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GOE 546 AIRFOIL (goe546-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 546 AIRFOIL (goe546-il)
Reynolds number: 50,000
Max Cl/Cd: 38.61 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe546-il-50000-n5.txt
Download as CSV file: xf-goe546-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 546 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4048   0.09656   0.08948  -0.0458   1.0000   0.0700
  -8.750  -0.4099   0.09334   0.08636  -0.0456   1.0000   0.0698
  -8.500  -0.4191   0.09031   0.08344  -0.0451   1.0000   0.0697
  -8.250  -0.4283   0.08741   0.08065  -0.0443   1.0000   0.0695
  -8.000  -0.4369   0.08403   0.07736  -0.0444   1.0000   0.0692
  -7.750  -0.4457   0.08048   0.07387  -0.0447   1.0000   0.0690
  -7.500  -0.4541   0.07672   0.07015  -0.0451   1.0000   0.0687
  -7.250  -0.4613   0.07290   0.06633  -0.0454   1.0000   0.0683
  -7.000  -0.4666   0.06898   0.06238  -0.0458   1.0000   0.0678
  -6.750  -0.4699   0.06480   0.05810  -0.0465   1.0000   0.0673
  -6.500  -0.4701   0.06043   0.05354  -0.0474   1.0000   0.0669
  -6.250  -0.4669   0.05590   0.04870  -0.0487   1.0000   0.0674
  -6.000  -0.4594   0.05137   0.04369  -0.0501   1.0000   0.0686
  -5.750  -0.4471   0.04741   0.03911  -0.0511   1.0000   0.0699
  -5.500  -0.4323   0.04411   0.03543  -0.0512   1.0000   0.0707
  -5.250  -0.4138   0.04128   0.03229  -0.0514   0.9994   0.0716
  -5.000  -0.3822   0.03910   0.02992  -0.0538   0.9942   0.0747
  -4.750  -0.3496   0.03686   0.02721  -0.0561   0.9886   0.0784
  -4.500  -0.3156   0.03460   0.02439  -0.0581   0.9833   0.0804
  -4.250  -0.2818   0.03277   0.02204  -0.0597   0.9777   0.0825
  -4.000  -0.2491   0.03131   0.02030  -0.0612   0.9721   0.0865
  -3.750  -0.2159   0.03018   0.01901  -0.0627   0.9661   0.0911
  -3.500  -0.1834   0.02914   0.01773  -0.0637   0.9600   0.0944
  -3.250  -0.1499   0.02827   0.01660  -0.0647   0.9538   0.0983
  -3.000  -0.1177   0.02745   0.01579  -0.0659   0.9474   0.1053
  -2.750  -0.0850   0.02688   0.01503  -0.0670   0.9404   0.1145
  -2.500  -0.0514   0.02622   0.01434  -0.0683   0.9340   0.1248
  -2.250  -0.0189   0.02563   0.01372  -0.0696   0.9265   0.1443
  -2.000   0.0188   0.02461   0.01320  -0.0721   0.9212   0.2091
  -1.750   0.0446   0.02369   0.01330  -0.0722   0.9128   0.4334
  -1.500   0.0772   0.02324   0.01330  -0.0726   0.9068   0.5845
  -1.250   0.0946   0.02261   0.01343  -0.0693   0.8976   0.7538
  -1.000   0.1539   0.02227   0.01308  -0.0749   0.8927   1.0000
  -0.750   0.1833   0.02247   0.01298  -0.0756   0.8826   1.0000
  -0.500   0.2245   0.02258   0.01279  -0.0783   0.8762   1.0000
   0.000   0.2858   0.02295   0.01274  -0.0797   0.8573   1.0000
   0.250   0.3171   0.02313   0.01275  -0.0805   0.8481   1.0000
   0.500   0.3455   0.02336   0.01284  -0.0808   0.8383   1.0000
   0.750   0.3818   0.02347   0.01283  -0.0823   0.8310   1.0000
   1.000   0.4061   0.02376   0.01303  -0.0818   0.8200   1.0000
   1.250   0.4446   0.02379   0.01297  -0.0835   0.8139   1.0000
   1.750   0.4925   0.02440   0.01348  -0.0823   0.7921   1.0000
   2.000   0.5265   0.02447   0.01353  -0.0832   0.7845   1.0000
   2.250   0.5491   0.02481   0.01386  -0.0823   0.7731   1.0000
