Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

GOE 584 AIRFOIL (goe584-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 584 AIRFOIL (goe584-il)
Reynolds number: 1,000,000
Max Cl/Cd: 126.11 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe584-il-1000000-n5.txt
Download as CSV file: xf-goe584-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -1.0074   0.03641   0.03360  -0.1038   1.0000   0.0117
 -15.000  -1.0435   0.03231   0.02928  -0.1006   1.0000   0.0116
 -14.750  -1.0366   0.02888   0.02563  -0.1025   0.9910   0.0119
 -14.500  -1.0194   0.02656   0.02314  -0.1040   0.9825   0.0123
 -14.250  -0.9948   0.02473   0.02115  -0.1060   0.9746   0.0126
 -14.000  -0.9647   0.02322   0.01949  -0.1084   0.9663   0.0130
 -13.750  -0.9326   0.02160   0.01772  -0.1113   0.9549   0.0136
 -13.500  -0.9008   0.02023   0.01619  -0.1137   0.9375   0.0142
 -13.250  -0.8763   0.01928   0.01507  -0.1140   0.9124   0.0149
 -13.000  -0.8565   0.01858   0.01419  -0.1131   0.8890   0.0156
 -12.750  -0.8374   0.01789   0.01335  -0.1120   0.8704   0.0162
 -12.500  -0.8186   0.01716   0.01248  -0.1108   0.8551   0.0171
 -12.250  -0.7980   0.01654   0.01175  -0.1098   0.8427   0.0180
 -12.000  -0.7763   0.01601   0.01110  -0.1089   0.8320   0.0189
 -11.750  -0.7547   0.01544   0.01042  -0.1080   0.8224   0.0200
 -11.500  -0.7320   0.01490   0.00981  -0.1073   0.8139   0.0214
 -11.000  -0.6850   0.01402   0.00880  -0.1059   0.7986   0.0247
 -10.750  -0.6606   0.01367   0.00838  -0.1053   0.7913   0.0266
 -10.500  -0.6353   0.01340   0.00808  -0.1049   0.7848   0.0287
 -10.250  -0.6097   0.01315   0.00778  -0.1044   0.7776   0.0304
 -10.000  -0.5843   0.01290   0.00745  -0.1039   0.7711   0.0317
  -9.750  -0.5578   0.01272   0.00726  -0.1036   0.7650   0.0330
  -9.500  -0.5311   0.01261   0.00712  -0.1032   0.7579   0.0344
  -9.250  -0.5046   0.01247   0.00693  -0.1029   0.7517   0.0356
  -9.000  -0.4779   0.01231   0.00671  -0.1026   0.7451   0.0366
  -8.750  -0.4516   0.01214   0.00646  -0.1021   0.7385   0.0373
  -8.500  -0.4251   0.01194   0.00621  -0.1018   0.7321   0.0380
  -8.250  -0.3985   0.01178   0.00602  -0.1015   0.7249   0.0390
  -8.000  -0.3715   0.01169   0.00590  -0.1012   0.7187   0.0398
  -7.750  -0.3443   0.01158   0.00577  -0.1009   0.7122   0.0406
  -7.500  -0.3172   0.01152   0.00565  -0.1006   0.7053   0.0414
  -7.250  -0.2901   0.01139   0.00548  -0.1003   0.6987   0.0422
  -7.000  -0.2632   0.01127   0.00530  -0.1000   0.6916   0.0429
  -6.750  -0.2362   0.01115   0.00513  -0.0997   0.6853   0.0436
  -6.500  -0.2087   0.01106   0.00499  -0.0995   0.6790   0.0441
  -6.250  -0.1818   0.01095   0.00482  -0.0992   0.6722   0.0444
  -6.000  -0.1549   0.01077   0.00458  -0.0989   0.6661   0.0448
  -5.750  -0.1293   0.01040   0.00416  -0.0984   0.6593   0.0456
  -5.500  -0.1030   0.01018   0.00389  -0.0980   0.6535   0.0462
  -5.250  -0.0759   0.01000   0.00368  -0.0977   0.6481   0.0468
  -5.000  -0.0490   0.00985   0.00350  -0.0974   0.6418   0.0473
  -4.750  -0.0220   0.00974   0.00335  -0.0971   0.6360   0.0479
