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GOE 570 AIRFOIL (goe570-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 570 AIRFOIL (goe570-il)
Reynolds number: 200,000
Max Cl/Cd: 10.35 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe570-il-200000-n5.txt
Download as CSV file: xf-goe570-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 570 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -17.000   0.2327   0.06397   0.05674  -0.2342   0.7266   0.0652
 -16.750   0.1999   0.05873   0.05126  -0.2363   0.7232   0.0652
 -16.500   0.1833   0.05511   0.04742  -0.2380   0.7204   0.0654
 -16.250   0.1699   0.05243   0.04463  -0.2381   0.7167   0.0656
 -16.000   0.1591   0.05026   0.04237  -0.2376   0.7126   0.0657
 -15.750   0.1530   0.04836   0.04037  -0.2372   0.7087   0.0658
 -15.500   0.1496   0.04662   0.03850  -0.2369   0.7049   0.0660
 -15.250   0.1494   0.04501   0.03675  -0.2367   0.7011   0.0662
 -15.000   0.1542   0.04359   0.03519  -0.2370   0.6978   0.0664
 -14.750   0.1471   0.04238   0.03394  -0.2347   0.6934   0.0666
 -14.500   0.1445   0.04129   0.03281  -0.2329   0.6891   0.0667
 -14.250   0.1439   0.04021   0.03163  -0.2314   0.6851   0.0669
 -14.000   0.1488   0.03928   0.03063  -0.2302   0.6814   0.0670
 -13.750   0.1542   0.03827   0.02948  -0.2295   0.6779   0.0673
 -13.500   0.1548   0.03749   0.02866  -0.2273   0.6741   0.0674
 -13.250   0.1528   0.03679   0.02798  -0.2244   0.6697   0.0677
 -13.000   0.1546   0.03614   0.02733  -0.2219   0.6653   0.0679
 -12.750   0.1575   0.03547   0.02662  -0.2197   0.6610   0.0681
 -12.500   0.1631   0.03478   0.02586  -0.2181   0.6573   0.0685
 -12.250   0.1609   0.03413   0.02522  -0.2151   0.6534   0.0689
 -12.000   0.1553   0.03357   0.02467  -0.2113   0.6490   0.0689
 -11.750   0.1499   0.03299   0.02407  -0.2076   0.6445   0.0693
 -11.500   0.1466   0.03238   0.02343  -0.2042   0.6401   0.0697
 -11.250   0.1478   0.03180   0.02276  -0.2015   0.6365   0.0700
 -11.000   0.1365   0.03135   0.02232  -0.1965   0.6320   0.0701
 -10.750   0.1224   0.03091   0.02188  -0.1909   0.6272   0.0704
 -10.500   0.1128   0.03048   0.02141  -0.1861   0.6228   0.0707
 -10.250   0.1074   0.03004   0.02090  -0.1818   0.6189   0.0710
 -10.000   0.1022   0.02962   0.02041  -0.1776   0.6152   0.0715
  -9.750   0.0840   0.02938   0.02019  -0.1709   0.6106   0.0716
  -9.500   0.0699   0.02912   0.01990  -0.1648   0.6059   0.0720
  -9.250   0.0598   0.02884   0.01957  -0.1593   0.6017   0.0721
  -9.000   0.0538   0.02853   0.01916  -0.1544   0.5978   0.0728
  -8.750   0.0384   0.02839   0.01901  -0.1479   0.5935   0.0730
  -8.500   0.0208   0.02831   0.01892  -0.1409   0.5887   0.0732
  -8.250   0.0086   0.02819   0.01875  -0.1347   0.5843   0.0737
  -8.000   0.0022   0.02804   0.01851  -0.1294   0.5805   0.0742
  -7.750  -0.0025   0.02787   0.01826  -0.1244   0.5771   0.0746
  -7.500  -0.0240   0.02792   0.01835  -0.1165   0.5728   0.0751
  -7.250  -0.0388   0.02796   0.01838  -0.1098   0.5684   0.0754
  -7.000  -0.0482   0.02791   0.01829  -0.1038   0.5643   0.0759
  -6.750  -0.0496   0.02779   0.01809  -0.0992   0.5608   0.0767
  -6.500  -0.0524   0.02775   0.01801  -0.0943   0.5574   0.0775
