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GOE 207 (AVIATIK V8) AIRFOIL (goe207-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 207 (AVIATIK V8) AIRFOIL (goe207-il)
Reynolds number: 100,000
Max Cl/Cd: 47.42 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe207-il-100000.txt
Download as CSV file: xf-goe207-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 207 (AVIATIK V8) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2359   0.10400   0.09965  -0.0151   1.0000   0.0471
  -7.750  -0.2286   0.10139   0.09711  -0.0163   1.0000   0.0480
  -7.500  -0.2225   0.09898   0.09478  -0.0174   1.0000   0.0489
  -7.250  -0.2181   0.09684   0.09272  -0.0186   1.0000   0.0498
  -7.000  -0.2145   0.09514   0.09115  -0.0203   1.0000   0.0509
  -6.750  -0.2287   0.09517   0.09136  -0.0185   1.0000   0.0513
  -6.250  -0.1563   0.08686   0.08301  -0.0393   0.9728   0.0530
  -6.000  -0.1238   0.08149   0.07763  -0.0435   0.9572   0.0544
  -5.750  -0.0888   0.07727   0.07334  -0.0500   0.9358   0.0561
  -5.500  -0.0582   0.07386   0.06984  -0.0555   0.9101   0.0581
  -5.250  -0.0297   0.07156   0.06739  -0.0609   0.8822   0.0603
  -5.000   0.0165   0.07178   0.06722  -0.0721   0.8556   0.0616
  -4.750   0.0194   0.06677   0.06227  -0.0682   0.8331   0.0622
  -4.500   0.0302   0.06346   0.05891  -0.0665   0.8120   0.0635
  -4.250   0.0487   0.06090   0.05623  -0.0671   0.7924   0.0655
  -4.000   0.0728   0.05861   0.05377  -0.0691   0.7740   0.0680
  -3.750   0.1245   0.05917   0.05380  -0.0771   0.7556   0.0717
  -3.500   0.1424   0.05524   0.04982  -0.0775   0.7395   0.0725
  -3.250   0.1579   0.05182   0.04638  -0.0769   0.7237   0.0739
  -3.000   0.1812   0.04945   0.04389  -0.0778   0.7082   0.0764
  -2.750   0.2114   0.04766   0.04188  -0.0799   0.6929   0.0803
  -2.500   0.2520   0.04675   0.04058  -0.0835   0.6780   0.0841
  -2.250   0.2712   0.04362   0.03743  -0.0836   0.6645   0.0865
  -2.000   0.3106   0.04398   0.03733  -0.0858   0.6501   0.0956
  -1.750   0.3328   0.04043   0.03372  -0.0866   0.6377   0.0982
  -1.500   0.3588   0.03847   0.03168  -0.0873   0.6236   0.1036
  -1.250   0.3935   0.03750   0.03039  -0.0890   0.6099   0.1118
  -1.000   0.4193   0.03558   0.02836  -0.0896   0.5970   0.1186
  -0.750   0.4504   0.03433   0.02682  -0.0906   0.5849   0.1285
  -0.500   0.4811   0.03331   0.02554  -0.0915   0.5722   0.1420
  -0.250   0.5100   0.03202   0.02412  -0.0923   0.5591   0.1574
   0.000   0.5379   0.03068   0.02264  -0.0929   0.5472   0.1763
   0.250   0.5660   0.02955   0.02126  -0.0935   0.5369   0.2100
   0.500   0.5915   0.02787   0.01960  -0.0943   0.5245   0.2689
   0.750   0.6185   0.02652   0.01818  -0.0948   0.5134   0.3197
   1.000   0.6477   0.02547   0.01690  -0.0950   0.5041   0.3532
   1.250   0.6782   0.02479   0.01615  -0.0955   0.4925   0.3731
   1.500   0.7102   0.02450   0.01560  -0.0958   0.4833   0.3759
   1.750   0.7438   0.02452   0.01534  -0.0960   0.4738   0.3393
   2.000   0.7804   0.02586   0.01612  -0.0952   0.4653   0.2290
   2.250   0.8126   0.02587   0.01584  -0.0944   0.4575   0.1653