  -4.500   0.0053   0.00960   0.00319  -0.0969   0.6303   0.0485
  -4.250   0.0324   0.00948   0.00302  -0.0966   0.6247   0.0490
  -4.000   0.0594   0.00937   0.00287  -0.0963   0.6194   0.0495
  -3.750   0.0868   0.00924   0.00272  -0.0961   0.6141   0.0501
  -3.500   0.1140   0.00915   0.00259  -0.0958   0.6083   0.0507
  -3.250   0.1411   0.00906   0.00246  -0.0955   0.6032   0.0512
  -3.000   0.1687   0.00897   0.00235  -0.0953   0.5981   0.0517
  -2.750   0.1960   0.00889   0.00224  -0.0951   0.5926   0.0521
  -2.250   0.2508   0.00878   0.00208  -0.0947   0.5820   0.0529
  -2.000   0.2781   0.00873   0.00200  -0.0944   0.5756   0.0533
  -1.750   0.3049   0.00864   0.00187  -0.0941   0.5692   0.0542
  -1.500   0.3322   0.00856   0.00178  -0.0939   0.5626   0.0553
  -1.250   0.3592   0.00852   0.00171  -0.0936   0.5563   0.0565
  -1.000   0.3865   0.00847   0.00166  -0.0934   0.5513   0.0577
  -0.750   0.4140   0.00843   0.00162  -0.0932   0.5457   0.0589
  -0.500   0.4411   0.00842   0.00159  -0.0929   0.5400   0.0601
  -0.250   0.4684   0.00840   0.00156  -0.0927   0.5348   0.0616
   0.000   0.4959   0.00839   0.00155  -0.0925   0.5294   0.0629
   0.250   0.5229   0.00840   0.00154  -0.0923   0.5232   0.0647
   0.500   0.5500   0.00838   0.00153  -0.0920   0.5181   0.0704
   0.750   0.5772   0.00836   0.00154  -0.0918   0.5122   0.0782
   1.000   0.6033   0.00831   0.00156  -0.0915   0.5058   0.1079
   1.250   0.6298   0.00822   0.00159  -0.0912   0.5006   0.1533
   1.500   0.6564   0.00819   0.00163  -0.0909   0.4939   0.1852
   1.750   0.6824   0.00818   0.00168  -0.0905   0.4875   0.2183
   2.000   0.7087   0.00810   0.00174  -0.0902   0.4812   0.2692
   2.250   0.7336   0.00796   0.00182  -0.0897   0.4744   0.3645
   2.500   0.7574   0.00773   0.00190  -0.0890   0.4675   0.4923
   2.750   0.7760   0.00725   0.00202  -0.0872   0.4601   0.7277
   3.000   0.8405   0.00691   0.00224  -0.0952   0.4508   0.9770
   3.250   0.8806   0.00709   0.00235  -0.0979   0.4389   0.9946
   3.500   0.9168   0.00727   0.00246  -0.0999   0.4247   1.0000
   3.750   0.9388   0.00748   0.00258  -0.0987   0.4080   1.0000
   4.000   0.9606   0.00771   0.00272  -0.0975   0.3900   1.0000
   4.250   0.9822   0.00794   0.00287  -0.0963   0.3730   1.0000
   4.500   1.0035   0.00820   0.00304  -0.0950   0.3555   1.0000
   4.750   1.0252   0.00844   0.00320  -0.0939   0.3419   1.0000
   5.000   1.0475   0.00865   0.00337  -0.0928   0.3303   1.0000
   5.250   1.0694   0.00887   0.00354  -0.0917   0.3188   1.0000
   5.500   1.0909   0.00912   0.00373  -0.0905   0.3076   1.0000
   5.750   1.1125   0.00935   0.00392  -0.0893   0.2972   1.0000
   6.000   1.1345   0.00956   0.00410  -0.0882   0.2885   1.0000
   6.500   1.1771   0.01004   0.00451  -0.0859   0.2696   1.0000
   6.750   1.1975   0.01031   0.00474  -0.0846   0.2597   1.0000
   7.000   1.2170   0.01062   0.00500  -0.0831   0.2482   1.0000
   7.250   1.2370   0.01089   0.00524  -0.0817   0.2381   1.0000
   7.500   1.2545   0.01126   0.00554  -0.0800   0.2237   1.0000