  -6.250  -0.0701   0.02803   0.01829  -0.0871   0.5527   0.0780
  -6.000  -0.0794   0.02815   0.01839  -0.0811   0.5487   0.0784
  -5.750  -0.0823   0.02819   0.01837  -0.0762   0.5451   0.0794
  -5.500  -0.0781   0.02811   0.01820  -0.0724   0.5421   0.0807
  -5.250  -0.0700   0.02797   0.01795  -0.0692   0.5393   0.0818
  -4.750  -0.0963   0.02868   0.01871  -0.0564   0.5311   0.0831
  -4.500  -0.0957   0.02879   0.01880  -0.0522   0.5275   0.0844
  -4.250  -0.0867   0.02873   0.01867  -0.0494   0.5242   0.0862
  -4.000  -0.0685   0.02852   0.01835  -0.0479   0.5216   0.0893
  -3.750  -0.0679   0.02881   0.01863  -0.0439   0.5183   0.0905
  -3.500  -0.0745   0.02929   0.01915  -0.0390   0.5145   0.0923
  -3.250  -0.0743   0.02964   0.01951  -0.0351   0.5109   0.0949
  -3.000  -0.0653   0.02981   0.01963  -0.0325   0.5077   0.0982
  -2.750  -0.0494   0.02966   0.01946  -0.0310   0.5050   0.1041
  -2.500  -0.0266   0.02936   0.01913  -0.0304   0.5028   0.1126
  -2.250  -0.0221   0.02967   0.01950  -0.0274   0.4994   0.1216
  -2.000  -0.0308   0.03047   0.02047  -0.0228   0.4949   0.1335
  -1.750  -0.0272   0.03096   0.02117  -0.0200   0.4915   0.1640
  -1.500  -0.0138   0.03131   0.02150  -0.0184   0.4886   0.1834
  -1.250   0.0074   0.03138   0.02152  -0.0179   0.4863   0.1964
  -1.000   0.0334   0.03125   0.02135  -0.0180   0.4843   0.2054
  -0.750   0.0563   0.03132   0.02135  -0.0178   0.4819   0.2138
  -0.500   0.0403   0.03296   0.02307  -0.0129   0.4771   0.2168
  -0.250   0.0441   0.03386   0.02403  -0.0106   0.4735   0.2215
   0.000   0.0570   0.03439   0.02457  -0.0095   0.4703   0.2282
   0.250   0.0795   0.03455   0.02468  -0.0094   0.4679   0.2357
   0.500   0.1086   0.03438   0.02451  -0.0103   0.4661   0.2451
   0.750   0.1416   0.03408   0.02419  -0.0116   0.4644   0.2584
   1.000   0.1312   0.03585   0.02610  -0.0081   0.4605   0.2654
   1.250   0.1226   0.03766   0.02804  -0.0050   0.4557   0.2750
   1.500   0.1350   0.03832   0.02895  -0.0044   0.4523   0.3149
   1.750   0.1542   0.03855   0.02943  -0.0042   0.4500   0.3806
   2.000   0.1809   0.03837   0.02936  -0.0047   0.4482   0.4272
   2.250   0.2102   0.03809   0.02916  -0.0053   0.4467   0.4620
   2.500   0.2142   0.03931   0.03049  -0.0036   0.4438   0.4858
   2.750   0.1718   0.04349   0.03487   0.0025   0.4369   0.4888
   3.000   0.1796   0.04463   0.03609   0.0038   0.4338   0.5118
   3.250   0.2023   0.04471   0.03628   0.0037   0.4317   0.5449
   3.500   0.2308   0.04451   0.03612   0.0030   0.4302   0.5705
   3.750   0.2622   0.04420   0.03590   0.0019   0.4291   0.6045
   4.000   0.2992   0.04359   0.03537   0.0001   0.4279   0.6401
   4.500   0.2209   0.05314   0.04551   0.0096   0.4140   0.6865
   5.000   0.5212   0.05633   0.04927  -0.0391   0.4133   0.9491
   5.250   0.5485   0.05672   0.04956  -0.0398   0.4123   0.9631
   5.500   0.5869   0.05669   0.04938  -0.0419   0.4111   0.9728
   6.500   0.6001   0.07040   0.06326  -0.0443   0.3950   0.9904
   6.750   0.6526   0.07061   0.06336  -0.0498   0.3944   0.9960
   7.000   0.7114   0.07037   0.06300  -0.0562   0.3938   1.0000
   8.000   0.6470   0.08505   0.07786  -0.0463   0.3759   1.0000
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