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GOE 477 AIRFOIL (goe477-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 477 AIRFOIL (goe477-il)
Reynolds number: 50,000
Max Cl/Cd: 36.51 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe477-il-50000-n5.txt
Download as CSV file: xf-goe477-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 477 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3515   0.11197   0.10598  -0.0262   1.0000   0.0942
  -8.000  -0.3575   0.11009   0.10416  -0.0259   0.9987   0.0971
  -7.750  -0.3650   0.10853   0.10267  -0.0309   0.9914   0.1009
  -7.500  -0.3644   0.10566   0.09982  -0.0361   0.9846   0.1014
  -7.000  -0.3457   0.09207   0.08613  -0.0442   0.9747   0.0608
  -6.750  -0.3355   0.08827   0.08231  -0.0458   0.9699   0.0598
  -6.500  -0.3254   0.08397   0.07799  -0.0498   0.9647   0.0596
  -6.250  -0.3150   0.07958   0.07354  -0.0539   0.9592   0.0597
  -6.000  -0.3017   0.07465   0.06851  -0.0591   0.9540   0.0603
  -5.750  -0.2881   0.06961   0.06331  -0.0636   0.9486   0.0607
  -5.500  -0.2667   0.06404   0.05750  -0.0688   0.9446   0.0609
  -5.000  -0.2350   0.05774   0.05092  -0.0715   0.9353   0.0655
  -4.750  -0.2081   0.05335   0.04617  -0.0753   0.9320   0.0684
  -4.500  -0.1893   0.04904   0.04138  -0.0771   0.9270   0.0710
  -4.250  -0.1641   0.04522   0.03700  -0.0792   0.9231   0.0756
  -4.000  -0.1366   0.04306   0.03454  -0.0806   0.9198   0.0805
  -3.750  -0.1073   0.03993   0.03054  -0.0821   0.9165   0.0876
  -3.500  -0.0874   0.03885   0.02941  -0.0816   0.9118   0.0928
  -3.250  -0.0585   0.03709   0.02700  -0.0823   0.9081   0.1010
  -3.000  -0.0287   0.03595   0.02568  -0.0833   0.9049   0.1079
  -2.750  -0.0006   0.03494   0.02422  -0.0837   0.9012   0.1158
  -2.500   0.0230   0.03401   0.02296  -0.0832   0.8964   0.1194
  -2.250   0.0518   0.03342   0.02223  -0.0836   0.8923   0.1256
  -2.000   0.0847   0.03294   0.02147  -0.0848   0.8889   0.1351
  -1.750   0.1091   0.03256   0.02096  -0.0843   0.8840   0.1398
  -1.500   0.1363   0.03225   0.02039  -0.0842   0.8788   0.1454
  -1.250   0.1720   0.03188   0.01991  -0.0856   0.8742   0.1530
  -1.000   0.2010   0.03161   0.01951  -0.0858   0.8662   0.1633
  -0.750   0.2399   0.03114   0.01902  -0.0875   0.8587   0.1809
  -0.500   0.2684   0.03080   0.01877  -0.0876   0.8487   0.2131
  -0.250   0.3097   0.02994   0.01836  -0.0900   0.8423   0.3047
   0.250   0.3820   0.02829   0.01811  -0.0924   0.8277   1.0000
   0.500   0.4045   0.02860   0.01819  -0.0915   0.8178   1.0000
   0.750   0.4440   0.02861   0.01796  -0.0931   0.8111   1.0000
   1.000   0.4647   0.02888   0.01809  -0.0918   0.7997   1.0000
   1.250   0.4965   0.02890   0.01796  -0.0920   0.7903   1.0000
   1.500   0.5322   0.02874   0.01767  -0.0927   0.7807   1.0000
   1.750   0.5559   0.02875   0.01759  -0.0915   0.7675   1.0000
   2.000   0.5809   0.02866   0.01743  -0.0904   0.7541   1.0000
   2.250   0.6058   0.02852   0.01723  -0.0893   0.7402   1.0000
