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GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 513 AIRFOIL (goe513-il)
Reynolds number: 50,000
Max Cl/Cd: 10.27 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe513-il-50000.txt
Download as CSV file: xf-goe513-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 513 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2892   0.12764   0.12142  -0.0174   1.0000   0.2474
  -9.000  -0.3073   0.12692   0.12082  -0.0160   1.0000   0.2529
  -8.750  -0.3525   0.12835   0.12242  -0.0147   1.0000   0.2553
  -8.500  -0.3291   0.12293   0.11703  -0.0131   1.0000   0.2583
  -8.250  -0.3204   0.12010   0.11423  -0.0111   1.0000   0.2632
  -8.000  -0.3307   0.11852   0.11274  -0.0094   1.0000   0.2685
  -7.750  -0.3712   0.11877   0.11313  -0.0076   1.0000   0.2731
  -7.500  -0.4255   0.11936   0.11389  -0.0053   1.0000   0.2742
  -7.250  -0.3754   0.11298   0.10749  -0.0042   1.0000   0.2782
  -7.000  -0.3776   0.11075   0.10534  -0.0022   1.0000   0.2818
  -6.750  -0.3935   0.10912   0.10380  -0.0001   1.0000   0.2862
  -6.500  -0.4453   0.10897   0.10380   0.0032   1.0000   0.2911
  -6.250  -0.5161   0.10983   0.10480   0.0076   1.0000   0.2929
  -6.000  -0.4953   0.10530   0.10034   0.0091   1.0000   0.2949
  -5.750  -0.4957   0.10281   0.09793   0.0112   1.0000   0.2975
  -5.500  -0.4763   0.09931   0.09440   0.0066   0.9882   0.3045
  -5.250  -0.4851   0.09620   0.09121   0.0017   0.9719   0.3128
  -5.000  -0.4536   0.09180   0.08677  -0.0021   0.9568   0.3164
  -4.750  -0.4972   0.07362   0.06728  -0.0140   0.9468   0.1680
  -4.500  -0.4759   0.07015   0.06360  -0.0155   0.9325   0.1651
  -4.250  -0.4567   0.06617   0.05926  -0.0166   0.9200   0.1621
  -4.000  -0.4470   0.06159   0.05412  -0.0156   0.9077   0.1585
  -3.750  -0.4425   0.05678   0.04839  -0.0130   0.8962   0.1551
  -3.500  -0.4189   0.05460   0.04587  -0.0128   0.8844   0.1557
  -3.250  -0.3864   0.05321   0.04429  -0.0139   0.8732   0.1583
  -3.000  -0.3702   0.05230   0.04320  -0.0125   0.8606   0.1618
  -2.750  -0.3479   0.05095   0.04143  -0.0117   0.8497   0.1672
  -2.500  -0.3111   0.05019   0.04051  -0.0132   0.8398   0.1749
  -2.250  -0.2961   0.04961   0.03971  -0.0114   0.8281   0.1821
  -2.000  -0.2662   0.04933   0.03937  -0.0118   0.8180   0.1939
  -1.750  -0.2403   0.04928   0.03926  -0.0115   0.8078   0.2117
  -1.500  -0.2231   0.04927   0.03907  -0.0097   0.7977   0.2372
  -1.250  -0.1957   0.04910   0.03910  -0.0088   0.7886   0.2970
  -1.000  -0.1914   0.04920   0.03921  -0.0055   0.7790   0.3424
  -0.750  -0.1485   0.04879   0.03871  -0.0077   0.7699   0.4000
  -0.500  -0.1309   0.04901   0.03897  -0.0076   0.7586   0.4344
  -0.250  -0.0618   0.04820   0.03844  -0.0153   0.7487   0.5096
   0.000  -0.0268   0.04844   0.03873  -0.0180   0.7369   0.5361
   0.250   0.0142   0.04867   0.03914  -0.0213   0.7261   0.5599
   0.500   0.3124   0.04849   0.04018  -0.0693   0.7063   1.0000
   0.750   0.3638   0.04814   0.03947  -0.0721   0.6968   1.0000
   1.000   0.3571   0.04990   0.04110  -0.0680   0.6832   1.0000
   1.250   0.4370   0.04807   0.03887  -0.0735   0.6762   1.0000
   1.500   0.4114   0.05070   0.04144  -0.0673   0.6614   1.0000
   1.750   0.4130   0.05223   0.04284  -0.0643   0.6493   1.0000
   2.000   0.4718   0.05088   0.04121  -0.0668   0.6410   1.0000
   2.500   0.4699   0.05430   0.04442  -0.0603   0.6168   1.0000
   2.750   0.4967   0.05447   0.04444  -0.0595   0.6066   1.0000
   3.000   0.4811   0.05724   0.04716  -0.0553   0.5937   1.0000
   3.250   0.5465   0.05501   0.04472  -0.0575   0.5873   1.0000
   3.500   0.5089   0.05941   0.04911  -0.0519   0.5729   1.0000
   3.750   0.5808   0.05654   0.04603  -0.0542   0.5675   1.0000
   4.000   0.5329   0.06205   0.05157  -0.0485   0.5530   1.0000
   4.250   0.5047   0.06646   0.05598  -0.0447   0.5421   1.0000
   4.500   0.5397   0.06627   0.05566  -0.0444   0.5338   1.0000
   4.750   0.5047   0.07142   0.06082  -0.0408   0.5237   1.0000
   5.000   0.5250   0.07247   0.06178  -0.0399   0.5158   1.0000
   5.250   0.5211   0.07567   0.06494  -0.0382   0.5092   1.0000
   5.500   0.4877   0.08118   0.07047  -0.0361   0.5047   1.0000
   5.750   0.4798   0.08478   0.07405  -0.0348   0.5010   1.0000
   6.000   0.5343   0.08371   0.07285  -0.0349   0.4926   1.0000
   6.250   0.5029   0.08930   0.07846  -0.0334   0.4910   1.0000
   6.500   0.5013   0.09315   0.08229  -0.0330   0.4920   1.0000
   6.750   0.3557   0.10855   0.09810  -0.0347   0.6091   1.0000
   7.000   0.3863   0.11220   0.10166  -0.0359   0.6033   1.0000
   7.250   0.3765   0.11276   0.10219  -0.0335   0.5912   1.0000
   7.500   0.4085   0.11650   0.10587  -0.0348   0.5864   1.0000
   7.750   0.3911   0.11708   0.10642  -0.0321   0.5770   1.0000
   8.000   0.4149   0.11993   0.10922  -0.0326   0.5702   1.0000
   8.250   0.4117   0.12173   0.11098  -0.0313   0.5628   1.0000
   8.500   0.4281   0.12394   0.11316  -0.0312   0.5535   1.0000
   8.750   0.4484   0.12747   0.11664  -0.0316   0.5489   1.0000
   9.000   0.4391   0.12808   0.11724  -0.0299   0.5384   1.0000
   9.250   0.4641   0.13140   0.12053  -0.0305   0.5330   1.0000
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