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GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 532 AIRFOIL (goe532-il)
Reynolds number: 50,000
Max Cl/Cd: 17.65 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe532-il-50000.txt
Download as CSV file: xf-goe532-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 532 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2665   0.11160   0.10472  -0.0263   1.0000   0.2388
  -8.750  -0.2452   0.10723   0.10035  -0.0249   1.0000   0.2475
  -8.500  -0.2746   0.10892   0.10226  -0.0250   1.0000   0.2545
  -8.250  -0.2430   0.10266   0.09600  -0.0235   1.0000   0.2617
  -8.000  -0.2567   0.10242   0.09592  -0.0226   1.0000   0.2711
  -7.750  -0.2482   0.09890   0.09248  -0.0214   1.0000   0.2772
  -7.500  -0.2526   0.09764   0.09136  -0.0195   1.0000   0.2877
  -7.250  -0.2660   0.09638   0.09028  -0.0173   1.0000   0.2932
  -7.000  -0.2610   0.09422   0.08821  -0.0147   1.0000   0.3047
  -6.750  -0.3079   0.09644   0.09070  -0.0096   1.0000   0.3081
  -6.500  -0.2803   0.09174   0.08601  -0.0081   1.0000   0.3202
  -6.250  -0.3201   0.09317   0.08768  -0.0027   1.0000   0.3248
  -6.000  -0.3706   0.09540   0.09014   0.0008   1.0000   0.3268
  -5.750  -0.3441   0.09099   0.08577   0.0047   1.0000   0.3386
  -5.500  -0.3900   0.09287   0.08785   0.0072   1.0000   0.3444
  -5.250  -0.3836   0.09007   0.08513   0.0109   1.0000   0.3518
  -5.000  -0.3555   0.08688   0.08195   0.0066   0.9895   0.3731
  -4.750  -0.3301   0.08408   0.07915  -0.0014   0.9728   0.4018
  -4.500  -0.2907   0.07994   0.07498  -0.0038   0.9605   0.4239
  -4.250  -0.2683   0.07766   0.07271  -0.0084   0.9444   0.4567
  -4.000  -0.2285   0.07370   0.06872  -0.0088   0.9331   0.4829
  -3.750  -0.1375   0.04944   0.04242  -0.0766   0.9147   0.1822
  -3.500  -0.0855   0.04444   0.03646  -0.0842   0.9043   0.1669
  -3.250  -0.0437   0.04173   0.03342  -0.0878   0.8928   0.1629
  -3.000  -0.0089   0.03981   0.03107  -0.0899   0.8802   0.1609
  -2.750   0.0386   0.03801   0.02879  -0.0935   0.8705   0.1634
  -2.500   0.0723   0.03695   0.02733  -0.0948   0.8586   0.1659
  -2.250   0.1048   0.03619   0.02620  -0.0956   0.8478   0.1681
  -2.000   0.1479   0.03506   0.02509  -0.0980   0.8390   0.1748
  -1.750   0.1706   0.03497   0.02484  -0.0973   0.8278   0.1835
  -1.500   0.2177   0.03409   0.02394  -0.0998   0.8203   0.2007
  -1.250   0.2335   0.03432   0.02423  -0.0984   0.8097   0.2160
  -1.000   0.2773   0.03332   0.02377  -0.1007   0.8030   0.2931
  -0.750   0.2802   0.03223   0.02463  -0.0952   0.7950   0.6799
  -0.500   0.3205   0.03185   0.02447  -0.0959   0.7869   1.0000
  -0.250   0.3522   0.03263   0.02480  -0.0973   0.7795   1.0000
   0.000   0.3611   0.03399   0.02591  -0.0959   0.7710   1.0000
   0.250   0.4058   0.03445   0.02600  -0.0985   0.7653   1.0000
   0.500   0.3986   0.03635   0.02776  -0.0953   0.7566   1.0000
   0.750   0.4250   0.03735   0.02853  -0.0958   0.7503   1.0000
   1.000   0.4488   0.03852   0.02951  -0.0961   0.7447   1.0000
   1.250   0.4457   0.04047   0.03134  -0.0937   0.7378   1.0000
   1.500   0.4738   0.04152   0.03223  -0.0943   0.7319   1.0000
   1.750   0.4890   0.04306   0.03364  -0.0938   0.7264   1.0000
   2.000   0.4900   0.04498   0.03547  -0.0920   0.7199   1.0000
   2.250   0.5401   0.04526   0.03561  -0.0941   0.7112   1.0000
   2.500   0.5283   0.04756   0.03785  -0.0912   0.7026   1.0000
   2.750   0.5615   0.04804   0.03822  -0.0912   0.6886   1.0000
   3.000   0.6007   0.04799   0.03807  -0.0912   0.6723   1.0000
   3.250   0.6465   0.04741   0.03741  -0.0914   0.6562   1.0000
   3.500   0.6930   0.04678   0.03672  -0.0917   0.6429   1.0000
   3.750   0.6818   0.04953   0.03945  -0.0890   0.6305   1.0000
   4.000   0.7143   0.04991   0.03981  -0.0887   0.6194   1.0000
   4.250   0.7540   0.04971   0.03960  -0.0886   0.6080   1.0000
   4.500   0.7496   0.05227   0.04216  -0.0864   0.5939   1.0000
   4.750   0.7685   0.05341   0.04330  -0.0853   0.5806   1.0000
   5.000   0.8422   0.05071   0.04062  -0.0861   0.5710   1.0000
   5.250   0.8466   0.05256   0.04249  -0.0839   0.5548   1.0000
   5.500   0.8578   0.05399   0.04395  -0.0820   0.5385   1.0000
   5.750   0.8725   0.05520   0.04517  -0.0802   0.5222   1.0000
   6.000   0.8856   0.05664   0.04663  -0.0786   0.5061   1.0000
   6.250   0.9522   0.05394   0.04397  -0.0785   0.4973   1.0000
   6.500   0.9693   0.05517   0.04523  -0.0771   0.4836   1.0000
   6.750   0.9363   0.06086   0.05092  -0.0747   0.4673   1.0000
   7.000   0.8875   0.06942   0.05946  -0.0747   0.4521   1.0000
   7.250   0.9544   0.06601   0.05611  -0.0730   0.4478   1.0000
   7.500   0.8555   0.08043   0.07047  -0.0755   0.4364   1.0000
   7.750   0.9069   0.07901   0.06911  -0.0741   0.4306   1.0000
   8.000   0.8553   0.08865   0.07872  -0.0763   0.4273   1.0000
   8.250   0.8425   0.09449   0.08460  -0.0778   0.4275   1.0000
   8.500   0.8447   0.09917   0.08931  -0.0789   0.4292   1.0000
  10.500   0.8875   0.12558   0.11612  -0.0809   0.3797   1.0000
  10.750   0.8750   0.13101   0.12162  -0.0827   0.3789   1.0000
  11.000   0.8706   0.13646   0.12716  -0.0846   0.3807   1.0000
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