   2.500   0.6296   0.02838   0.01704  -0.0880   0.7260   1.0000
   2.750   0.6526   0.02821   0.01686  -0.0865   0.7110   1.0000
   3.000   0.6751   0.02803   0.01666  -0.0850   0.6953   1.0000
   3.250   0.6981   0.02779   0.01643  -0.0835   0.6792   1.0000
   3.500   0.7217   0.02752   0.01617  -0.0820   0.6627   1.0000
   4.000   0.7709   0.02692   0.01561  -0.0793   0.6261   1.0000
   4.250   0.7952   0.02672   0.01540  -0.0780   0.6040   1.0000
   4.500   0.8272   0.02622   0.01488  -0.0776   0.5823   1.0000
   4.750   0.8543   0.02604   0.01466  -0.0766   0.5557   1.0000
   5.000   0.8847   0.02583   0.01433  -0.0761   0.5287   1.0000
   5.250   0.9150   0.02579   0.01413  -0.0757   0.5023   1.0000
   5.500   0.9406   0.02609   0.01428  -0.0749   0.4786   1.0000
   5.750   0.9656   0.02652   0.01454  -0.0741   0.4584   1.0000
   6.000   0.9894   0.02710   0.01500  -0.0733   0.4405   1.0000
   6.500   1.0361   0.02848   0.01629  -0.0720   0.4104   1.0000
   6.750   1.0596   0.02923   0.01711  -0.0715   0.3977   1.0000
   7.000   1.0855   0.02998   0.01792  -0.0713   0.3873   1.0000
   7.250   1.1137   0.03072   0.01872  -0.0714   0.3783   1.0000
   7.500   1.1385   0.03155   0.01976  -0.0712   0.3697   1.0000
   7.750   1.1674   0.03232   0.02063  -0.0715   0.3622   1.0000
   8.000   1.1907   0.03324   0.02178  -0.0711   0.3550   1.0000
   8.250   1.2159   0.03413   0.02289  -0.0709   0.3485   1.0000
   8.500   1.2442   0.03502   0.02397  -0.0711   0.3433   1.0000
   8.750   1.2584   0.03602   0.02526  -0.0695   0.3349   1.0000
   9.000   1.2674   0.03672   0.02608  -0.0669   0.3223   1.0000
   9.250   1.2694   0.03735   0.02678  -0.0633   0.3078   1.0000
   9.500   1.2698   0.03803   0.02755  -0.0596   0.2946   1.0000
   9.750   1.2669   0.03888   0.02847  -0.0558   0.2809   1.0000
  10.000   1.2633   0.04002   0.02976  -0.0524   0.2677   1.0000
  10.250   1.2585   0.04140   0.03130  -0.0493   0.2536   1.0000
  10.500   1.2534   0.04299   0.03303  -0.0465   0.2383   1.0000
  10.750   1.2472   0.04490   0.03507  -0.0441   0.2198   1.0000
  11.000   1.2408   0.04717   0.03754  -0.0421   0.1947   1.0000
  11.250   1.2349   0.04984   0.04030  -0.0405   0.1269   1.0000
  11.500   1.2125   0.05430   0.04400  -0.0391   0.0834   1.0000
  11.750   1.1972   0.05893   0.04848  -0.0384   0.0723   1.0000
  12.000   1.1830   0.06372   0.05331  -0.0382   0.0665   1.0000
  12.250   1.1699   0.06862   0.05837  -0.0384   0.0630   1.0000
  12.500   1.1556   0.07400   0.06390  -0.0393   0.0608   1.0000
  12.750   1.1415   0.07964   0.06967  -0.0406   0.0591   1.0000
  13.000   1.1303   0.08511   0.07534  -0.0421   0.0572   1.0000
  13.250   1.1196   0.09067   0.08106  -0.0437   0.0554   1.0000
  13.500   1.1100   0.09613   0.08664  -0.0454   0.0536   1.0000
  13.750   1.1017   0.10134   0.09193  -0.0470   0.0518   1.0000
  14.000   1.0946   0.10621   0.09687  -0.0485   0.0499   1.0000
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