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GOE 488 AIRFOIL (goe488-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 488 AIRFOIL (goe488-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.45 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe488-il-1000000.txt
Download as CSV file: xf-goe488-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 488 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4237   0.08471   0.08313  -0.0255   1.0000   0.0189
  -8.000  -0.4341   0.08239   0.08084  -0.0239   1.0000   0.0180
  -7.750  -0.4454   0.07805   0.07655  -0.0277   0.9987   0.0197
  -7.500  -0.4304   0.07296   0.07144  -0.0331   0.9964   0.0187
  -7.250  -0.4081   0.06572   0.06414  -0.0435   0.9931   0.0186
  -7.000  -0.3950   0.03185   0.02952  -0.0725   0.9839   0.0205
  -6.750  -0.3591   0.03740   0.03524  -0.0720   0.9836   0.0208
  -6.500  -0.3244   0.04786   0.04599  -0.0671   0.9837   0.0220
  -6.250  -0.2973   0.04371   0.04173  -0.0709   0.9788   0.0242
  -6.000  -0.2771   0.02507   0.02221  -0.0794   0.9729   0.0239
  -5.750  -0.2483   0.02112   0.01779  -0.0810   0.9703   0.0253
  -5.500  -0.2307   0.01727   0.01337  -0.0801   0.9624   0.0266
  -5.250  -0.2037   0.01556   0.01146  -0.0806   0.9582   0.0274
  -5.000  -0.1760   0.01512   0.01097  -0.0807   0.9528   0.0282
  -4.750  -0.1493   0.01486   0.01070  -0.0806   0.9462   0.0292
  -4.500  -0.1227   0.01347   0.00907  -0.0804   0.9406   0.0293
  -4.250  -0.0984   0.01243   0.00785  -0.0796   0.9328   0.0295
  -4.000  -0.0717   0.01153   0.00678  -0.0793   0.9264   0.0298
  -3.750  -0.0464   0.01082   0.00596  -0.0786   0.9190   0.0302
  -3.500  -0.0192   0.01035   0.00541  -0.0784   0.9132   0.0310
  -3.250   0.0066   0.00984   0.00482  -0.0778   0.9060   0.0316
  -3.000   0.0332   0.00938   0.00428  -0.0774   0.8996   0.0321
  -2.750   0.0594   0.00902   0.00386  -0.0769   0.8923   0.0326
  -2.500   0.0859   0.00868   0.00346  -0.0764   0.8849   0.0330
  -2.250   0.1121   0.00837   0.00311  -0.0760   0.8775   0.0332
  -2.000   0.1385   0.00809   0.00278  -0.0755   0.8702   0.0335
  -1.750   0.1646   0.00784   0.00250  -0.0750   0.8621   0.0337
  -1.500   0.1909   0.00764   0.00225  -0.0745   0.8536   0.0339
  -1.250   0.2158   0.00718   0.00172  -0.0737   0.8438   0.0353
  -1.000   0.2418   0.00695   0.00145  -0.0732   0.8347   0.0371
  -0.500   0.2947   0.00672   0.00118  -0.0722   0.8163   0.0408
  -0.250   0.3211   0.00665   0.00107  -0.0718   0.8049   0.0427
   0.000   0.3472   0.00661   0.00099  -0.0712   0.7896   0.0442
   0.250   0.3726   0.00648   0.00088  -0.0705   0.7709   0.0646
   0.500   0.3962   0.00622   0.00087  -0.0696   0.7444   0.1759
   0.750   0.4189   0.00625   0.00087  -0.0684   0.6965   0.2333
   1.000   0.4381   0.00654   0.00094  -0.0666   0.6156   0.2859
   1.250   0.4473   0.00550   0.00105  -0.0631   0.5624   0.7765
   1.750   0.5348   0.00628   0.00148  -0.0703   0.3756   0.9939
   2.000   0.5841   0.00651   0.00156  -0.0752   0.3489   1.0000
   2.250   0.6070   0.00665   0.00163  -0.0741   0.3362   1.0000
   2.500   0.6300   0.00677   0.00170  -0.0730   0.3260   1.0000
   2.750   0.6531   0.00691   0.00179  -0.0720   0.3161   1.0000
   3.000   0.6765   0.00703   0.00187  -0.0710   0.3059   1.0000
   3.250   0.6998   0.00717   0.00196  -0.0700   0.2942   1.0000
   3.500   0.7231   0.00732   0.00205  -0.0690   0.2817   1.0000
   3.750   0.7465   0.00747   0.00216  -0.0681   0.2676   1.0000
   4.000   0.7700   0.00763   0.00226  -0.0672   0.2537   1.0000
