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GOE 415 AIRFOIL (goe415-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 415 AIRFOIL (goe415-il)
Reynolds number: 200,000
Max Cl/Cd: 68.93 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe415-il-200000.txt
Download as CSV file: xf-goe415-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 415 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4264   0.10421   0.10092  -0.0089   1.0000   0.0247
  -8.250  -0.4212   0.10059   0.09734  -0.0116   1.0000   0.0248
  -8.000  -0.4221   0.09452   0.09134  -0.0131   1.0000   0.0252
  -7.750  -0.4166   0.09029   0.08712  -0.0112   1.0000   0.0260
  -7.500  -0.4104   0.08696   0.08382  -0.0115   1.0000   0.0266
  -7.250  -0.4035   0.08356   0.08046  -0.0131   1.0000   0.0273
  -7.000  -0.3948   0.07991   0.07683  -0.0159   1.0000   0.0280
  -6.750  -0.3848   0.07605   0.07299  -0.0195   1.0000   0.0289
  -6.500  -0.3732   0.07198   0.06893  -0.0235   1.0000   0.0299
  -6.250  -0.3598   0.06776   0.06471  -0.0279   1.0000   0.0315
  -6.000  -0.3413   0.06307   0.05993  -0.0339   1.0000   0.0340
  -5.750  -0.3146   0.05889   0.05543  -0.0411   1.0000   0.0357
  -5.500  -0.3010   0.05586   0.05216  -0.0422   1.0000   0.0360
  -5.250  -0.2995   0.04874   0.04517  -0.0423   1.0000   0.0374
  -5.000  -0.2900   0.04606   0.04253  -0.0413   1.0000   0.0387
  -4.750  -0.2780   0.04348   0.03989  -0.0406   1.0000   0.0403
  -4.500  -0.2634   0.04070   0.03698  -0.0404   1.0000   0.0425
  -4.250  -0.2452   0.03788   0.03390  -0.0403   1.0000   0.0461
  -4.000  -0.1737   0.01808   0.01406  -0.0487   0.9840   0.0544
  -3.750  -0.1809   0.03099   0.02647  -0.0457   0.9938   0.0562
  -3.500  -0.1369   0.02782   0.02293  -0.0500   0.9866   0.0683
  -3.250  -0.0939   0.02552   0.02030  -0.0542   0.9788   0.0931
  -2.750   0.0250   0.00632   0.00023  -0.0610   0.9363   0.0762
  -2.500   0.0461   0.01809   0.01119  -0.0598   0.9517   0.0496
  -2.250   0.0845   0.01552   0.00847  -0.0611   0.9376   0.0449
  -2.000   0.1196   0.01430   0.00709  -0.0615   0.9184   0.0459
  -1.750   0.1498   0.01354   0.00621  -0.0609   0.8944   0.0486
  -1.500   0.1754   0.01259   0.00520  -0.0596   0.8647   0.0500
  -1.250   0.1993   0.01176   0.00430  -0.0581   0.8283   0.0551
  -1.000   0.2240   0.01141   0.00373  -0.0567   0.7834   0.0627
  -0.750   0.2489   0.01110   0.00315  -0.0554   0.7404   0.0763
  -0.500   0.2823   0.00832   0.00301  -0.0563   0.7040   1.0000
  -0.250   0.3080   0.00856   0.00284  -0.0555   0.6722   1.0000
   0.000   0.3339   0.00879   0.00275  -0.0548   0.6452   1.0000
   0.250   0.3601   0.00900   0.00271  -0.0543   0.6214   1.0000
   0.500   0.3864   0.00921   0.00269  -0.0539   0.6006   1.0000
   0.750   0.4127   0.00943   0.00269  -0.0534   0.5811   1.0000
   1.000   0.4391   0.00966   0.00272  -0.0530   0.5632   1.0000
   1.250   0.4655   0.00990   0.00278  -0.0527   0.5466   1.0000
   1.500   0.4921   0.01013   0.00287  -0.0523   0.5303   1.0000
   1.750   0.5187   0.01036   0.00297  -0.0520   0.5148   1.0000