   2.500   0.5783   0.02499   0.01404  -0.0824   0.7640   1.0000
   2.750   0.6082   0.02512   0.01418  -0.0826   0.7547   1.0000
   3.000   0.6315   0.02544   0.01455  -0.0818   0.7433   1.0000
   3.250   0.6610   0.02556   0.01471  -0.0818   0.7337   1.0000
   3.500   0.6916   0.02560   0.01481  -0.0818   0.7239   1.0000
   3.750   0.7169   0.02573   0.01500  -0.0810   0.7108   1.0000
   4.000   0.7447   0.02568   0.01502  -0.0803   0.6971   1.0000
   4.250   0.7731   0.02559   0.01500  -0.0797   0.6830   1.0000
   4.500   0.8015   0.02555   0.01506  -0.0791   0.6694   1.0000
   4.750   0.8303   0.02557   0.01517  -0.0786   0.6564   1.0000
   5.000   0.8602   0.02557   0.01528  -0.0783   0.6437   1.0000
   5.250   0.8903   0.02561   0.01545  -0.0781   0.6308   1.0000
   5.500   0.9155   0.02583   0.01580  -0.0772   0.6159   1.0000
   5.750   0.9406   0.02608   0.01619  -0.0763   0.6005   1.0000
   6.000   0.9656   0.02633   0.01660  -0.0753   0.5845   1.0000
   6.250   0.9866   0.02662   0.01703  -0.0737   0.5650   1.0000
   6.500   1.0070   0.02653   0.01699  -0.0714   0.5373   1.0000
   6.750   1.0186   0.02665   0.01711  -0.0679   0.5018   1.0000
   7.000   1.0317   0.02672   0.01706  -0.0646   0.4607   1.0000
   7.250   1.0416   0.02718   0.01741  -0.0613   0.4188   1.0000
   7.500   1.0512   0.02785   0.01798  -0.0582   0.3780   1.0000
   7.750   1.0579   0.02872   0.01870  -0.0550   0.3346   1.0000
   8.000   1.0629   0.02979   0.01960  -0.0517   0.2917   1.0000
   8.250   1.0645   0.03124   0.02080  -0.0483   0.2477   1.0000
   8.500   1.0646   0.03300   0.02232  -0.0453   0.2044   1.0000
   8.750   1.0646   0.03499   0.02409  -0.0426   0.1622   1.0000
   9.000   1.0642   0.03717   0.02604  -0.0401   0.1354   1.0000
   9.250   1.0654   0.03937   0.02811  -0.0379   0.1206   1.0000
   9.500   1.0689   0.04151   0.03021  -0.0360   0.1104   1.0000
   9.750   1.0731   0.04367   0.03229  -0.0342   0.1036   1.0000
  10.000   1.0828   0.04551   0.03427  -0.0327   0.0969   1.0000
  10.250   1.0913   0.04748   0.03624  -0.0313   0.0915   1.0000
  10.500   1.1061   0.04914   0.03810  -0.0301   0.0860   1.0000
  10.750   1.1243   0.05074   0.03985  -0.0290   0.0817   1.0000
  11.000   1.1489   0.05230   0.04139  -0.0281   0.0779   1.0000
  11.250   1.1690   0.05422   0.04360  -0.0273   0.0743   1.0000
  11.500   1.1826   0.05639   0.04608  -0.0263   0.0706   1.0000
  11.750   1.1987   0.05863   0.04848  -0.0255   0.0679   1.0000
  12.000   1.2202   0.06107   0.05092  -0.0251   0.0651   1.0000
  12.250   1.2184   0.06419   0.05449  -0.0237   0.0634   1.0000
  12.500   1.2150   0.06757   0.05824  -0.0227   0.0617   1.0000
  12.750   1.2100   0.07120   0.06219  -0.0219   0.0603   1.0000
  13.000   1.2032   0.07517   0.06644  -0.0214   0.0593   1.0000
  13.250   1.1933   0.07947   0.07101  -0.0214   0.0585   1.0000
  13.500   1.1802   0.08419   0.07597  -0.0219   0.0578   1.0000
  13.750   1.1642   0.08946   0.08149  -0.0231   0.0573   1.0000
  14.000   1.1432   0.09569   0.08795  -0.0253   0.0571   1.0000
  14.250   1.1107   0.10427   0.09682  -0.0296   0.0577   1.0000
  14.500   1.0629   0.11709   0.10990  -0.0376   0.0595   1.0000
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