   4.250   0.7933   0.00782   0.00238  -0.0662   0.2348   1.0000
   4.500   0.8145   0.00818   0.00254  -0.0649   0.1949   1.0000
   4.750   0.8348   0.00864   0.00280  -0.0635   0.1550   1.0000
   5.000   0.8562   0.00902   0.00305  -0.0623   0.1293   1.0000
   5.250   0.8781   0.00939   0.00329  -0.0611   0.1066   1.0000
   5.500   0.8972   0.01003   0.00367  -0.0596   0.0602   1.0000
   5.750   0.9191   0.01044   0.00401  -0.0584   0.0437   1.0000
   6.000   0.9395   0.01103   0.00444  -0.0570   0.0184   1.0000
   6.250   0.9621   0.01142   0.00484  -0.0559   0.0153   1.0000
   6.500   0.9850   0.01177   0.00523  -0.0550   0.0142   1.0000
   6.750   1.0079   0.01213   0.00563  -0.0540   0.0135   1.0000
   7.000   1.0304   0.01253   0.00609  -0.0530   0.0127   1.0000
   7.250   1.0522   0.01300   0.00660  -0.0519   0.0118   1.0000
   7.500   1.0718   0.01373   0.00741  -0.0504   0.0109   1.0000
   7.750   1.0909   0.01449   0.00825  -0.0488   0.0104   1.0000
   8.000   1.1124   0.01495   0.00876  -0.0477   0.0100   1.0000
   8.250   1.1327   0.01552   0.00940  -0.0464   0.0097   1.0000
   8.500   1.1526   0.01612   0.01005  -0.0451   0.0094   1.0000
   8.750   1.1716   0.01677   0.01076  -0.0436   0.0090   1.0000
   9.000   1.1898   0.01747   0.01152  -0.0420   0.0087   1.0000
   9.250   1.2075   0.01820   0.01232  -0.0404   0.0084   1.0000
   9.500   1.2238   0.01902   0.01318  -0.0386   0.0081   1.0000
   9.750   1.2349   0.02027   0.01448  -0.0361   0.0077   1.0000
  10.000   1.2408   0.02217   0.01651  -0.0329   0.0073   1.0000
  10.250   1.2581   0.02272   0.01714  -0.0313   0.0072   1.0000
  10.500   1.2705   0.02368   0.01819  -0.0290   0.0071   1.0000
  10.750   1.2807   0.02465   0.01926  -0.0263   0.0069   1.0000
  11.000   1.2896   0.02570   0.02042  -0.0235   0.0068   1.0000
  11.250   1.2967   0.02701   0.02184  -0.0206   0.0067   1.0000
  11.500   1.3032   0.02835   0.02330  -0.0178   0.0066   1.0000
  11.750   1.3098   0.02954   0.02459  -0.0153   0.0064   1.0000
  12.000   1.3138   0.03111   0.02629  -0.0126   0.0064   1.0000
  12.250   1.3158   0.03289   0.02821  -0.0100   0.0063   1.0000
  12.500   1.3144   0.03510   0.03059  -0.0073   0.0063   1.0000
  12.750   1.3191   0.03626   0.03183  -0.0055   0.0061   1.0000
  13.000   1.3146   0.03882   0.03456  -0.0033   0.0061   1.0000
  13.250   1.3102   0.04138   0.03727  -0.0016   0.0060   1.0000
  13.500   1.3031   0.04438   0.04045  -0.0002   0.0060   1.0000
  13.750   1.2948   0.04766   0.04389   0.0006   0.0060   1.0000
  14.000   1.2878   0.05095   0.04731   0.0007   0.0059   1.0000
  14.250   1.2878   0.05347   0.04987   0.0004   0.0058   1.0000
  14.500   1.2685   0.05918   0.05581  -0.0009   0.0058   1.0000
  14.750   1.2583   0.06389   0.06065  -0.0028   0.0058   1.0000
  15.000   1.2420   0.07006   0.06700  -0.0057   0.0058   1.0000
  15.250   1.2327   0.07543   0.07246  -0.0087   0.0057   1.0000
  15.500   1.2068   0.08454   0.08181  -0.0140   0.0058   1.0000
  15.750   1.2095   0.08809   0.08536  -0.0163   0.0056   1.0000
  16.000   1.1744   0.09997   0.09749  -0.0234   0.0057   1.0000
  16.250   1.1289   0.11500   0.11279  -0.0325   0.0060   1.0000
  16.500   1.0964   0.12776   0.12574  -0.0402   0.0062   1.0000
  16.750   1.0755   0.13838   0.13647  -0.0466   0.0062   1.0000
  17.000   1.0325   0.15653   0.15479  -0.0571   0.0066   1.0000
  17.250   0.9782   0.18164   0.18000  -0.0695   0.0078   1.0000
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