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GOE 496 AIRFOIL (goe496-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 496 AIRFOIL (goe496-il)
Reynolds number: 200,000
Max Cl/Cd: 89.6 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe496-il-200000.txt
Download as CSV file: xf-goe496-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 496 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3306   0.10335   0.09983  -0.0366   1.0000   0.0655
  -8.750  -0.3585   0.10233   0.09894  -0.0370   1.0000   0.0663
  -8.500  -0.3825   0.10141   0.09812  -0.0353   1.0000   0.0665
  -8.250  -0.3653   0.09693   0.09364  -0.0321   1.0000   0.0679
  -8.000  -0.3605   0.09548   0.09222  -0.0288   1.0000   0.0692
  -7.750  -0.3682   0.09441   0.09120  -0.0259   1.0000   0.0703
  -7.500  -0.3518   0.09117   0.08795  -0.0299   0.9963   0.0734
  -7.250  -0.3392   0.08252   0.07932  -0.0520   0.9838   0.0788
  -7.000  -0.3181   0.08058   0.07736  -0.0483   0.9814   0.0802
  -6.750  -0.2936   0.07842   0.07517  -0.0490   0.9765   0.0836
  -6.500  -0.2632   0.06820   0.06488  -0.0740   0.9642   0.0917
  -6.250  -0.2253   0.03923   0.03494  -0.1100   0.9571   0.0676
  -6.000  -0.1981   0.03419   0.02948  -0.1141   0.9492   0.0656
  -5.750  -0.1603   0.02831   0.02296  -0.1202   0.9457   0.0643
  -5.500  -0.1192   0.02448   0.01848  -0.1248   0.9434   0.0644
  -5.250  -0.0876   0.02267   0.01623  -0.1262   0.9372   0.0658
  -5.000  -0.0512   0.02099   0.01418  -0.1282   0.9327   0.0668
  -4.750  -0.0120   0.01910   0.01207  -0.1309   0.9301   0.0685
  -4.500   0.0299   0.01806   0.01096  -0.1337   0.9282   0.0709
  -4.250   0.0590   0.01748   0.01030  -0.1339   0.9207   0.0741
  -4.000   0.0981   0.01670   0.00937  -0.1359   0.9171   0.0777
  -3.750   0.1382   0.01578   0.00849  -0.1382   0.9144   0.0822
  -3.500   0.1726   0.01528   0.00795  -0.1392   0.9090   0.0884
  -3.250   0.2052   0.01477   0.00746  -0.1400   0.9026   0.0980
  -3.000   0.2439   0.01419   0.00686  -0.1418   0.8989   0.1195
  -2.750   0.2738   0.01369   0.00644  -0.1421   0.8914   0.1501
  -2.500   0.3076   0.01328   0.00608  -0.1432   0.8855   0.1721
  -2.250   0.3410   0.01297   0.00579  -0.1440   0.8794   0.1894
  -2.000   0.3705   0.01274   0.00557  -0.1441   0.8711   0.2049
  -1.750   0.4034   0.01247   0.00533  -0.1448   0.8647   0.2246
  -1.500   0.4317   0.01226   0.00522  -0.1447   0.8555   0.2497
  -1.250   0.4620   0.01203   0.00509  -0.1449   0.8476   0.2916
  -1.000   0.4910   0.01179   0.00502  -0.1449   0.8388   0.3475
  -0.750   0.5188   0.01168   0.00501  -0.1446   0.8295   0.3944
  -0.500   0.5489   0.01156   0.00492  -0.1447   0.8214   0.4334
  -0.250   0.5751   0.01152   0.00494  -0.1442   0.8109   0.4671
   0.000   0.6038   0.01142   0.00488  -0.1440   0.8025   0.5020
   0.250   0.6302   0.01131   0.00489  -0.1435   0.7923   0.5417
   0.500   0.6561   0.01118   0.00496  -0.1428   0.7826   0.5992
   0.750   0.6820   0.01093   0.00493  -0.1419   0.7738   0.6967
   1.000   0.7081   0.01041   0.00485  -0.1408   0.7622   1.0000
   1.250   0.7355   0.01051   0.00482  -0.1404   0.7508   1.0000
   1.500   0.7635   0.01059   0.00477  -0.1401   0.7398   1.0000
   1.750   0.7905   0.01069   0.00477  -0.1396   0.7281   1.0000
   2.000   0.8166   0.01080   0.00481  -0.1390   0.7156   1.0000
   2.250   0.8431   0.01090   0.00484  -0.1385   0.7034   1.0000
   2.500   0.8700   0.01102   0.00488  -0.1380   0.6922   1.0000
   2.750   0.8967   0.01116   0.00496  -0.1376   0.6814   1.0000
   3.000   0.9227   0.01132   0.00510  -0.1370   0.6704   1.0000
   3.250   0.9494   0.01148   0.00521  -0.1366   0.6602   1.0000
   3.500   0.9760   0.01163   0.00532  -0.1361   0.6495   1.0000
   3.750   1.0013   0.01179   0.00549  -0.1355   0.6377   1.0000
