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GOE 595 AIRFOIL (goe595-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 595 AIRFOIL (goe595-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.06 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe595-il-1000000-n5.txt
Download as CSV file: xf-goe595-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 595 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4248   0.10775   0.10608  -0.0318   1.0000   0.0035
 -10.750  -0.4282   0.10323   0.10157  -0.0328   1.0000   0.0035
 -10.250  -0.6828   0.02607   0.02330  -0.0838   0.9781   0.0035
 -10.000  -0.6690   0.02271   0.01954  -0.0840   0.9724   0.0036
  -9.750  -0.6458   0.02084   0.01744  -0.0847   0.9690   0.0037
  -9.500  -0.6180   0.01950   0.01592  -0.0859   0.9669   0.0038
  -9.250  -0.5939   0.01822   0.01444  -0.0861   0.9627   0.0039
  -9.000  -0.5677   0.01723   0.01328  -0.0865   0.9586   0.0041
  -8.750  -0.5395   0.01624   0.01213  -0.0873   0.9554   0.0043
  -8.500  -0.5122   0.01528   0.01101  -0.0878   0.9516   0.0044
  -8.250  -0.4868   0.01446   0.01003  -0.0877   0.9463   0.0046
  -8.000  -0.4589   0.01378   0.00923  -0.0881   0.9420   0.0048
  -7.750  -0.4318   0.01309   0.00840  -0.0883   0.9377   0.0050
  -7.500  -0.4059   0.01259   0.00779  -0.0881   0.9318   0.0052
  -7.250  -0.3801   0.01180   0.00685  -0.0880   0.9260   0.0056
  -7.000  -0.3550   0.01129   0.00624  -0.0876   0.9193   0.0059
  -6.750  -0.3288   0.01090   0.00575  -0.0874   0.9129   0.0062
  -6.500  -0.3029   0.01055   0.00534  -0.0871   0.9073   0.0066
  -6.250  -0.2775   0.01019   0.00490  -0.0866   0.9011   0.0069
  -6.000  -0.2514   0.00986   0.00447  -0.0863   0.8957   0.0073
  -5.750  -0.2259   0.00960   0.00415  -0.0859   0.8895   0.0077
  -5.500  -0.2006   0.00922   0.00369  -0.0854   0.8834   0.0086
  -5.250  -0.1746   0.00901   0.00347  -0.0850   0.8776   0.0097
  -5.000  -0.1486   0.00881   0.00322  -0.0847   0.8711   0.0107
  -4.750  -0.1224   0.00861   0.00296  -0.0843   0.8646   0.0113
  -4.500  -0.0969   0.00836   0.00267  -0.0838   0.8563   0.0133
  -4.250  -0.0708   0.00822   0.00253  -0.0834   0.8475   0.0152
  -4.000  -0.0445   0.00814   0.00239  -0.0831   0.8382   0.0168
  -3.750  -0.0187   0.00794   0.00217  -0.0826   0.8288   0.0193
  -3.500   0.0076   0.00782   0.00201  -0.0823   0.8206   0.0216
  -3.250   0.0338   0.00774   0.00187  -0.0819   0.8108   0.0239
  -3.000   0.0601   0.00767   0.00176  -0.0815   0.7995   0.0250
  -2.750   0.0857   0.00760   0.00162  -0.0810   0.7850   0.0260
  -2.500   0.1107   0.00751   0.00143  -0.0804   0.7685   0.0284
  -2.250   0.1359   0.00746   0.00130  -0.0798   0.7519   0.0302
  -2.000   0.1614   0.00742   0.00119  -0.0792   0.7364   0.0317
  -1.750   0.1869   0.00740   0.00110  -0.0787   0.7215   0.0328
  -1.500   0.2123   0.00740   0.00103  -0.0781   0.7044   0.0342
  -1.250   0.2377   0.00739   0.00097  -0.0776   0.6878   0.0419
  -1.000   0.2622   0.00732   0.00093  -0.0769   0.6687   0.0739
  -0.750   0.2868   0.00735   0.00090  -0.0763   0.6454   0.0865
  -0.500   0.3103   0.00732   0.00088  -0.0754   0.6172   0.1257
  -0.250   0.3341   0.00731   0.00088  -0.0746   0.5903   0.1632
   0.000   0.3574   0.00731   0.00090  -0.0738   0.5607   0.2121
   0.250   0.3800   0.00735   0.00095  -0.0728   0.5257   0.2672
   0.500   0.4035   0.00737   0.00099  -0.0720   0.4980   0.3149
   0.750   0.4251   0.00714   0.00104  -0.0710   0.4770   0.4503
   1.000   0.4484   0.00708   0.00111  -0.0702   0.4581   0.5229
   1.250   0.4711   0.00697   0.00117  -0.0693   0.4424   0.6061
   1.500   0.4897   0.00663   0.00126  -0.0673   0.4313   0.7582
   1.750   0.5299   0.00633   0.00147  -0.0699   0.4201   0.9556
   2.000   0.5773   0.00653   0.00159  -0.0745   0.4019   0.9766
   2.250   0.6111   0.00669   0.00167  -0.0760   0.3865   0.9832
   2.500   0.6448   0.00684   0.00177  -0.0774   0.3732   0.9897
   2.750   0.6816   0.00700   0.00187  -0.0796   0.3585   0.9962
