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GOE 287 AIRFOIL (goe287-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 287 AIRFOIL (goe287-il)
Reynolds number: 500,000
Max Cl/Cd: 106.35 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe287-il-500000.txt
Download as CSV file: xf-goe287-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 287 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3740   0.10102   0.09908  -0.0107   0.9609   0.0190
  -8.250  -0.3735   0.09793   0.09595  -0.0118   0.9204   0.0191
  -8.000  -0.3734   0.09481   0.09273  -0.0128   0.8788   0.0191
  -7.750  -0.3679   0.09116   0.08897  -0.0157   0.8517   0.0191
  -7.500  -0.3650   0.08666   0.08438  -0.0147   0.8343   0.0194
  -7.250  -0.3552   0.08376   0.08140  -0.0149   0.8188   0.0197
  -7.000  -0.3435   0.08067   0.07824  -0.0170   0.8050   0.0201
  -6.750  -0.3298   0.07733   0.07481  -0.0203   0.7921   0.0206
  -6.500  -0.3139   0.07371   0.07112  -0.0244   0.7797   0.0213
  -6.250  -0.2950   0.06978   0.06711  -0.0293   0.7675   0.0225
  -6.000  -0.2542   0.06375   0.06088  -0.0422   0.7553   0.0242
  -5.750  -0.2286   0.05898   0.05595  -0.0470   0.7428   0.0243
  -5.500  -0.2129   0.05229   0.04913  -0.0507   0.7312   0.0248
  -5.250  -0.1944   0.04978   0.04653  -0.0516   0.7171   0.0253
  -5.000  -0.1725   0.04735   0.04398  -0.0530   0.7030   0.0260
  -4.750  -0.1474   0.04469   0.04117  -0.0550   0.6897   0.0273
  -4.500  -0.1063   0.04149   0.03758  -0.0584   0.6779   0.0311
  -4.250  -0.0762   0.03816   0.03393  -0.0601   0.6669   0.0314
  -4.000  -0.0544   0.03193   0.02746  -0.0626   0.6581   0.0326
  -3.750  -0.0295   0.03041   0.02581  -0.0634   0.6488   0.0336
  -3.500  -0.0027   0.02888   0.02414  -0.0641   0.6394   0.0354
  -3.250   0.0283   0.02715   0.02211  -0.0646   0.6316   0.0393
  -3.000   0.0599   0.02391   0.01831  -0.0654   0.6247   0.0419
  -2.750   0.0866   0.02218   0.01649  -0.0661   0.6187   0.0433
  -2.500   0.1143   0.02117   0.01540  -0.0666   0.6123   0.0453
  -2.250   0.1435   0.02029   0.01431  -0.0669   0.6065   0.0494
  -2.000   0.1739   0.01871   0.01234  -0.0672   0.6012   0.0549
  -1.750   0.2020   0.01771   0.01131  -0.0677   0.5956   0.0572
  -1.500   0.2309   0.01709   0.01053  -0.0679   0.5908   0.0613
  -0.750   0.3224   0.01269   0.00527  -0.0676   0.5778   0.0428
  -0.500   0.3513   0.01221   0.00470  -0.0677   0.5740   0.0423
  -0.250   0.3803   0.01172   0.00419  -0.0678   0.5701   0.0423
   0.000   0.4091   0.01130   0.00375  -0.0679   0.5660   0.0425
   0.250   0.4378   0.01096   0.00337  -0.0681   0.5622   0.0435
   0.500   0.4666   0.01073   0.00312  -0.0683   0.5582   0.0448
   0.750   0.4957   0.01049   0.00289  -0.0685   0.5537   0.0454
   1.000   0.5247   0.01033   0.00272  -0.0687   0.5494   0.0469
   1.250   0.5534   0.01027   0.00260  -0.0689   0.5452   0.0491
   1.500   0.5825   0.01015   0.00251  -0.0691   0.5405   0.0516
   1.750   0.6115   0.01007   0.00242  -0.0693   0.5357   0.0570
