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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 500,000
Max Cl/Cd: 88.12 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe54-il-500000-n5.txt
Download as CSV file: xf-goe54-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5769   0.11907   0.11687   0.0461   1.0000   0.0122
  -9.250  -0.5720   0.11533   0.11314   0.0445   1.0000   0.0123
  -9.000  -0.5680   0.11124   0.10906   0.0425   1.0000   0.0124
  -8.750  -0.5615   0.10823   0.10607   0.0412   1.0000   0.0127
  -8.500  -0.5550   0.10512   0.10298   0.0398   1.0000   0.0129
  -8.250  -0.5489   0.10185   0.09972   0.0381   1.0000   0.0131
  -8.000  -0.5427   0.09862   0.09652   0.0363   1.0000   0.0133
  -7.750  -0.5361   0.09544   0.09336   0.0344   1.0000   0.0140
  -7.250  -0.5163   0.08822   0.08617   0.0276   1.0000   0.0157
  -7.000  -0.5025   0.08451   0.08246   0.0236   1.0000   0.0160
  -6.750  -0.4842   0.08019   0.07814   0.0178   1.0000   0.0175
  -6.500  -0.4685   0.07657   0.07377   0.0137   0.7071   0.0175
  -6.250  -0.4499   0.07255   0.06948   0.0092   0.6369   0.0175
  -6.000  -0.4168   0.06581   0.06241  -0.0013   0.5811   0.0178
  -5.750  -0.4028   0.06354   0.05995  -0.0014   0.5245   0.0181
  -5.500  -0.3815   0.06071   0.05695  -0.0038   0.4940   0.0185
  -5.250  -0.3571   0.05762   0.05371  -0.0067   0.4753   0.0192
  -5.000  -0.3235   0.05352   0.04941  -0.0114   0.4636   0.0208
  -4.750  -0.2876   0.04899   0.04458  -0.0157   0.4547   0.0210
  -4.500  -0.2566   0.04513   0.04045  -0.0182   0.4461   0.0210
  -4.250  -0.2341   0.04203   0.03727  -0.0194   0.4374   0.0212
  -4.000  -0.2108   0.03981   0.03497  -0.0204   0.4283   0.0215
  -3.750  -0.1848   0.03774   0.03278  -0.0214   0.4201   0.0219
  -3.500  -0.1569   0.03568   0.03057  -0.0224   0.4122   0.0226
  -3.250  -0.1199   0.03381   0.02831  -0.0228   0.4059   0.0247
  -3.000  -0.0896   0.03162   0.02587  -0.0233   0.3992   0.0248
  -2.750  -0.0601   0.02965   0.02364  -0.0237   0.3922   0.0248
  -2.500  -0.0310   0.02786   0.02164  -0.0239   0.3855   0.0249
  -2.250  -0.0045   0.02524   0.01894  -0.0249   0.3777   0.0252
  -2.000   0.0225   0.02389   0.01751  -0.0254   0.3699   0.0257
  -1.750   0.0507   0.02276   0.01625  -0.0257   0.3607   0.0264
  -1.500   0.0799   0.02161   0.01493  -0.0258   0.3513   0.0273
  -1.250   0.1116   0.02145   0.01443  -0.0250   0.3409   0.0294
  -1.000   0.1412   0.02054   0.01327  -0.0249   0.3283   0.0295
  -0.750   0.1702   0.01963   0.01214  -0.0249   0.3117   0.0295
  -0.500   0.1992   0.01888   0.01117  -0.0249   0.2925   0.0296
  -0.250   0.2280   0.01712   0.00925  -0.0253   0.2761   0.0301
   0.250   0.2852   0.01549   0.00742  -0.0254   0.2569   0.0280
   0.500   0.3142   0.01485   0.00663  -0.0252   0.2498   0.0274
   0.750   0.3431   0.01430   0.00598  -0.0251   0.2446   0.0273
   1.000   0.3717   0.01386   0.00544  -0.0249   0.2388   0.0275
   1.250   0.4003   0.01351   0.00500  -0.0248   0.2337   0.0277
   1.500   0.4287   0.01323   0.00467  -0.0246   0.2296   0.0284
   1.750   0.4572   0.01302   0.00440  -0.0244   0.2252   0.0290
   2.000   0.4855   0.01272   0.00408  -0.0243   0.2208   0.0289
   2.250   0.5138   0.01249   0.00382  -0.0242   0.2170   0.0290
   2.500   0.5421   0.01231   0.00363  -0.0240   0.2141   0.0292
