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GOE 769 AIRFOIL (goe769-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 769 AIRFOIL (goe769-il)
Reynolds number: 200,000
Max Cl/Cd: 61.81 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe769-il-200000-n5.txt
Download as CSV file: xf-goe769-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 769 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2350   0.11041   0.10671  -0.0207   1.0000   0.0481
  -9.750  -0.2300   0.10747   0.10382  -0.0217   1.0000   0.0485
  -9.250  -0.2451   0.09683   0.09321  -0.0274   1.0000   0.0410
  -9.000  -0.2126   0.09332   0.08967  -0.0322   0.9278   0.0404
  -8.750  -0.1734   0.08739   0.08354  -0.0428   0.8622   0.0392
  -8.500  -0.1616   0.08237   0.07831  -0.0482   0.8153   0.0382
  -8.250  -0.1856   0.07370   0.06952  -0.0537   0.7901   0.0368
  -7.250  -0.3126   0.02927   0.02303  -0.0773   0.7317   0.0368
  -7.000  -0.2949   0.02742   0.02086  -0.0766   0.7172   0.0370
  -6.750  -0.2740   0.02619   0.01943  -0.0759   0.7040   0.0373
  -6.500  -0.2523   0.02505   0.01805  -0.0751   0.6920   0.0376
  -6.250  -0.2297   0.02395   0.01676  -0.0744   0.6801   0.0381
  -6.000  -0.2067   0.02291   0.01547  -0.0737   0.6697   0.0385
  -5.750  -0.1830   0.02190   0.01423  -0.0730   0.6584   0.0390
  -5.500  -0.1588   0.02100   0.01308  -0.0723   0.6483   0.0397
  -5.250  -0.1339   0.02014   0.01197  -0.0716   0.6377   0.0405
  -5.000  -0.1086   0.01944   0.01107  -0.0709   0.6285   0.0414
  -4.750  -0.0828   0.01895   0.01055  -0.0703   0.6180   0.0420
  -4.500  -0.0569   0.01849   0.00999  -0.0697   0.6082   0.0428
  -4.250  -0.0307   0.01797   0.00937  -0.0691   0.5972   0.0436
  -4.000  -0.0046   0.01748   0.00874  -0.0684   0.5875   0.0446
  -3.750   0.0219   0.01700   0.00813  -0.0678   0.5769   0.0456
  -3.500   0.0481   0.01662   0.00771  -0.0671   0.5670   0.0466
  -3.250   0.0747   0.01630   0.00735  -0.0666   0.5553   0.0478
  -3.000   0.1013   0.01601   0.00698  -0.0660   0.5443   0.0496
  -2.750   0.1277   0.01572   0.00662  -0.0653   0.5322   0.0516
  -2.500   0.1543   0.01550   0.00636  -0.0647   0.5185   0.0539
  -2.250   0.1807   0.01526   0.00604  -0.0641   0.5043   0.0567
  -2.000   0.2069   0.01509   0.00580  -0.0634   0.4909   0.0597
  -1.750   0.2336   0.01490   0.00558  -0.0629   0.4783   0.0637
  -1.500   0.2603   0.01478   0.00541  -0.0623   0.4673   0.0694
  -1.250   0.2869   0.01471   0.00528  -0.0617   0.4561   0.0764
  -1.000   0.3137   0.01464   0.00519  -0.0612   0.4459   0.0840
  -0.750   0.3402   0.01461   0.00512  -0.0606   0.4363   0.0919
  -0.500   0.3671   0.01457   0.00507  -0.0601   0.4268   0.1005
  -0.250   0.3935   0.01457   0.00503  -0.0595   0.4176   0.1096
   0.000   0.4204   0.01455   0.00501  -0.0591   0.4090   0.1200
   0.250   0.4468   0.01455   0.00498  -0.0585   0.4006   0.1311
   0.500   0.4733   0.01454   0.00496  -0.0580   0.3927   0.1427
   0.750   0.4997   0.01451   0.00496  -0.0574   0.3843   0.1553
   1.000   0.5257   0.01451   0.00496  -0.0569   0.3769   0.1714
   1.500   0.5775   0.01440   0.00505  -0.0557   0.3619   0.2475
   1.750   0.6025   0.01423   0.00514  -0.0551   0.3547   0.3343
   2.000   0.6207   0.01342   0.00527  -0.0532   0.3476   0.6343
   2.500   0.7132   0.01324   0.00551  -0.0597   0.3296   1.0000
   2.750   0.7375   0.01347   0.00561  -0.0588   0.3229   1.0000
   3.000   0.7626   0.01366   0.00574  -0.0580   0.3154   1.0000
   3.250   0.7870   0.01390   0.00586  -0.0572   0.3081   1.0000
   3.500   0.8117   0.01412   0.00602  -0.0564   0.3013   1.0000
   3.750   0.8364   0.01436   0.00618  -0.0556   0.2943   1.0000