   4.000   1.0273   0.01197   0.00566  -0.1349   0.6269   1.0000
   4.250   1.0535   0.01216   0.00581  -0.1344   0.6159   1.0000
   4.500   1.0787   0.01233   0.00598  -0.1337   0.6035   1.0000
   4.750   1.1034   0.01252   0.00619  -0.1329   0.5905   1.0000
   5.000   1.1282   0.01273   0.00641  -0.1321   0.5776   1.0000
   5.250   1.1528   0.01294   0.00663  -0.1313   0.5640   1.0000
   5.500   1.1767   0.01316   0.00685  -0.1304   0.5489   1.0000
   5.750   1.2001   0.01340   0.00710  -0.1294   0.5326   1.0000
   6.000   1.2230   0.01365   0.00737  -0.1282   0.5150   1.0000
   6.250   1.2442   0.01395   0.00760  -0.1268   0.4929   1.0000
   6.500   1.2630   0.01426   0.00786  -0.1249   0.4630   1.0000
   6.750   1.2802   0.01466   0.00818  -0.1228   0.4267   1.0000
   7.000   1.2955   0.01523   0.00857  -0.1205   0.3865   1.0000
   7.250   1.3099   0.01592   0.00906  -0.1182   0.3465   1.0000
   7.500   1.3235   0.01671   0.00965  -0.1158   0.3125   1.0000
   7.750   1.3381   0.01748   0.01029  -0.1136   0.2861   1.0000
   8.000   1.3523   0.01827   0.01098  -0.1114   0.2652   1.0000
   8.250   1.3674   0.01899   0.01166  -0.1094   0.2465   1.0000
   8.500   1.3813   0.01970   0.01235  -0.1072   0.2278   1.0000
   8.750   1.3931   0.02045   0.01307  -0.1046   0.2086   1.0000
   9.000   1.4037   0.02125   0.01383  -0.1020   0.1852   1.0000
   9.250   1.4096   0.02235   0.01476  -0.0988   0.1426   1.0000
   9.500   1.4030   0.02443   0.01636  -0.0942   0.0876   1.0000
   9.750   1.3986   0.02652   0.01827  -0.0902   0.0670   1.0000
  10.000   1.3963   0.02852   0.02023  -0.0866   0.0577   1.0000
  10.250   1.3993   0.03021   0.02200  -0.0839   0.0519   1.0000
  10.500   1.3959   0.03248   0.02427  -0.0808   0.0481   1.0000
  10.750   1.4016   0.03415   0.02607  -0.0788   0.0447   1.0000
  11.000   1.4047   0.03609   0.02805  -0.0768   0.0420   1.0000
  11.250   1.4018   0.03877   0.03074  -0.0745   0.0400   1.0000
  11.500   1.4081   0.04070   0.03279  -0.0729   0.0385   1.0000
  11.750   1.4145   0.04270   0.03490  -0.0714   0.0370   1.0000
  12.000   1.4211   0.04474   0.03701  -0.0700   0.0355   1.0000
  12.250   1.4276   0.04683   0.03914  -0.0688   0.0341   1.0000
  12.500   1.4385   0.04929   0.04153  -0.0674   0.0323   1.0000
  12.750   1.4456   0.05130   0.04373  -0.0664   0.0314   1.0000
  13.000   1.4552   0.05342   0.04602  -0.0653   0.0305   1.0000
  13.250   1.4650   0.05565   0.04839  -0.0643   0.0297   1.0000
  13.500   1.4742   0.05798   0.05086  -0.0634   0.0289   1.0000
  13.750   1.4821   0.06049   0.05351  -0.0625   0.0282   1.0000
  14.000   1.4890   0.06310   0.05622  -0.0618   0.0276   1.0000
  14.250   1.4989   0.06576   0.05894  -0.0612   0.0268   1.0000
  14.500   1.5084   0.06974   0.06310  -0.0605   0.0260   1.0000
  14.750   1.4991   0.07347   0.06711  -0.0602   0.0258   1.0000
  15.000   1.4895   0.07759   0.07150  -0.0602   0.0256   1.0000
  15.250   1.4791   0.08211   0.07629  -0.0606   0.0254   1.0000
  15.500   1.4675   0.08709   0.08153  -0.0614   0.0252   1.0000
  15.750   1.4542   0.09249   0.08719  -0.0627   0.0252   1.0000
  16.000   1.4392   0.09837   0.09332  -0.0645   0.0252   1.0000
  16.250   1.4229   0.10470   0.09990  -0.0670   0.0252   1.0000
  16.500   1.4052   0.11151   0.10694  -0.0701   0.0252   1.0000
  16.750   1.3869   0.11879   0.11445  -0.0739   0.0253   1.0000
  17.000   1.3677   0.12659   0.12247  -0.0784   0.0254   1.0000
  17.250   1.3485   0.13483   0.13090  -0.0835   0.0256   1.0000
  17.500   1.3285   0.14370   0.13994  -0.0893   0.0258   1.0000
  17.750   1.3095   0.15286   0.14926  -0.0954   0.0260   1.0000
  18.000   1.2926   0.16205   0.15862  -0.1019   0.0263   1.0000
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