   2.000   0.5453   0.01059   0.00309  -0.0517   0.4998   1.0000
   2.250   0.5719   0.01082   0.00322  -0.0514   0.4851   1.0000
   2.500   0.5985   0.01105   0.00336  -0.0511   0.4705   1.0000
   2.750   0.6251   0.01128   0.00352  -0.0509   0.4565   1.0000
   3.000   0.6516   0.01151   0.00367  -0.0506   0.4430   1.0000
   3.250   0.6781   0.01173   0.00383  -0.0503   0.4294   1.0000
   3.500   0.7045   0.01196   0.00399  -0.0500   0.4161   1.0000
   3.750   0.7309   0.01220   0.00419  -0.0497   0.4037   1.0000
   4.000   0.7573   0.01245   0.00439  -0.0495   0.3918   1.0000
   4.250   0.7837   0.01269   0.00462  -0.0492   0.3802   1.0000
   4.500   0.8101   0.01297   0.00490  -0.0490   0.3699   1.0000
   4.750   0.8364   0.01327   0.00520  -0.0487   0.3603   1.0000
   5.000   0.8626   0.01356   0.00548  -0.0485   0.3511   1.0000
   5.250   0.8889   0.01386   0.00584  -0.0482   0.3422   1.0000
   5.500   0.9149   0.01422   0.00617  -0.0480   0.3341   1.0000
   5.750   0.9408   0.01447   0.00651  -0.0477   0.3237   1.0000
   6.000   0.9659   0.01465   0.00670  -0.0473   0.3087   1.0000
   6.250   0.9908   0.01486   0.00692  -0.0469   0.2937   1.0000
   6.500   1.0160   0.01506   0.00719  -0.0465   0.2789   1.0000
   6.750   1.0413   0.01524   0.00750  -0.0462   0.2615   1.0000
   7.000   1.0663   0.01547   0.00779  -0.0458   0.2424   1.0000
   7.250   1.0903   0.01582   0.00807  -0.0454   0.2075   1.0000
   7.500   1.1114   0.01671   0.00861  -0.0447   0.1409   1.0000
   7.750   1.1285   0.01832   0.00979  -0.0436   0.0739   1.0000
   8.000   1.1427   0.02034   0.01148  -0.0421   0.0296   1.0000
   8.250   1.1630   0.02138   0.01276  -0.0411   0.0260   1.0000
   8.500   1.1816   0.02260   0.01419  -0.0399   0.0237   1.0000
   8.750   1.1979   0.02400   0.01582  -0.0386   0.0225   1.0000
   9.000   1.2108   0.02565   0.01768  -0.0369   0.0217   1.0000
   9.250   1.2200   0.02753   0.01971  -0.0349   0.0212   1.0000
   9.500   1.2267   0.02952   0.02182  -0.0327   0.0209   1.0000
   9.750   1.2330   0.03154   0.02393  -0.0304   0.0208   1.0000
  10.000   1.2379   0.03378   0.02623  -0.0279   0.0206   1.0000
  10.250   1.2453   0.03580   0.02838  -0.0258   0.0201   1.0000
  10.500   1.2539   0.03745   0.03018  -0.0240   0.0196   1.0000
  10.750   1.2636   0.03963   0.03248  -0.0222   0.0194   1.0000
  11.000   1.2746   0.04221   0.03520  -0.0206   0.0196   1.0000
  11.250   1.2867   0.04541   0.03857  -0.0191   0.0199   1.0000
  11.500   1.3080   0.04889   0.04219  -0.0184   0.0207   1.0000
  11.750   1.3115   0.05024   0.04374  -0.0165   0.0212   1.0000
  12.000   1.3094   0.05211   0.04593  -0.0147   0.0222   1.0000
  12.250   1.3012   0.05592   0.05024  -0.0134   0.0243   1.0000
  12.500   1.2917   0.06054   0.05518  -0.0129   0.0260   1.0000
  12.750   1.2805   0.06572   0.06061  -0.0130   0.0273   1.0000
  13.000   1.2798   0.06958   0.06491  -0.0130   0.0321   1.0000
  13.250   1.2562   0.07576   0.07139  -0.0159   0.0329   1.0000
  13.500   1.2343   0.08236   0.07824  -0.0195   0.0334   1.0000
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