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GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 584 AIRFOIL (goe584-il)
Reynolds number: 500,000
Max Cl/Cd: 112.34 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe584-il-500000.txt
Download as CSV file: xf-goe584-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 584 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.3013   0.10239   0.10004  -0.0461   1.0000   0.0393
 -10.500  -0.2917   0.10103   0.09871  -0.0453   1.0000   0.0401
 -10.250  -0.5346   0.03224   0.02880  -0.1061   0.9501   0.0388
 -10.000  -0.4926   0.03321   0.02993  -0.1080   0.9418   0.0394
  -9.750  -0.4445   0.03577   0.03272  -0.1089   0.9334   0.0398
  -9.250  -0.2647   0.06828   0.06594  -0.0805   0.9508   0.0438
  -9.000  -0.4172   0.02757   0.02332  -0.1078   0.8782   0.0438
  -8.750  -0.4062   0.02538   0.02080  -0.1065   0.8659   0.0450
  -8.500  -0.3814   0.02533   0.02076  -0.1060   0.8559   0.0457
  -8.250  -0.3560   0.02542   0.02089  -0.1056   0.8461   0.0465
  -8.000  -0.3343   0.02481   0.02014  -0.1048   0.8373   0.0476
  -7.750  -0.3166   0.02340   0.01846  -0.1036   0.8279   0.0490
  -7.500  -0.2968   0.02244   0.01712  -0.1024   0.8198   0.0504
  -7.250  -0.2796   0.02055   0.01492  -0.1012   0.8112   0.0516
  -7.000  -0.2562   0.01977   0.01406  -0.1007   0.8039   0.0526
  -6.750  -0.2311   0.01944   0.01374  -0.1003   0.7961   0.0536
  -6.500  -0.2065   0.01896   0.01317  -0.0997   0.7887   0.0548
  -6.250  -0.1826   0.01821   0.01226  -0.0990   0.7814   0.0559
  -6.000  -0.1582   0.01759   0.01145  -0.0983   0.7739   0.0570
  -5.750  -0.1328   0.01719   0.01087  -0.0977   0.7674   0.0580
  -5.500  -0.1071   0.01695   0.01048  -0.0971   0.7599   0.0586
  -5.250  -0.0838   0.01530   0.00865  -0.0965   0.7534   0.0597
  -5.000  -0.0582   0.01466   0.00800  -0.0961   0.7463   0.0609
  -4.750  -0.0322   0.01425   0.00753  -0.0957   0.7393   0.0619
  -4.500  -0.0058   0.01384   0.00704  -0.0953   0.7331   0.0628
  -4.250   0.0205   0.01342   0.00657  -0.0949   0.7260   0.0638
  -4.000   0.0469   0.01306   0.00612  -0.0944   0.7195   0.0647
  -3.750   0.0736   0.01275   0.00577  -0.0940   0.7128   0.0658
  -3.500   0.1003   0.01248   0.00543  -0.0936   0.7062   0.0668
  -3.250   0.1271   0.01225   0.00512  -0.0932   0.7002   0.0674
  -3.000   0.1532   0.01183   0.00468  -0.0928   0.6934   0.0682
  -2.750   0.1787   0.01134   0.00415  -0.0922   0.6873   0.0697
  -2.500   0.2049   0.01107   0.00387  -0.0918   0.6813   0.0711
  -2.250   0.2313   0.01087   0.00367  -0.0914   0.6747   0.0728
  -2.000   0.2579   0.01074   0.00348  -0.0910   0.6689   0.0745
  -1.750   0.2845   0.01057   0.00331  -0.0906   0.6627   0.0760
  -1.500   0.3112   0.01044   0.00315  -0.0902   0.6563   0.0775
  -1.250   0.3376   0.01030   0.00295  -0.0897   0.6504   0.0794
  -1.000   0.3638   0.01010   0.00279  -0.0893   0.6436   0.0828
  -0.750   0.3904   0.01001   0.00267  -0.0889   0.6373   0.0868
  -0.500   0.4171   0.00993   0.00258  -0.0885   0.6313   0.0923
  -0.250   0.4435   0.00978   0.00250  -0.0881   0.6251   0.1061
   0.000   0.4684   0.00948   0.00248  -0.0875   0.6195   0.1948
   0.250   0.4936   0.00923   0.00250  -0.0870   0.6138   0.2756
   0.500   0.5177   0.00889   0.00252  -0.0864   0.6077   0.3987
   0.750   0.5345   0.00816   0.00258  -0.0842   0.6025   0.6742
   1.000   0.6032   0.00762   0.00277  -0.0923   0.5958   0.9665
   1.250   0.6615   0.00773   0.00280  -0.0987   0.5890   0.9946
   1.500   0.7022   0.00781   0.00280  -0.1015   0.5828   1.0000
   1.750   0.7261   0.00787   0.00284  -0.1006   0.5765   1.0000
   2.000   0.7498   0.00796   0.00286  -0.0996   0.5706   1.0000
   2.250   0.7738   0.00805   0.00292  -0.0988   0.5646   1.0000
   2.500   0.7978   0.00812   0.00298  -0.0979   0.5581   1.0000
