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GOE 491 AIRFOIL (goe491-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 491 AIRFOIL (goe491-il)
Reynolds number: 50,000
Max Cl/Cd: 37.1 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe491-il-50000-n5.txt
Download as CSV file: xf-goe491-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 491 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4755   0.11483   0.10782  -0.0067   1.0000   0.0680
  -8.500  -0.4774   0.11276   0.10585  -0.0090   1.0000   0.0683
  -8.250  -0.4780   0.11045   0.10362  -0.0113   1.0000   0.0685
  -8.000  -0.4753   0.10781   0.10103  -0.0144   1.0000   0.0686
  -7.750  -0.4614   0.10062   0.09389  -0.0103   1.0000   0.0700
  -7.500  -0.4540   0.09661   0.08991  -0.0100   1.0000   0.0714
  -7.250  -0.4481   0.09323   0.08658  -0.0109   1.0000   0.0725
  -7.000  -0.4423   0.08990   0.08325  -0.0121   1.0000   0.0737
  -6.750  -0.4357   0.08660   0.07998  -0.0136   1.0000   0.0750
  -6.500  -0.4283   0.08340   0.07681  -0.0155   1.0000   0.0777
  -6.250  -0.4186   0.08079   0.07417  -0.0198   1.0000   0.0813
  -6.000  -0.4051   0.07826   0.07151  -0.0243   1.0000   0.0823
  -5.750  -0.3990   0.07317   0.06658  -0.0215   1.0000   0.0851
  -5.500  -0.3876   0.06971   0.06312  -0.0217   1.0000   0.0876
  -5.250  -0.3606   0.06447   0.05749  -0.0269   1.0000   0.0551
  -5.000  -0.3510   0.06054   0.05362  -0.0257   1.0000   0.0523
  -4.750  -0.3353   0.05678   0.04976  -0.0262   1.0000   0.0496
  -4.500  -0.3170   0.05289   0.04570  -0.0271   1.0000   0.0473
  -4.250  -0.2967   0.04893   0.04149  -0.0278   1.0000   0.0455
  -4.000  -0.2764   0.04524   0.03751  -0.0279   1.0000   0.0449
  -3.750  -0.2584   0.04267   0.03479  -0.0273   1.0000   0.0477
  -3.500  -0.2376   0.03978   0.03157  -0.0268   1.0000   0.0507
  -3.250  -0.2158   0.03674   0.02813  -0.0262   1.0000   0.0521
  -3.000  -0.1932   0.03369   0.02461  -0.0252   1.0000   0.0532
  -2.750  -0.1690   0.03075   0.02101  -0.0241   1.0000   0.0558
  -2.500  -0.1491   0.02927   0.01943  -0.0231   1.0000   0.0646
  -2.250  -0.1245   0.02687   0.01643  -0.0219   1.0000   0.0701
  -2.000  -0.1007   0.02536   0.01447  -0.0208   1.0000   0.0828
  -1.750  -0.0766   0.02398   0.01276  -0.0200   1.0000   0.0963
  -1.500  -0.0524   0.02282   0.01142  -0.0194   1.0000   0.1116
  -1.250  -0.0256   0.02180   0.01018  -0.0189   1.0000   0.1203
  -1.000   0.0039   0.02097   0.00905  -0.0188   1.0000   0.1265
  -0.750   0.0292   0.02044   0.00837  -0.0183   1.0000   0.1376
  -0.500   0.0532   0.01992   0.00781  -0.0177   1.0000   0.1456
  -0.250   0.0760   0.01956   0.00732  -0.0168   1.0000   0.1532
   0.000   0.0977   0.01924   0.00703  -0.0159   1.0000   0.1640
   0.250   0.1240   0.01896   0.00682  -0.0161   0.9968   0.1869
   0.500   0.1681   0.01812   0.00655  -0.0201   0.9815   0.2832
   0.750   0.2358   0.01656   0.00622  -0.0280   0.9711   1.0000
   1.000   0.2811   0.01667   0.00614  -0.0317   0.9496   1.0000
   1.250   0.3284   0.01672   0.00608  -0.0355   0.9281   1.0000
   1.500   0.3749   0.01672   0.00604  -0.0390   0.9043   1.0000
   1.750   0.4192   0.01672   0.00602  -0.0419   0.8770   1.0000
   2.000   0.4602   0.01672   0.00604  -0.0440   0.8448   1.0000
   2.250   0.4956   0.01676   0.00607  -0.0448   0.8068   1.0000
   2.500   0.5291   0.01683   0.00611  -0.0451   0.7667   1.0000
   2.750   0.5597   0.01698   0.00622  -0.0448   0.7262   1.0000
   3.000   0.5871   0.01724   0.00636  -0.0439   0.6870   1.0000
   3.250   0.6119   0.01758   0.00660  -0.0426   0.6489   1.0000
   3.500   0.6358   0.01797   0.00692  -0.0413   0.6143   1.0000
   3.750   0.6587   0.01840   0.00730  -0.0399   0.5818   1.0000
   4.000   0.6818   0.01885   0.00773  -0.0386   0.5534   1.0000
   4.250   0.7054   0.01934   0.00822  -0.0375   0.5282   1.0000
   4.500   0.7292   0.01984   0.00886  -0.0366   0.5035   1.0000
   4.750   0.7519   0.02036   0.00942  -0.0353   0.4758   1.0000
   5.000   0.7733   0.02091   0.00996  -0.0338   0.4444   1.0000
   5.250   0.7941   0.02146   0.01054  -0.0323   0.4121   1.0000
   5.500   0.8141   0.02198   0.01125  -0.0307   0.3775   1.0000
   5.750   0.8330   0.02245   0.01184  -0.0290   0.3382   1.0000
   6.000   0.8508   0.02294   0.01239  -0.0272   0.2875   1.0000
   6.250   0.8686   0.02370   0.01310  -0.0255   0.2304   1.0000
   6.500   0.8845   0.02513   0.01427  -0.0238   0.1639   1.0000
   6.750   0.8993   0.02711   0.01593  -0.0221   0.1158   1.0000
   7.000   0.9151   0.02890   0.01777  -0.0205   0.0922   1.0000
   7.250   0.9307   0.03082   0.01980  -0.0186   0.0807   1.0000
   7.500   0.9457   0.03273   0.02184  -0.0168   0.0679   1.0000
   7.750   0.9606   0.03495   0.02418  -0.0150   0.0593   1.0000
   8.000   0.9754   0.03709   0.02647  -0.0133   0.0514   1.0000
   8.250   0.9922   0.03996   0.02961  -0.0116   0.0469   1.0000
   8.500   1.0069   0.04261   0.03259  -0.0100   0.0420   1.0000
   8.750   1.0199   0.04599   0.03605  -0.0087   0.0389   1.0000
   9.000   1.0296   0.04961   0.04023  -0.0068   0.0376   1.0000
   9.250   1.0333   0.05333   0.04451  -0.0048   0.0361   1.0000
   9.500   1.0326   0.05708   0.04873  -0.0030   0.0350   1.0000
   9.750   1.0273   0.06087   0.05289  -0.0012   0.0340   1.0000
  10.000   1.0174   0.06468   0.05701   0.0003   0.0333   1.0000
  10.250   1.0019   0.06852   0.06108   0.0018   0.0333   1.0000
  10.500   0.9837   0.07293   0.06569   0.0017   0.0336   1.0000
  10.750   0.9641   0.07822   0.07114  -0.0004   0.0341   1.0000
  11.000   0.9444   0.08470   0.07775  -0.0044   0.0350   1.0000
  11.250   0.9261   0.09214   0.08526  -0.0096   0.0357   1.0000
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