   2.750   0.5705   0.01218   0.00351  -0.0239   0.2118   0.0295
   3.000   0.5990   0.01194   0.00330  -0.0239   0.2091   0.0301
   3.250   0.6273   0.01185   0.00324  -0.0239   0.2061   0.0307
   3.500   0.6556   0.01185   0.00325  -0.0239   0.2030   0.0319
   3.750   0.6838   0.01189   0.00329  -0.0238   0.1998   0.0334
   4.000   0.7121   0.01189   0.00331  -0.0237   0.1973   0.0339
   4.250   0.7405   0.01188   0.00334  -0.0237   0.1946   0.0346
   4.500   0.7686   0.01192   0.00341  -0.0236   0.1912   0.0353
   4.750   0.7968   0.01196   0.00345  -0.0235   0.1876   0.0368
   5.000   0.8248   0.01209   0.00357  -0.0235   0.1838   0.0392
   5.250   0.8528   0.01218   0.00370  -0.0234   0.1807   0.0418
   5.500   0.8807   0.01227   0.00381  -0.0233   0.1764   0.0449
   5.750   0.9086   0.01241   0.00395  -0.0231   0.1717   0.0505
   6.000   0.9322   0.01092   0.00422  -0.0226   0.1664   1.0000
   6.250   0.9598   0.01113   0.00437  -0.0225   0.1574   1.0000
   6.500   0.9873   0.01136   0.00457  -0.0224   0.1490   1.0000
   6.750   1.0147   0.01163   0.00481  -0.0223   0.1420   1.0000
   7.000   1.0421   0.01188   0.00506  -0.0222   0.1368   1.0000
   7.250   1.0693   0.01217   0.00535  -0.0221   0.1322   1.0000
   7.500   1.0964   0.01247   0.00566  -0.0220   0.1284   1.0000
   7.750   1.1235   0.01275   0.00597  -0.0219   0.1250   1.0000
   8.000   1.1503   0.01307   0.00631  -0.0218   0.1207   1.0000
   8.250   1.1770   0.01343   0.00668  -0.0217   0.1167   1.0000
   8.500   1.2037   0.01375   0.00706  -0.0216   0.1135   1.0000
   8.750   1.2304   0.01405   0.00742  -0.0214   0.1100   1.0000
   9.000   1.2567   0.01442   0.00783  -0.0213   0.1060   1.0000
   9.250   1.2827   0.01487   0.00831  -0.0212   0.1012   1.0000
   9.500   1.3091   0.01517   0.00869  -0.0210   0.0968   1.0000
   9.750   1.3347   0.01565   0.00917  -0.0209   0.0859   1.0000
  10.250   1.3815   0.01755   0.01088  -0.0207   0.0521   1.0000
  10.500   1.4054   0.01831   0.01170  -0.0205   0.0477   1.0000
  10.750   1.4295   0.01896   0.01242  -0.0203   0.0447   1.0000
  11.000   1.4526   0.01977   0.01330  -0.0200   0.0416   1.0000
  11.250   1.4756   0.02056   0.01417  -0.0198   0.0392   1.0000
  11.500   1.4988   0.02125   0.01496  -0.0195   0.0372   1.0000
  11.750   1.5208   0.02210   0.01589  -0.0193   0.0347   1.0000
  12.000   1.5416   0.02313   0.01698  -0.0190   0.0324   1.0000
  12.250   1.5633   0.02391   0.01787  -0.0187   0.0306   1.0000
  12.500   1.5835   0.02488   0.01893  -0.0184   0.0284   1.0000
  12.750   1.6020   0.02607   0.02020  -0.0180   0.0263   1.0000
  13.000   1.6208   0.02711   0.02135  -0.0176   0.0240   1.0000
  13.250   1.6364   0.02853   0.02283  -0.0173   0.0216   1.0000
  13.500   1.6513   0.02993   0.02435  -0.0169   0.0195   1.0000
  13.750   1.6623   0.03174   0.02626  -0.0165   0.0177   1.0000
  14.000   1.6699   0.03384   0.02850  -0.0163   0.0164   1.0000
  14.250   1.6694   0.03662   0.03144  -0.0162   0.0155   1.0000
  14.500   1.6492   0.04487   0.03999  -0.0240   0.0155   1.0000
  14.750   1.6139   0.05606   0.05144  -0.0325   0.0159   1.0000
  15.000   1.5709   0.06649   0.06206  -0.0381   0.0166   1.0000
  15.250   1.5291   0.07654   0.07226  -0.0430   0.0172   1.0000
  15.500   1.4942   0.08558   0.08145  -0.0472   0.0176   1.0000
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