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GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 796 AIRFOIL (goe796-il)
Reynolds number: 50,000
Max Cl/Cd: 35.55 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe796-il-50000-n5.txt
Download as CSV file: xf-goe796-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 796 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3673   0.10368   0.09617  -0.0441   1.0000   0.0663
  -9.250  -0.3718   0.10019   0.09276  -0.0447   1.0000   0.0656
  -9.000  -0.3787   0.09675   0.08942  -0.0450   1.0000   0.0651
  -8.750  -0.3885   0.09341   0.08619  -0.0450   1.0000   0.0648
  -8.500  -0.4017   0.09022   0.08312  -0.0447   1.0000   0.0645
  -8.250  -0.4203   0.08719   0.08023  -0.0437   1.0000   0.0641
  -8.000  -0.4419   0.08388   0.07705  -0.0430   1.0000   0.0637
  -7.750  -0.4606   0.07994   0.07319  -0.0431   1.0000   0.0633
  -7.500  -0.4781   0.07571   0.06900  -0.0432   1.0000   0.0630
  -7.250  -0.4927   0.07139   0.06466  -0.0432   1.0000   0.0630
  -7.000  -0.5030   0.06726   0.06047  -0.0430   1.0000   0.0632
  -6.750  -0.5091   0.06333   0.05642  -0.0427   1.0000   0.0639
  -6.500  -0.4959   0.05790   0.05067  -0.0466   0.9948   0.0655
  -6.250  -0.4758   0.05174   0.04397  -0.0514   0.9874   0.0676
  -6.000  -0.4529   0.04536   0.03675  -0.0554   0.9810   0.0702
  -5.750  -0.4258   0.04216   0.03315  -0.0576   0.9745   0.0728
  -5.500  -0.3956   0.04008   0.03077  -0.0595   0.9688   0.0769
  -5.250  -0.3668   0.03734   0.02741  -0.0612   0.9623   0.0842
  -5.000  -0.3326   0.03625   0.02600  -0.0634   0.9571   0.0946
  -4.750  -0.3063   0.03579   0.02552  -0.0641   0.9492   0.1056
  -4.500  -0.2728   0.03482   0.02432  -0.0660   0.9440   0.1185
  -4.250  -0.2438   0.03337   0.02230  -0.0667   0.9371   0.1274
  -4.000  -0.2123   0.03250   0.02144  -0.0680   0.9312   0.1359
  -3.750  -0.1759   0.03134   0.01987  -0.0698   0.9268   0.1439
  -3.500  -0.1504   0.03071   0.01924  -0.0698   0.9191   0.1515
  -3.250  -0.1153   0.03003   0.01839  -0.0714   0.9141   0.1625
  -3.000  -0.0853   0.02949   0.01768  -0.0720   0.9078   0.1725
  -2.750  -0.0545   0.02901   0.01718  -0.0728   0.9015   0.1831
  -2.500  -0.0172   0.02858   0.01667  -0.0747   0.8972   0.1994
  -2.250   0.0072   0.02836   0.01642  -0.0744   0.8894   0.2153
  -2.000   0.0413   0.02802   0.01609  -0.0758   0.8841   0.2383
  -1.750   0.0712   0.02769   0.01584  -0.0765   0.8780   0.2632
  -1.500   0.0994   0.02735   0.01562  -0.0769   0.8713   0.2935
  -1.250   0.1347   0.02670   0.01532  -0.0785   0.8670   0.3568
  -1.000   0.1539   0.02611   0.01539  -0.0773   0.8589   0.4759
  -0.750   0.2117   0.02494   0.01546  -0.0812   0.8560   1.0000
  -0.500   0.2483   0.02502   0.01521  -0.0828   0.8512   1.0000
  -0.250   0.2663   0.02539   0.01538  -0.0814   0.8412   1.0000
   0.000   0.3026   0.02545   0.01520  -0.0829   0.8362   1.0000
   0.250   0.3212   0.02583   0.01542  -0.0815   0.8260   1.0000
   0.500   0.3533   0.02587   0.01529  -0.0821   0.8182   1.0000
   0.750   0.3830   0.02587   0.01515  -0.0821   0.8082   1.0000
   1.000   0.4088   0.02594   0.01509  -0.0815   0.7968   1.0000
   1.250   0.4432   0.02577   0.01480  -0.0821   0.7883   1.0000
   1.500   0.4698   0.02585   0.01479  -0.0816   0.7779   1.0000
   1.750   0.4942   0.02604   0.01492  -0.0808   0.7679   1.0000
   2.000   0.5275   0.02596   0.01476  -0.0813   0.7607   1.0000
   2.250   0.5487   0.02629   0.01506  -0.0802   0.7498   1.0000
   2.500   0.5827   0.02618   0.01489  -0.0807   0.7431   1.0000
   2.750   0.6044   0.02649   0.01519  -0.0796   0.7318   1.0000
