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GOE 55 AIRFOIL (goe55-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 55 AIRFOIL (goe55-il)
Reynolds number: 500,000
Max Cl/Cd: 64.71 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe55-il-500000.txt
Download as CSV file: xf-goe55-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 55 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.6342   0.08722   0.08496   0.0184   1.0000   0.0306
  -7.500  -0.6289   0.08042   0.07815   0.0136   1.0000   0.0310
  -7.250  -0.6173   0.07761   0.07533   0.0133   1.0000   0.0314
  -7.000  -0.6029   0.07466   0.07238   0.0118   1.0000   0.0318
  -6.750  -0.5864   0.07129   0.06899   0.0091   1.0000   0.0324
  -6.500  -0.5676   0.06730   0.06496   0.0052   1.0000   0.0333
  -6.250  -0.5442   0.06203   0.05960  -0.0009   1.0000   0.0352
  -6.000  -0.5116   0.04995   0.04714  -0.0134   1.0000   0.0377
  -5.750  -0.4909   0.04791   0.04508  -0.0140   1.0000   0.0382
  -5.500  -0.4679   0.04561   0.04273  -0.0151   1.0000   0.0390
  -5.250  -0.4425   0.04276   0.03978  -0.0168   1.0000   0.0402
  -5.000  -0.4055   0.03373   0.03000  -0.0223   1.0000   0.0453
  -4.750  -0.3811   0.03209   0.02840  -0.0228   1.0000   0.0460
  -4.500  -0.3552   0.03067   0.02696  -0.0233   1.0000   0.0470
  -4.250  -0.3276   0.02887   0.02505  -0.0239   1.0000   0.0486
  -4.000  -0.2941   0.02842   0.02418  -0.0239   1.0000   0.0535
  -3.750  -0.2610   0.01843   0.01334  -0.0266   1.0000   0.0424
  -3.500  -0.2305   0.01572   0.01025  -0.0270   1.0000   0.0411
  -3.250  -0.2008   0.01421   0.00851  -0.0272   1.0000   0.0410
  -3.000  -0.1716   0.01317   0.00734  -0.0272   1.0000   0.0413
  -2.750  -0.1425   0.01236   0.00645  -0.0272   1.0000   0.0419
  -2.500  -0.1135   0.01180   0.00584  -0.0271   1.0000   0.0430
  -2.250  -0.0863   0.01163   0.00540  -0.0261   0.8439   0.0437
  -2.000  -0.0643   0.01235   0.00495  -0.0245   0.5428   0.0442
  -1.500  -0.0068   0.01166   0.00367  -0.0248   0.4162   0.0464
  -1.250   0.0221   0.01144   0.00338  -0.0248   0.3995   0.0479
  -1.000   0.0510   0.01128   0.00318  -0.0248   0.3881   0.0501
  -0.750   0.0799   0.01117   0.00302  -0.0248   0.3797   0.0526
  -0.500   0.1090   0.01095   0.00276  -0.0248   0.3718   0.0557
  -0.250   0.1380   0.01083   0.00262  -0.0248   0.3639   0.0608
   0.000   0.1670   0.01070   0.00251  -0.0248   0.3564   0.0711
   0.250   0.1960   0.01064   0.00251  -0.0248   0.3502   0.0989
   0.500   0.2249   0.01051   0.00245  -0.0248   0.3438   0.1244
   0.750   0.2538   0.01035   0.00247  -0.0250   0.3367   0.1915
   1.000   0.2815   0.00877   0.00258  -0.0256   0.3301   0.7450
   1.250   0.3033   0.00812   0.00241  -0.0235   0.3242   1.0000
   1.500   0.3320   0.00826   0.00246  -0.0234   0.3184   1.0000
   1.750   0.3608   0.00832   0.00248  -0.0233   0.3116   1.0000
   2.000   0.3894   0.00846   0.00252  -0.0232   0.3036   1.0000
