0.8425
   3.000   0.3649   0.03052   0.01993  -0.0019   0.5649   0.8528
   3.250   0.3831   0.03079   0.02022  -0.0003   0.5511   0.8679
   3.500   0.4281   0.03101   0.02040  -0.0031   0.5374   0.8751
   3.750   0.4527   0.03116   0.02053  -0.0025   0.5248   0.8892
   4.000   0.4958   0.03147   0.02085  -0.0053   0.5101   0.8968
   4.250   0.5266   0.03151   0.02078  -0.0057   0.4990   0.9096
   4.500   0.5659   0.03186   0.02119  -0.0081   0.4837   0.9181
   4.750   0.5958   0.03212   0.02144  -0.0088   0.4712   0.9301
   5.000   0.6373   0.03221   0.02145  -0.0114   0.4583   0.9389
   5.250   0.6676   0.03262   0.02192  -0.0125   0.4443   0.9500
   5.500   0.7028   0.03283   0.02209  -0.0142   0.4315   0.9604
   5.750   0.7407   0.03302   0.02225  -0.0165   0.4179   0.9693
   6.000   0.7729   0.03344   0.02272  -0.0182   0.4038   0.9796
   6.250   0.8104   0.03366   0.02288  -0.0206   0.3907   0.9885
   6.500   0.8473   0.03391   0.02311  -0.0230   0.3772   0.9971
   6.750   0.8618   0.03441   0.02366  -0.0217   0.3661   1.0000
   7.000   0.8716   0.03467   0.02385  -0.0190   0.3573   1.0000
   7.250   0.8752   0.03522   0.02444  -0.0156   0.3483   1.0000
   7.500   0.8817   0.03563   0.02482  -0.0125   0.3397   1.0000
   7.750   0.8876   0.03612   0.02528  -0.0093   0.3318   1.0000
   8.000   0.8886   0.03676   0.02598  -0.0055   0.3234   1.0000
   8.250   0.9007   0.03704   0.02610  -0.0030   0.3163   1.0000
   8.500   0.8935   0.03798   0.02719   0.0018   0.3083   1.0000
   8.750   0.8989   0.03846   0.02762   0.0052   0.3011   1.0000
   9.000   0.8995   0.03918   0.02833   0.0090   0.2943   1.0000
   9.250   0.8932   0.04009   0.02931   0.0137   0.2873   1.0000
   9.500   0.9038   0.04045   0.02954   0.0164   0.2808   1.0000
   9.750   0.8891   0.04156   0.03072   0.0220   0.2749   1.0000
  10.000   0.8794   0.04262   0.03183   0.0268   0.2688   1.0000
  10.250   0.8948   0.04296   0.03203   0.0287   0.2625   1.0000
  10.500   0.8773   0.04468   0.03387   0.0335   0.2568   1.0000
  10.750   0.8698   0.04620   0.03544   0.0370   0.2507   1.0000
  11.000   0.8923   0.04637   0.03545   0.0380   0.2446   1.0000
  11.250   0.8686   0.04918   0.03845   0.0417   0.2391   1.0000
  11.500   0.8600   0.05139   0.04075   0.0440   0.2333   1.0000
  11.750   0.8879   0.05122   0.04040   0.0447   0.2277   1.0000
  12.000   0.8529   0.05577   0.04521   0.0470   0.2226   1.0000
  12.250   0.8303   0.05996   0.04953   0.0480   0.2172   1.0000
  12.500   0.8596   0.05943   0.04888   0.0489   0.2122   1.0000
  12.750   0.8010   0.06798   0.05771   0.0483   0.2071   1.0000
  13.000   0.7223   0.08110   0.07108   0.0444   0.1994   1.0000
  13.250   0.7756   0.07662   0.06648   0.0472   0.1968   1.0000
  13.500   0.6348   0.10191   0.09204   0.0369   0.1838   1.0000
  13.750   0.6634   0.10031   0.09042   0.0385   0.1816   1.0000
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