   3.000   0.8457   0.00832   0.00311  -0.0962   0.5454   1.0000
   3.250   0.8695   0.00843   0.00318  -0.0953   0.5388   1.0000
   3.500   0.8934   0.00854   0.00327  -0.0944   0.5322   1.0000
   3.750   0.9173   0.00864   0.00335  -0.0935   0.5248   1.0000
   4.000   0.9408   0.00878   0.00345  -0.0926   0.5176   1.0000
   4.250   0.9642   0.00887   0.00354  -0.0916   0.5080   1.0000
   4.500   0.9871   0.00900   0.00364  -0.0906   0.4978   1.0000
   5.000   1.0324   0.00929   0.00386  -0.0884   0.4758   1.0000
   5.250   1.0551   0.00945   0.00400  -0.0874   0.4661   1.0000
   5.500   1.0772   0.00963   0.00415  -0.0863   0.4559   1.0000
   5.750   1.0998   0.00979   0.00432  -0.0852   0.4446   1.0000
   6.000   1.1214   0.01000   0.00449  -0.0840   0.4327   1.0000
   6.250   1.1424   0.01023   0.00468  -0.0827   0.4200   1.0000
   6.750   1.1836   0.01074   0.00512  -0.0800   0.3936   1.0000
   7.000   1.2037   0.01102   0.00537  -0.0786   0.3803   1.0000
   7.250   1.2229   0.01133   0.00564  -0.0771   0.3668   1.0000
   7.500   1.2411   0.01167   0.00594  -0.0754   0.3522   1.0000
   7.750   1.2580   0.01206   0.00626  -0.0735   0.3364   1.0000
   8.000   1.2743   0.01245   0.00660  -0.0715   0.3215   1.0000
   8.250   1.2898   0.01286   0.00697  -0.0694   0.3075   1.0000
   8.500   1.3026   0.01328   0.00734  -0.0668   0.2951   1.0000
   8.750   1.3149   0.01372   0.00774  -0.0641   0.2819   1.0000
   9.000   1.3276   0.01416   0.00816  -0.0616   0.2683   1.0000
   9.250   1.3398   0.01467   0.00863  -0.0591   0.2547   1.0000
   9.500   1.3515   0.01522   0.00914  -0.0567   0.2414   1.0000
   9.750   1.3622   0.01585   0.00973  -0.0542   0.2276   1.0000
  10.000   1.3721   0.01656   0.01039  -0.0518   0.2135   1.0000
  10.250   1.3810   0.01736   0.01115  -0.0493   0.1990   1.0000
  10.500   1.3894   0.01825   0.01199  -0.0470   0.1853   1.0000
  10.750   1.3971   0.01922   0.01292  -0.0448   0.1725   1.0000
  11.000   1.4043   0.02031   0.01396  -0.0427   0.1610   1.0000
  11.250   1.4133   0.02134   0.01499  -0.0409   0.1509   1.0000
  11.500   1.4219   0.02246   0.01611  -0.0392   0.1427   1.0000
  12.000   1.4374   0.02495   0.01859  -0.0361   0.1270   1.0000
  12.250   1.4434   0.02640   0.02003  -0.0346   0.1199   1.0000
  12.500   1.4518   0.02772   0.02138  -0.0333   0.1130   1.0000
  12.750   1.4574   0.02929   0.02295  -0.0320   0.1057   1.0000
  13.000   1.4629   0.03092   0.02458  -0.0308   0.0982   1.0000
  13.250   1.4678   0.03264   0.02631  -0.0297   0.0889   1.0000
  13.500   1.4667   0.03492   0.02852  -0.0284   0.0751   1.0000
  13.750   1.4590   0.03787   0.03135  -0.0270   0.0550   1.0000
  14.000   1.4482   0.04125   0.03463  -0.0258   0.0417   1.0000
  14.250   1.4426   0.04427   0.03766  -0.0250   0.0367   1.0000
  14.500   1.4412   0.04699   0.04044  -0.0243   0.0343   1.0000
  14.750   1.4373   0.05005   0.04355  -0.0239   0.0323   1.0000
  15.000   1.4336   0.05320   0.04676  -0.0235   0.0309   1.0000
  15.250   1.4330   0.05605   0.04972  -0.0233   0.0298   1.0000
  15.500   1.4304   0.05921   0.05296  -0.0232   0.0288   1.0000
  15.750   1.4239   0.06291   0.05673  -0.0233   0.0277   1.0000
  16.000   1.4167   0.06679   0.06069  -0.0236   0.0271   1.0000
  16.250   1.4076   0.07101   0.06500  -0.0240   0.0265   1.0000
  16.500   1.4055   0.07441   0.06851  -0.0244   0.0260   1.0000
  16.750   1.4015   0.07812   0.07232  -0.0249   0.0253   1.0000
  17.000   1.3969   0.08195   0.07624  -0.0256   0.0247   1.0000
  17.250   1.3914   0.08598   0.08036  -0.0264   0.0243   1.0000
  17.500   1.3844   0.09030   0.08477  -0.0273   0.0239   1.0000
  17.750   1.3760   0.09489   0.08943  -0.0285   0.0234   1.0000
  18.000   1.3663   0.09970   0.09431  -0.0298   0.0230   1.0000
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