   3.000   0.7194   0.00719   0.00197  -0.0820   0.3363   0.9998
   3.250   0.7404   0.00749   0.00211  -0.0807   0.3000   1.0000
   3.500   0.7594   0.00783   0.00228  -0.0791   0.2633   1.0000
   3.750   0.7801   0.00809   0.00245  -0.0777   0.2431   1.0000
   4.000   0.8014   0.00832   0.00262  -0.0764   0.2273   1.0000
   4.500   0.8445   0.00879   0.00296  -0.0740   0.1993   1.0000
   4.750   0.8666   0.00900   0.00313  -0.0729   0.1864   1.0000
   5.000   0.8884   0.00924   0.00332  -0.0718   0.1716   1.0000
   5.250   0.9075   0.00966   0.00357  -0.0702   0.1360   1.0000
   5.500   0.9175   0.01074   0.00422  -0.0671   0.0511   1.0000
   5.750   0.9384   0.01106   0.00451  -0.0658   0.0411   1.0000
   6.000   0.9604   0.01131   0.00476  -0.0647   0.0375   1.0000
   6.250   0.9820   0.01159   0.00504  -0.0636   0.0340   1.0000
   6.500   1.0036   0.01187   0.00532  -0.0625   0.0304   1.0000
   6.750   1.0260   0.01209   0.00557  -0.0616   0.0289   1.0000
   7.000   1.0475   0.01238   0.00586  -0.0605   0.0247   1.0000
   7.250   1.0681   0.01273   0.00619  -0.0593   0.0186   1.0000
   7.500   1.0882   0.01311   0.00654  -0.0580   0.0131   1.0000
   7.750   1.1081   0.01350   0.00692  -0.0566   0.0106   1.0000
   8.000   1.1280   0.01389   0.00733  -0.0553   0.0089   1.0000
   8.250   1.1478   0.01426   0.00774  -0.0540   0.0079   1.0000
   8.500   1.1666   0.01469   0.00818  -0.0525   0.0069   1.0000
   8.750   1.1846   0.01517   0.00870  -0.0509   0.0061   1.0000
   9.000   1.2029   0.01557   0.00916  -0.0493   0.0057   1.0000
   9.250   1.2192   0.01600   0.00964  -0.0474   0.0054   1.0000
   9.500   1.2346   0.01646   0.01014  -0.0453   0.0050   1.0000
   9.750   1.2489   0.01698   0.01070  -0.0431   0.0046   1.0000
  10.000   1.2616   0.01762   0.01139  -0.0407   0.0043   1.0000
  10.250   1.2755   0.01819   0.01203  -0.0385   0.0041   1.0000
  10.500   1.2891   0.01879   0.01269  -0.0364   0.0039   1.0000
  10.750   1.3028   0.01939   0.01335  -0.0344   0.0037   1.0000
  11.000   1.3145   0.02011   0.01415  -0.0321   0.0036   1.0000
  11.250   1.3287   0.02070   0.01480  -0.0303   0.0033   1.0000
  11.500   1.3399   0.02147   0.01564  -0.0282   0.0032   1.0000
  11.750   1.3500   0.02234   0.01658  -0.0261   0.0031   1.0000
  12.000   1.3589   0.02330   0.01761  -0.0239   0.0029   1.0000
  12.250   1.3659   0.02443   0.01883  -0.0216   0.0028   1.0000
  12.500   1.3693   0.02584   0.02034  -0.0191   0.0027   1.0000
  12.750   1.3757   0.02710   0.02169  -0.0171   0.0027   1.0000
  13.000   1.3823   0.02839   0.02308  -0.0152   0.0026   1.0000
  13.250   1.3880   0.02980   0.02459  -0.0135   0.0025   1.0000
  13.500   1.3921   0.03141   0.02630  -0.0119   0.0025   1.0000
  13.750   1.3939   0.03329   0.02831  -0.0103   0.0024   1.0000
  14.000   1.3969   0.03516   0.03028  -0.0090   0.0023   1.0000
  14.250   1.4000   0.03711   0.03233  -0.0080   0.0022   1.0000
  14.500   1.3977   0.03969   0.03503  -0.0070   0.0022   1.0000
  14.750   1.3982   0.04212   0.03758  -0.0064   0.0022   1.0000
  15.000   1.3956   0.04502   0.04059  -0.0061   0.0021   1.0000
  15.250   1.3949   0.04783   0.04350  -0.0060   0.0021   1.0000
  15.500   1.3839   0.05210   0.04793  -0.0063   0.0021   1.0000
  15.750   1.3798   0.05570   0.05165  -0.0070   0.0021   1.0000
  16.000   1.3735   0.05978   0.05584  -0.0079   0.0020   1.0000
  16.250   1.3757   0.06278   0.05892  -0.0088   0.0019   1.0000
  16.500   1.3560   0.06919   0.06551  -0.0109   0.0020   1.0000
  16.750   1.3554   0.07281   0.06920  -0.0122   0.0019   1.0000
  17.000   1.3263   0.08106   0.07766  -0.0153   0.0020   1.0000
  17.250   1.3247   0.08506   0.08173  -0.0170   0.0019   1.0000
  17.500   1.3116   0.09099   0.08779  -0.0195   0.0019   1.0000
  17.750   1.2969   0.09733   0.09424  -0.0222   0.0019   1.0000
  18.000   1.2763   0.10496   0.10201  -0.0257   0.0019   1.0000
  18.250   1.2631   0.11142   0.10858  -0.0287   0.0019   1.0000
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