   7.750   1.2682   0.01177   0.00593  -0.0775   0.2035   1.0000
   8.000   1.2798   0.01222   0.00630  -0.0747   0.1859   1.0000
   8.250   1.2915   0.01267   0.00668  -0.0719   0.1717   1.0000
   8.500   1.3034   0.01315   0.00710  -0.0692   0.1581   1.0000
   8.750   1.3152   0.01368   0.00756  -0.0666   0.1441   1.0000
   9.000   1.3283   0.01418   0.00802  -0.0644   0.1338   1.0000
   9.250   1.3402   0.01477   0.00857  -0.0620   0.1237   1.0000
   9.500   1.3538   0.01531   0.00909  -0.0601   0.1161   1.0000
   9.750   1.3655   0.01599   0.00973  -0.0579   0.1075   1.0000
  10.000   1.3794   0.01658   0.01032  -0.0562   0.1019   1.0000
  10.250   1.3910   0.01734   0.01105  -0.0543   0.0953   1.0000
  10.500   1.4055   0.01798   0.01171  -0.0529   0.0910   1.0000
  10.750   1.4163   0.01887   0.01257  -0.0512   0.0845   1.0000
  11.000   1.4260   0.01988   0.01355  -0.0494   0.0756   1.0000
  11.250   1.4360   0.02093   0.01457  -0.0479   0.0676   1.0000
  11.500   1.4307   0.02308   0.01657  -0.0451   0.0424   1.0000
  11.750   1.4290   0.02513   0.01856  -0.0430   0.0288   1.0000
  12.000   1.4370   0.02652   0.01997  -0.0417   0.0252   1.0000
  12.250   1.4450   0.02794   0.02142  -0.0406   0.0226   1.0000
  12.500   1.4548   0.02927   0.02278  -0.0396   0.0212   1.0000
  12.750   1.4618   0.03082   0.02436  -0.0385   0.0195   1.0000
  13.000   1.4699   0.03233   0.02592  -0.0376   0.0182   1.0000
  13.250   1.4775   0.03392   0.02755  -0.0367   0.0171   1.0000
  13.500   1.4837   0.03564   0.02931  -0.0359   0.0161   1.0000
  13.750   1.4900   0.03740   0.03111  -0.0351   0.0153   1.0000
  14.000   1.4969   0.03916   0.03292  -0.0344   0.0146   1.0000
  14.250   1.5024   0.04108   0.03489  -0.0338   0.0139   1.0000
  14.500   1.5066   0.04316   0.03702  -0.0332   0.0132   1.0000
  14.750   1.5102   0.04534   0.03926  -0.0326   0.0127   1.0000
  15.000   1.5155   0.04740   0.04137  -0.0322   0.0123   1.0000
  15.250   1.5193   0.04964   0.04368  -0.0318   0.0119   1.0000
  15.500   1.5223   0.05201   0.04610  -0.0315   0.0114   1.0000
  15.750   1.5247   0.05445   0.04861  -0.0312   0.0111   1.0000
  16.000   1.5251   0.05718   0.05138  -0.0310   0.0105   1.0000
  16.500   1.5260   0.06273   0.05707  -0.0308   0.0101   1.0000
  16.750   1.5269   0.06548   0.05990  -0.0308   0.0097   1.0000
  17.000   1.5258   0.06854   0.06304  -0.0309   0.0096   1.0000
  17.250   1.5248   0.07161   0.06618  -0.0310   0.0093   1.0000
  17.500   1.5229   0.07485   0.06948  -0.0313   0.0090   1.0000
  17.750   1.5196   0.07826   0.07296  -0.0316   0.0088   1.0000
  18.000   1.5155   0.08185   0.07662  -0.0320   0.0087   1.0000
  18.250   1.5094   0.08577   0.08062  -0.0326   0.0085   1.0000
  18.500   1.5034   0.08971   0.08465  -0.0333   0.0082   1.0000
  18.750   1.4982   0.09359   0.08861  -0.0340   0.0082   1.0000
  19.000   1.4930   0.09752   0.09262  -0.0348   0.0080   1.0000
  19.250   1.4863   0.10174   0.09694  -0.0359   0.0079   1.0000
<< Back to GOE 584 AIRFOIL (goe584-il)

Polar data table (+)

Polar graphs


<< Back to GOE 584 AIRFOIL (goe584-il)