   4.000   0.8603   0.01464   0.00636  -0.0548   0.2879   1.0000
   4.250   0.8852   0.01487   0.00655  -0.0540   0.2808   1.0000
   4.500   0.9090   0.01515   0.00675  -0.0532   0.2741   1.0000
   4.750   0.9332   0.01543   0.00698  -0.0524   0.2681   1.0000
   5.000   0.9572   0.01571   0.00722  -0.0516   0.2620   1.0000
   5.250   0.9803   0.01605   0.00746  -0.0507   0.2565   1.0000
   5.500   1.0043   0.01634   0.00774  -0.0499   0.2511   1.0000
   5.750   1.0276   0.01666   0.00802  -0.0491   0.2457   1.0000
   6.000   1.0499   0.01704   0.00832  -0.0481   0.2412   1.0000
   6.250   1.0731   0.01738   0.00865  -0.0473   0.2369   1.0000
   6.500   1.0959   0.01773   0.00899  -0.0464   0.2325   1.0000
   6.750   1.1178   0.01813   0.00934  -0.0454   0.2283   1.0000
   7.000   1.1386   0.01858   0.00972  -0.0443   0.2247   1.0000
   7.250   1.1611   0.01894   0.01011  -0.0435   0.2211   1.0000
   7.500   1.1827   0.01934   0.01052  -0.0425   0.2177   1.0000
   7.750   1.2033   0.01978   0.01095  -0.0414   0.2144   1.0000
   8.000   1.2227   0.02027   0.01139  -0.0402   0.2113   1.0000
   8.250   1.2423   0.02076   0.01187  -0.0390   0.2084   1.0000
   8.500   1.2624   0.02119   0.01235  -0.0379   0.2053   1.0000
   8.750   1.2815   0.02166   0.01286  -0.0366   0.2024   1.0000
   9.000   1.2993   0.02217   0.01337  -0.0353   0.1998   1.0000
   9.250   1.3153   0.02273   0.01391  -0.0337   0.1974   1.0000
   9.500   1.3292   0.02336   0.01450  -0.0318   0.1951   1.0000
   9.750   1.3447   0.02389   0.01510  -0.0301   0.1927   1.0000
  10.000   1.3592   0.02446   0.01574  -0.0284   0.1902   1.0000
  10.250   1.3728   0.02510   0.01642  -0.0268   0.1877   1.0000
  10.500   1.3856   0.02580   0.01716  -0.0251   0.1855   1.0000
  10.750   1.3977   0.02658   0.01795  -0.0235   0.1835   1.0000
  11.000   1.4094   0.02745   0.01880  -0.0220   0.1816   1.0000
  11.250   1.4216   0.02833   0.01973  -0.0207   0.1798   1.0000
  11.500   1.4332   0.02924   0.02075  -0.0195   0.1777   1.0000
  11.750   1.4439   0.03026   0.02184  -0.0183   0.1755   1.0000
  12.000   1.4539   0.03135   0.02300  -0.0173   0.1734   1.0000
  12.250   1.4632   0.03254   0.02424  -0.0163   0.1715   1.0000
  12.500   1.4720   0.03382   0.02554  -0.0154   0.1697   1.0000
  12.750   1.4814   0.03512   0.02684  -0.0146   0.1681   1.0000
  13.000   1.4903   0.03652   0.02831  -0.0139   0.1666   1.0000
  13.250   1.4975   0.03809   0.03001  -0.0133   0.1649   1.0000
  13.500   1.5039   0.03977   0.03180  -0.0129   0.1630   1.0000
  13.750   1.5097   0.04154   0.03366  -0.0125   0.1612   1.0000
  14.000   1.5151   0.04339   0.03558  -0.0122   0.1595   1.0000
  14.250   1.5201   0.04529   0.03753  -0.0120   0.1579   1.0000
  14.500   1.5255   0.04717   0.03943  -0.0118   0.1563   1.0000
  14.750   1.5329   0.04888   0.04114  -0.0115   0.1549   1.0000
  15.000   1.5332   0.05143   0.04385  -0.0117   0.1535   1.0000
  15.250   1.5331   0.05408   0.04665  -0.0119   0.1520   1.0000
  15.500   1.5326   0.05684   0.04953  -0.0123   0.1504   1.0000
  15.750   1.5318   0.05967   0.05248  -0.0127   0.1489   1.0000
  16.000   1.5308   0.06262   0.05552  -0.0133   0.1474   1.0000
  16.250   1.5303   0.06556   0.05854  -0.0140   0.1460   1.0000
  16.500   1.5331   0.06809   0.06110  -0.0145   0.1446   1.0000
  16.750   1.5404   0.07002   0.06302  -0.0147   0.1433   1.0000
  17.000   1.5304   0.07447   0.06765  -0.0162   0.1419   1.0000
  17.250   1.5154   0.07981   0.07319  -0.0183   0.1404   1.0000
  17.500   1.5002   0.08531   0.07888  -0.0205   0.1388   1.0000
  17.750   1.4855   0.09090   0.08462  -0.0228   0.1372   1.0000
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