   2.000   0.6360   0.00829   0.00260  -0.0695   0.5314   0.8198
   2.250   0.6629   0.00797   0.00252  -0.0688   0.5271   1.0000
   2.500   0.6917   0.00803   0.00254  -0.0690   0.5222   1.0000
   2.750   0.7203   0.00813   0.00258  -0.0692   0.5173   1.0000
   3.000   0.7490   0.00820   0.00264  -0.0694   0.5117   1.0000
   3.250   0.7776   0.00826   0.00268  -0.0696   0.5046   1.0000
   3.500   0.8061   0.00834   0.00274  -0.0697   0.4972   1.0000
   3.750   0.8347   0.00841   0.00280  -0.0699   0.4884   1.0000
   4.000   0.8632   0.00848   0.00287  -0.0701   0.4791   1.0000
   4.250   0.8916   0.00856   0.00294  -0.0703   0.4673   1.0000
   4.500   0.9199   0.00865   0.00303  -0.0705   0.4483   1.0000
   4.750   0.9473   0.00891   0.00310  -0.0706   0.3989   1.0000
   5.000   0.9716   0.00982   0.00354  -0.0707   0.3211   1.0000
   5.250   0.9977   0.01036   0.00392  -0.0708   0.2951   1.0000
   5.500   1.0242   0.01077   0.00425  -0.0709   0.2780   1.0000
   5.750   1.0509   0.01111   0.00456  -0.0710   0.2658   1.0000
   6.000   1.0774   0.01147   0.00486  -0.0710   0.2528   1.0000
   6.250   1.1038   0.01182   0.00517  -0.0711   0.2396   1.0000
   6.500   1.1299   0.01219   0.00549  -0.0711   0.2205   1.0000
   6.750   1.1497   0.01351   0.00619  -0.0707   0.1225   1.0000
   7.000   1.1639   0.01559   0.00777  -0.0695   0.0293   1.0000
   7.250   1.1869   0.01630   0.00855  -0.0690   0.0249   1.0000
   7.500   1.2095   0.01702   0.00940  -0.0684   0.0227   1.0000
   7.750   1.2320   0.01767   0.01012  -0.0679   0.0210   1.0000
   8.000   1.2530   0.01845   0.01097  -0.0672   0.0195   1.0000
   8.250   1.2716   0.01945   0.01205  -0.0663   0.0183   1.0000
   8.500   1.2838   0.02102   0.01374  -0.0646   0.0173   1.0000
   8.750   1.2961   0.02239   0.01523  -0.0629   0.0168   1.0000
   9.000   1.3114   0.02335   0.01628  -0.0616   0.0163   1.0000
   9.250   1.3242   0.02442   0.01742  -0.0600   0.0156   1.0000
   9.500   1.3317   0.02561   0.01869  -0.0577   0.0150   1.0000
   9.750   1.3370   0.02709   0.02025  -0.0557   0.0145   1.0000
  10.000   1.3417   0.02882   0.02206  -0.0540   0.0141   1.0000
  10.250   1.3461   0.03076   0.02408  -0.0527   0.0138   1.0000
  10.500   1.3499   0.03287   0.02626  -0.0515   0.0134   1.0000
  10.750   1.3527   0.03515   0.02859  -0.0504   0.0132   1.0000
  11.000   1.3547   0.03754   0.03102  -0.0489   0.0129   1.0000
  11.250   1.3590   0.03979   0.03328  -0.0467   0.0127   1.0000
  11.500   1.3785   0.04155   0.03499  -0.0435   0.0124   1.0000
  11.750   1.3827   0.04343   0.03704  -0.0430   0.0122   1.0000
  12.000   1.3889   0.04537   0.03914  -0.0423   0.0120   1.0000
  12.250   1.3958   0.04738   0.04128  -0.0416   0.0117   1.0000
  12.500   1.4035   0.04947   0.04349  -0.0406   0.0114   1.0000
  12.750   1.4130   0.05163   0.04578  -0.0392   0.0113   1.0000
  13.000   1.4220   0.05404   0.04833  -0.0379   0.0112   1.0000
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