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GOE 655 AIRFOIL (goe655-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 655 AIRFOIL (goe655-il)
Reynolds number: 50,000
Max Cl/Cd: 16.12 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe655-il-50000.txt
Download as CSV file: xf-goe655-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 655 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2939   0.12113   0.11437  -0.0300   1.0000   0.2448
  -9.500  -0.2585   0.11467   0.10784  -0.0281   1.0000   0.2540
  -9.250  -0.2855   0.11545   0.10880  -0.0276   1.0000   0.2609
  -9.000  -0.2600   0.11009   0.10344  -0.0260   1.0000   0.2687
  -8.750  -0.2789   0.10993   0.10342  -0.0248   1.0000   0.2771
  -8.500  -0.2708   0.10626   0.09982  -0.0233   1.0000   0.2825
  -8.250  -0.2718   0.10437   0.09801  -0.0214   1.0000   0.2912
  -8.000  -0.3073   0.10496   0.09883  -0.0190   1.0000   0.2963
  -7.750  -0.2806   0.10035   0.09419  -0.0172   1.0000   0.3047
  -7.500  -0.3212   0.10167   0.09574  -0.0137   1.0000   0.3120
  -7.250  -0.2993   0.09732   0.09140  -0.0119   1.0000   0.3204
  -7.000  -0.3316   0.09781   0.09206  -0.0079   1.0000   0.3283
  -6.750  -0.3260   0.09489   0.08921  -0.0055   1.0000   0.3363
  -6.500  -0.3552   0.09506   0.08953  -0.0013   1.0000   0.3450
  -6.250  -0.3652   0.09316   0.08774   0.0018   1.0000   0.3513
  -6.000  -0.3847   0.09255   0.08724   0.0058   1.0000   0.3618
  -5.500  -0.4245   0.09039   0.08530   0.0122   1.0000   0.3807
  -5.250  -0.4177   0.08748   0.08244   0.0148   1.0000   0.3891
  -5.000  -0.4407   0.08624   0.08131   0.0173   1.0000   0.4021
  -4.750  -0.4596   0.08508   0.08024   0.0194   1.0000   0.4177
  -4.500  -0.4436   0.05580   0.04924  -0.0281   1.0000   0.1764
  -4.250  -0.4297   0.05241   0.04565  -0.0285   1.0000   0.1719
  -4.000  -0.4130   0.04840   0.04114  -0.0300   1.0000   0.1681
  -3.750  -0.3963   0.04578   0.03813  -0.0305   1.0000   0.1686
  -3.500  -0.3446   0.04293   0.03463  -0.0366   0.9867   0.1703
  -3.250  -0.2931   0.04078   0.03181  -0.0419   0.9721   0.1748
  -3.000  -0.2441   0.03939   0.03006  -0.0464   0.9568   0.1836
  -2.750  -0.1958   0.03823   0.02840  -0.0503   0.9411   0.1942
  -2.500  -0.1509   0.03740   0.02747  -0.0535   0.9253   0.2119
  -2.250  -0.1073   0.03665   0.02681  -0.0563   0.9094   0.2363
  -2.000  -0.0665   0.03590   0.02618  -0.0583   0.8936   0.2815
  -1.750  -0.0289   0.03501   0.02576  -0.0595   0.8782   0.3827
  -1.500   0.0037   0.03428   0.02561  -0.0594   0.8627   0.5058
  -1.250   0.0330   0.03361   0.02555  -0.0584   0.8474   0.6225
  -1.000   0.1424   0.03227   0.02501  -0.0709   0.8324   1.0000
  -0.750   0.1840   0.03247   0.02463  -0.0739   0.8155   1.0000
  -0.500   0.2231   0.03269   0.02446  -0.0759   0.7992   1.0000
  -0.250   0.2614   0.03288   0.02433  -0.0775   0.7832   1.0000
   0.000   0.2995   0.03303   0.02421  -0.0788   0.7679   1.0000
   0.250   0.3404   0.03307   0.02400  -0.0805   0.7537   1.0000
   0.500   0.3990   0.03248   0.02316  -0.0842   0.7433   1.0000
   0.750   0.4243   0.03289   0.02339  -0.0835   0.7278   1.0000
   1.000   0.4465   0.03347   0.02382  -0.0825   0.7128   1.0000
   1.250   0.4671   0.03419   0.02440  -0.0814   0.6987   1.0000
   1.500   0.4964   0.03461   0.02468  -0.0813   0.6871   1.0000
   1.750   0.5344   0.03460   0.02453  -0.0821   0.6770   1.0000
   2.000   0.5406   0.03607   0.02592  -0.0796   0.6632   1.0000
   2.250   0.5546   0.03729   0.02705  -0.0781   0.6519   1.0000
   2.500   0.5897   0.03751   0.02717  -0.0786   0.6437   1.0000
   2.750   0.5789   0.04016   0.02977  -0.0750   0.6315   1.0000
   3.000   0.6335   0.03931   0.02882  -0.0771   0.6256   1.0000
   3.250   0.6005   0.04330   0.03279  -0.0719   0.6131   1.0000
   3.500   0.6249   0.04430   0.03374  -0.0717   0.6062   1.0000
   3.750   0.5924   0.04872   0.03814  -0.0676   0.5964   1.0000
   4.000   0.6058   0.05048   0.03986  -0.0667   0.5892   1.0000
   4.250   0.5856   0.05447   0.04383  -0.0645   0.5811   1.0000
   4.500   0.6258   0.05451   0.04382  -0.0648   0.5743   1.0000
   4.750   0.5968   0.05902   0.04832  -0.0623   0.5650   1.0000
   5.000   0.6195   0.06003   0.04930  -0.0617   0.5554   1.0000
   5.250   0.6472   0.06052   0.04977  -0.0610   0.5448   1.0000
   5.500   0.6304   0.06437   0.05360  -0.0594   0.5351   1.0000
   5.750   0.6853   0.06294   0.05215  -0.0593   0.5252   1.0000
   6.000   0.6519   0.06827   0.05749  -0.0578   0.5157   1.0000
   6.250   0.6721   0.06962   0.05885  -0.0571   0.5062   1.0000
   6.500   0.6842   0.07153   0.06078  -0.0563   0.4961   1.0000
   6.750   0.6730   0.07547   0.06473  -0.0556   0.4865   1.0000
   7.000   0.7346   0.07345   0.06273  -0.0548   0.4766   1.0000
   7.250   0.6819   0.08109   0.07037  -0.0545   0.4671   1.0000
   7.500   0.7013   0.08273   0.07204  -0.0539   0.4569   1.0000
   7.750   0.6978   0.08638   0.07571  -0.0537   0.4479   1.0000
   8.000   0.7038   0.08966   0.07901  -0.0536   0.4410   1.0000
   8.250   0.6840   0.09540   0.08479  -0.0545   0.4388   1.0000
   8.500   0.6744   0.10040   0.08982  -0.0554   0.4386   1.0000
   8.750   0.6724   0.10508   0.09453  -0.0564   0.4406   1.0000
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