   3.000   0.6288   0.02671   0.01542  -0.0788   0.7214   1.0000
   3.250   0.6617   0.02660   0.01529  -0.0791   0.7135   1.0000
   3.500   0.6825   0.02696   0.01567  -0.0778   0.7014   1.0000
   3.750   0.7075   0.02715   0.01589  -0.0771   0.6904   1.0000
   4.000   0.7401   0.02702   0.01577  -0.0772   0.6817   1.0000
   4.500   0.7833   0.02766   0.01652  -0.0748   0.6559   1.0000
   4.750   0.8082   0.02784   0.01675  -0.0740   0.6438   1.0000
   5.000   0.8374   0.02782   0.01677  -0.0736   0.6328   1.0000
   5.250   0.8623   0.02796   0.01698  -0.0727   0.6196   1.0000
   5.500   0.8847   0.02816   0.01725  -0.0714   0.6048   1.0000
   5.750   0.9078   0.02828   0.01742  -0.0702   0.5894   1.0000
   6.000   0.9315   0.02831   0.01749  -0.0689   0.5732   1.0000
   6.250   0.9515   0.02849   0.01773  -0.0672   0.5550   1.0000
   6.500   0.9706   0.02873   0.01802  -0.0654   0.5364   1.0000
   6.750   0.9914   0.02895   0.01829  -0.0639   0.5189   1.0000
   7.000   1.0127   0.02924   0.01861  -0.0625   0.5025   1.0000
   7.250   1.0341   0.02958   0.01903  -0.0613   0.4867   1.0000
   7.500   1.0551   0.02995   0.01945  -0.0599   0.4708   1.0000
   7.750   1.0756   0.03037   0.01990  -0.0585   0.4546   1.0000
   8.000   1.0955   0.03084   0.02041  -0.0571   0.4383   1.0000
   8.250   1.1148   0.03136   0.02097  -0.0556   0.4216   1.0000
   8.500   1.1331   0.03191   0.02150  -0.0539   0.4041   1.0000
   8.750   1.1464   0.03270   0.02235  -0.0518   0.3856   1.0000
   9.000   1.1583   0.03353   0.02320  -0.0495   0.3665   1.0000
   9.250   1.1686   0.03441   0.02410  -0.0470   0.3479   1.0000
   9.500   1.1783   0.03538   0.02507  -0.0445   0.3297   1.0000
   9.750   1.1873   0.03644   0.02614  -0.0421   0.3122   1.0000
  10.000   1.1952   0.03762   0.02735  -0.0398   0.2954   1.0000
  10.250   1.2014   0.03893   0.02872  -0.0374   0.2792   1.0000
  10.500   1.2064   0.04037   0.03025  -0.0352   0.2635   1.0000
  10.750   1.2117   0.04187   0.03184  -0.0331   0.2489   1.0000
  11.000   1.2167   0.04344   0.03346  -0.0312   0.2352   1.0000
  11.250   1.2212   0.04513   0.03523  -0.0294   0.2223   1.0000
  11.500   1.2259   0.04694   0.03712  -0.0277   0.2102   1.0000
  11.750   1.2304   0.04883   0.03908  -0.0262   0.1989   1.0000
  12.000   1.2351   0.05076   0.04102  -0.0247   0.1884   1.0000
  12.250   1.2417   0.05256   0.04274  -0.0233   0.1785   1.0000
  12.500   1.2450   0.05488   0.04526  -0.0221   0.1686   1.0000
  12.750   1.2480   0.05721   0.04765  -0.0209   0.1591   1.0000
  13.000   1.2514   0.05935   0.04973  -0.0197   0.1495   1.0000
  13.250   1.2443   0.06276   0.05342  -0.0190   0.1410   1.0000
  13.500   1.2416   0.06556   0.05622  -0.0183   0.1328   1.0000
  13.750   1.2330   0.06929   0.06019  -0.0181   0.1253   1.0000
  14.000   1.2286   0.07252   0.06348  -0.0179   0.1185   1.0000
  14.250   1.2198   0.07663   0.06783  -0.0182   0.1122   1.0000
  14.500   1.2174   0.07977   0.07096  -0.0181   0.1065   1.0000
  14.750   1.2060   0.08472   0.07623  -0.0190   0.1012   1.0000
  15.000   1.2023   0.08829   0.07984  -0.0194   0.0961   1.0000
  15.250   1.1930   0.09315   0.08489  -0.0205   0.0918   1.0000
  15.500   1.1796   0.09893   0.09091  -0.0223   0.0879   1.0000
  15.750   1.1802   0.10188   0.09379  -0.0228   0.0830   1.0000
  16.000   1.1636   0.10868   0.10083  -0.0255   0.0801   1.0000
  16.250   1.1405   0.11728   0.10972  -0.0296   0.0781   1.0000
  16.500   1.1114   0.12785   0.12051  -0.0351   0.0770   1.0000
  16.750   1.0593   0.14566   0.13850  -0.0454   0.0776   1.0000
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