   2.500   0.8431   0.02607   0.01569  -0.0938   0.4504   0.1392
   2.750   0.8721   0.02588   0.01536  -0.0934   0.4427   0.1248
   3.000   0.9003   0.02537   0.01471  -0.0931   0.4374   0.1193
   3.250   0.9275   0.02534   0.01477  -0.0928   0.4295   0.1151
   3.500   0.9545   0.02520   0.01452  -0.0923   0.4239   0.1150
   3.750   0.9810   0.02533   0.01460  -0.0919   0.4183   0.1213
   4.000   1.0074   0.02550   0.01478  -0.0916   0.4121   0.1259
   4.250   1.0353   0.02561   0.01478  -0.0914   0.4075   0.1356
   4.500   1.0629   0.02597   0.01511  -0.0915   0.4034   0.1633
   4.750   1.0842   0.02516   0.01561  -0.0901   0.3987   1.0000
   5.000   1.1105   0.02584   0.01612  -0.0900   0.3945   1.0000
   5.250   1.1373   0.02646   0.01660  -0.0899   0.3912   1.0000
   5.500   1.1635   0.02728   0.01735  -0.0898   0.3882   1.0000
   5.750   1.1864   0.02844   0.01870  -0.0897   0.3843   1.0000
   6.000   1.2105   0.02947   0.01982  -0.0896   0.3810   1.0000
   6.250   1.2351   0.03040   0.02080  -0.0894   0.3782   1.0000
   6.500   1.2607   0.03119   0.02158  -0.0893   0.3756   1.0000
   6.750   1.2872   0.03198   0.02228  -0.0893   0.3732   1.0000
   7.000   1.3042   0.03371   0.02439  -0.0888   0.3692   1.0000
   7.250   1.3240   0.03509   0.02595  -0.0884   0.3655   1.0000
   7.500   1.3487   0.03567   0.02656  -0.0881   0.3618   1.0000
   7.750   1.3791   0.03528   0.02594  -0.0879   0.3566   1.0000
   8.000   1.3941   0.03642   0.02741  -0.0869   0.3495   1.0000
   8.250   1.4314   0.03466   0.02521  -0.0869   0.3415   1.0000
   8.500   1.4448   0.03585   0.02677  -0.0857   0.3348   1.0000
   8.750   1.4735   0.03528   0.02608  -0.0854   0.3283   1.0000
   9.000   1.4952   0.03572   0.02662  -0.0847   0.3227   1.0000
   9.250   1.5152   0.03595   0.02699  -0.0838   0.3156   1.0000
   9.500   1.5423   0.03520   0.02612  -0.0833   0.3072   1.0000
   9.750   1.5615   0.03507   0.02614  -0.0821   0.2986   1.0000
  10.000   1.5823   0.03483   0.02593  -0.0811   0.2900   1.0000
  10.250   1.6028   0.03453   0.02566  -0.0800   0.2815   1.0000
  10.500   1.6158   0.03464   0.02594  -0.0781   0.2715   1.0000
  10.750   1.6318   0.03441   0.02571  -0.0765   0.2615   1.0000
  11.000   1.6413   0.03488   0.02642  -0.0744   0.2522   1.0000
  11.250   1.6500   0.03555   0.02725  -0.0723   0.2440   1.0000
  11.500   1.6552   0.03622   0.02801  -0.0698   0.2347   1.0000
  11.750   1.6535   0.03761   0.02965  -0.0669   0.2263   1.0000
  12.000   1.6521   0.03916   0.03130  -0.0646   0.2175   1.0000
  12.250   1.6486   0.04139   0.03373  -0.0631   0.2079   1.0000
  12.500   1.6413   0.04439   0.03694  -0.0623   0.1956   1.0000
  12.750   1.6324   0.04801   0.04076  -0.0622   0.1823   1.0000
  13.000   1.6194   0.05245   0.04536  -0.0626   0.1618   1.0000
  13.250   1.5936   0.05877   0.05165  -0.0640   0.1400   1.0000
  13.500   1.5663   0.06583   0.05880  -0.0659   0.1338   1.0000
  14.250   1.4262   0.09893   0.09315  -0.0757   0.1873   1.0000
  14.500   1.3777   0.11101   0.10534  -0.0798   0.1878   1.0000
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