   2.250   0.4181   0.00849   0.00256  -0.0231   0.2966   1.0000
   2.500   0.4467   0.00861   0.00260  -0.0230   0.2888   1.0000
   2.750   0.4754   0.00866   0.00265  -0.0229   0.2806   1.0000
   3.000   0.5040   0.00876   0.00271  -0.0228   0.2711   1.0000
   3.250   0.5325   0.00884   0.00275  -0.0227   0.2581   1.0000
   3.500   0.5611   0.00894   0.00280  -0.0227   0.2418   1.0000
   3.750   0.5895   0.00911   0.00287  -0.0226   0.2101   1.0000
   4.500   0.6735   0.01050   0.00365  -0.0227   0.0948   1.0000
   4.750   0.7013   0.01121   0.00407  -0.0228   0.0523   1.0000
   5.000   0.7294   0.01164   0.00447  -0.0228   0.0467   1.0000
   5.250   0.7575   0.01201   0.00487  -0.0227   0.0446   1.0000
   5.500   0.7855   0.01239   0.00530  -0.0226   0.0430   1.0000
   5.750   0.8133   0.01282   0.00576  -0.0225   0.0414   1.0000
   6.000   0.8410   0.01332   0.00629  -0.0224   0.0402   1.0000
   6.250   0.8684   0.01392   0.00694  -0.0223   0.0391   1.0000
   6.500   0.8953   0.01469   0.00776  -0.0222   0.0381   1.0000
   6.750   0.9217   0.01557   0.00871  -0.0220   0.0374   1.0000
   7.000   0.9486   0.01614   0.00934  -0.0219   0.0370   1.0000
   7.250   0.9753   0.01673   0.01000  -0.0217   0.0363   1.0000
   7.500   1.0015   0.01743   0.01077  -0.0214   0.0357   1.0000
   7.750   1.0274   0.01822   0.01162  -0.0212   0.0351   1.0000
   8.000   1.0530   0.01908   0.01256  -0.0209   0.0345   1.0000
   8.250   1.0782   0.01998   0.01353  -0.0206   0.0338   1.0000
   8.500   1.1031   0.02089   0.01451  -0.0203   0.0330   1.0000
   8.750   1.1274   0.02194   0.01560  -0.0200   0.0323   1.0000
   9.000   1.1505   0.02336   0.01708  -0.0196   0.0316   1.0000
   9.250   1.1715   0.02572   0.01955  -0.0191   0.0309   1.0000
   9.500   1.1928   0.02763   0.02167  -0.0186   0.0303   1.0000
   9.750   1.2164   0.02833   0.02255  -0.0182   0.0298   1.0000
  10.000   1.2384   0.02954   0.02395  -0.0177   0.0291   1.0000
  10.250   1.2590   0.03106   0.02566  -0.0172   0.0285   1.0000
  10.500   1.2783   0.03271   0.02749  -0.0167   0.0279   1.0000
  10.750   1.2973   0.03419   0.02910  -0.0161   0.0272   1.0000
  11.000   1.3163   0.03552   0.03051  -0.0156   0.0265   1.0000
  11.250   1.3328   0.03723   0.03230  -0.0151   0.0258   1.0000
  11.500   1.3423   0.04069   0.03589  -0.0145   0.0252   1.0000
  11.750   1.3386   0.04567   0.04128  -0.0136   0.0247   1.0000
  12.000   1.3437   0.04760   0.04349  -0.0129   0.0244   1.0000
  12.250   1.3404   0.05055   0.04672  -0.0122   0.0242   1.0000
  12.500   1.3252   0.05408   0.05047  -0.0114   0.0240   1.0000
  12.750   1.3056   0.05974   0.05636  -0.0154   0.0240   1.0000
  13.000   1.2839   0.06846   0.06531  -0.0241   0.0240   1.0000
  13.250   1.2570   0.07884   0.07589  -0.0332   0.0242   1.0000
  13.500   1.2238   0.09007   0.08728  -0.0416   0.0244   1.0000
  13.750   1.1842   0.10246   0.09980  -0.0496   0.0246   1.0000
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