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GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 6K AIRFOIL (goe06k-il)
Reynolds number: 200,000
Max Cl/Cd: 76.99 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe06k-il-200000-n5.txt
Download as CSV file: xf-goe06k-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 6K 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4422   0.11549   0.11201  -0.0273   1.0000   0.0137
  -9.250  -0.4441   0.11286   0.10941  -0.0268   1.0000   0.0140
  -9.000  -0.4467   0.11035   0.10693  -0.0262   1.0000   0.0147
  -8.750  -0.4408   0.10675   0.10335  -0.0283   0.9988   0.0145
  -8.500  -0.4314   0.10287   0.09948  -0.0317   0.9967   0.0153
  -8.250  -0.4224   0.09925   0.09588  -0.0375   0.9936   0.0167
  -8.000  -0.4138   0.09571   0.09236  -0.0438   0.9895   0.0171
  -7.500  -0.3957   0.08753   0.08419  -0.0533   0.9808   0.0172
  -7.000  -0.3779   0.07665   0.07329  -0.0618   0.9719   0.0178
  -6.750  -0.3675   0.07258   0.06919  -0.0632   0.9694   0.0185
  -6.500  -0.3568   0.06873   0.06530  -0.0656   0.9647   0.0190
  -6.250  -0.3432   0.06471   0.06121  -0.0684   0.9600   0.0195
  -6.000  -0.3233   0.06010   0.05650  -0.0726   0.9570   0.0204
  -5.750  -0.3098   0.05614   0.05242  -0.0742   0.9519   0.0209
  -5.500  -0.2931   0.05217   0.04830  -0.0758   0.9471   0.0213
  -5.250  -0.2702   0.04767   0.04359  -0.0782   0.9441   0.0214
  -5.000  -0.2419   0.04016   0.03557  -0.0800   0.9418   0.0121
  -4.750  -0.2331   0.03726   0.03246  -0.0776   0.9353   0.0116
  -4.500  -0.2122   0.03371   0.02859  -0.0772   0.9321   0.0108
  -4.250  -0.1877   0.02975   0.02416  -0.0768   0.9298   0.0107
  -4.000  -0.1608   0.02636   0.02024  -0.0764   0.9282   0.0117
  -3.750  -0.1432   0.02390   0.01734  -0.0740   0.9238   0.0118
  -3.500  -0.1218   0.02149   0.01441  -0.0722   0.9204   0.0120
  -3.250  -0.0954   0.01949   0.01193  -0.0714   0.9184   0.0124
  -3.000  -0.0676   0.01832   0.01057  -0.0715   0.9166   0.0143
  -2.750  -0.0382   0.01722   0.00927  -0.0717   0.9153   0.0160
  -2.500  -0.0091   0.01602   0.00790  -0.0718   0.9140   0.0178
  -2.250   0.0112   0.01549   0.00732  -0.0703   0.9099   0.0227
  -2.000   0.0326   0.01499   0.00670  -0.0690   0.9060   0.0282
  -1.750   0.0599   0.01463   0.00631  -0.0689   0.9036   0.0441
  -1.500   0.0885   0.01420   0.00588  -0.0692   0.9017   0.0704
  -1.250   0.1175   0.01368   0.00556  -0.0698   0.9003   0.1301
  -0.750   0.2602   0.01168   0.00586  -0.0905   0.9078   1.0000
  -0.500   0.2867   0.01168   0.00575  -0.0904   0.9045   1.0000
  -0.250   0.3165   0.01166   0.00562  -0.0909   0.9023   1.0000
   0.000   0.3478   0.01163   0.00552  -0.0919   0.9007   1.0000
   0.250   0.3805   0.01159   0.00542  -0.0931   0.8994   1.0000
   0.750   0.4230   0.01178   0.00555  -0.0906   0.8897   1.0000
   1.000   0.4533   0.01178   0.00555  -0.0914   0.8875   1.0000
   1.250   0.4859   0.01175   0.00554  -0.0926   0.8859   1.0000
   1.500   0.5218   0.01168   0.00550  -0.0945   0.8844   1.0000
   1.750   0.5347   0.01181   0.00568  -0.0913   0.8758   1.0000
   2.000   0.5722   0.01161   0.00555  -0.0933   0.8724   1.0000
   2.250   0.6017   0.01144   0.00546  -0.0936   0.8650   1.0000
   2.500   0.6386   0.01116   0.00528  -0.0953   0.8579   1.0000
   2.750   0.6623   0.01107   0.00529  -0.0942   0.8480   1.0000
   3.000   0.6931   0.01082   0.00517  -0.0945   0.8351   1.0000
   3.250   0.7270   0.01040   0.00485  -0.0951   0.8094   1.0000
   3.500   0.7784   0.01011   0.00393  -0.0987   0.6335   1.0000
   3.750   0.7603   0.01159   0.00428  -0.0886   0.4348   1.0000
   4.000   0.7473   0.01321   0.00494  -0.0806   0.2452   1.0000
   4.250   0.7458   0.01474   0.00565  -0.0752   0.0861   1.0000
   4.750   0.7683   0.01656   0.00719  -0.0686   0.0184   1.0000
   5.000   0.7837   0.01722   0.00800  -0.0661   0.0156   1.0000
   5.250   0.7966   0.01814   0.00900  -0.0632   0.0134   1.0000
   5.500   0.8117   0.01896   0.00992  -0.0607   0.0116   1.0000
   5.750   0.8272   0.01997   0.01102  -0.0583   0.0108   1.0000
   6.000   0.8454   0.02144   0.01252  -0.0567   0.0100   1.0000
   6.250   0.8751   0.02333   0.01460  -0.0571   0.0095   1.0000
   6.500   0.9037   0.02494   0.01645  -0.0572   0.0081   1.0000
   6.750   0.9313   0.02688   0.01858  -0.0574   0.0075   1.0000
   7.000   0.9594   0.02985   0.02186  -0.0575   0.0073   1.0000
   7.250   0.9806   0.03284   0.02532  -0.0560   0.0072   1.0000
   7.500   0.9954   0.03598   0.02887  -0.0534   0.0073   1.0000
   8.000   1.0093   0.04481   0.03897  -0.0439   0.0084   1.0000
   8.250   1.0092   0.04856   0.04307  -0.0393   0.0087   1.0000
   8.500   1.0066   0.05198   0.04679  -0.0347   0.0089   1.0000
   8.750   1.0014   0.05537   0.05045  -0.0300   0.0090   1.0000
   9.000   0.9937   0.05875   0.05409  -0.0252   0.0085   1.0000
   9.250   0.9820   0.06164   0.05717  -0.0202   0.0085   1.0000
   9.500   0.9659   0.06488   0.06059  -0.0152   0.0087   1.0000
   9.750   0.9514   0.06783   0.06369  -0.0113   0.0082   1.0000
  10.000   0.9369   0.07120   0.06718  -0.0082   0.0105   1.0000
  10.250   0.9208   0.07438   0.07048  -0.0059   0.0103   1.0000
  10.500   0.8979   0.07971   0.07598  -0.0046   0.0106   1.0000
  10.750   0.8832   0.08339   0.07974  -0.0046   0.0104   1.0000
  11.000   0.8675   0.08795   0.08438  -0.0058   0.0102   1.0000
  11.250   0.8544   0.09238   0.08885  -0.0076   0.0101   1.0000
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