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GOE 735 AIRFOIL (goe735-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 735 AIRFOIL (goe735-il)
Reynolds number: 100,000
Max Cl/Cd: 23.43 at α=1.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe735-il-100000.txt
Download as CSV file: xf-goe735-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 735 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1323   0.10301   0.09791  -0.0512   0.8205   0.2044
 -10.500  -0.3929   0.06647   0.06121  -0.0793   0.8342   0.1447
 -10.250  -0.4212   0.06235   0.05693  -0.0769   0.8243   0.1442
 -10.000  -0.4544   0.05886   0.05327  -0.0732   0.8126   0.1439
  -9.750  -0.4883   0.05542   0.04951  -0.0684   0.8043   0.1439
  -9.500  -0.5181   0.05211   0.04580  -0.0639   0.7931   0.1446
  -9.250  -0.4652   0.05257   0.04664  -0.0652   0.7823   0.1495
  -9.000  -0.4696   0.05050   0.04438  -0.0624   0.7714   0.1517
  -8.750  -0.4790   0.04812   0.04167  -0.0585   0.7638   0.1537
  -8.500  -0.4859   0.04577   0.03898  -0.0551   0.7531   0.1561
  -8.250  -0.4929   0.04364   0.03632  -0.0506   0.7461   0.1585
  -8.000  -0.4845   0.04174   0.03423  -0.0486   0.7355   0.1613
  -7.750  -0.4596   0.04102   0.03361  -0.0478   0.7271   0.1652
  -7.500  -0.4457   0.03990   0.03232  -0.0460   0.7175   0.1685
  -7.250  -0.4354   0.03856   0.03064  -0.0434   0.7092   0.1721
  -7.000  -0.4263   0.03744   0.02900  -0.0401   0.7031   0.1751
  -6.750  -0.4058   0.03599   0.02760  -0.0396   0.6924   0.1784
  -6.500  -0.3832   0.03510   0.02664  -0.0383   0.6858   0.1822
  -6.250  -0.3637   0.03436   0.02576  -0.0371   0.6767   0.1860
  -6.000  -0.3451   0.03348   0.02459  -0.0354   0.6690   0.1898
  -5.750  -0.3245   0.03239   0.02318  -0.0337   0.6638   0.1934
  -5.500  -0.3011   0.03174   0.02263  -0.0335   0.6537   0.1973
  -5.250  -0.2769   0.03100   0.02176  -0.0324   0.6471   0.2017
  -5.000  -0.2532   0.03034   0.02087  -0.0312   0.6417   0.2066
  -4.750  -0.2313   0.02993   0.02036  -0.0306   0.6324   0.2110
  -4.500  -0.2036   0.02909   0.01954  -0.0302   0.6265   0.2162
  -4.250  -0.1780   0.02860   0.01894  -0.0294   0.6209   0.2224
  -4.000  -0.1558   0.02849   0.01870  -0.0287   0.6121   0.2284
  -3.750  -0.1266   0.02764   0.01794  -0.0286   0.6066   0.2355
  -3.500  -0.0997   0.02720   0.01740  -0.0279   0.6019   0.2440
  -3.250  -0.0769   0.02714   0.01747  -0.0276   0.5934   0.2524
  -3.000  -0.0505   0.02672   0.01703  -0.0270   0.5879   0.2638
  -2.750  -0.0218   0.02607   0.01638  -0.0265   0.5839   0.2771
  -2.500  -0.0021   0.02626   0.01676  -0.0258   0.5756   0.2921
  -2.250   0.0220   0.02592   0.01654  -0.0250   0.5698   0.3134
  -2.000   0.0474   0.02535   0.01610  -0.0241   0.5659   0.3465
  -1.750   0.0663   0.02508   0.01621  -0.0227   0.5606   0.3975
  -1.500   0.0783   0.02478   0.01667  -0.0204   0.5538   0.4978
  -1.250   0.1587   0.02408   0.01713  -0.0267   0.5480   0.7950
  -1.000   0.2214   0.02469   0.01751  -0.0303   0.5436   0.8575
  -0.750   0.2718   0.02638   0.01923  -0.0340   0.5350   0.8865
  -0.500   0.3215   0.02706   0.01972  -0.0366   0.5298   0.9130
  -0.250   0.3921   0.02732   0.01966  -0.0426   0.5254   0.9327
   0.000   0.4508   0.02848   0.02083  -0.0490   0.5173   0.9520
   0.250   0.5185   0.02867   0.02087  -0.0562   0.5113   0.9713
   0.500   0.6075   0.02804   0.01994  -0.0669   0.5066   0.9952
   0.750   0.6363   0.02864   0.02055  -0.0687   0.5016   1.0000
   1.000   0.6473   0.02957   0.02155  -0.0676   0.4960   1.0000
   1.250   0.6635   0.02985   0.02176  -0.0664   0.4919   1.0000
   1.500   0.6822   0.02992   0.02171  -0.0651   0.4886   1.0000
   1.750   0.7028   0.02999   0.02162  -0.0640   0.4860   1.0000
   2.000   0.7004   0.03231   0.02418  -0.0621   0.4800   1.0000
   2.250   0.7040   0.03387   0.02582  -0.0600   0.4750   1.0000
   2.500   0.7191   0.03432   0.02622  -0.0585   0.4717   1.0000
   2.750   0.7409   0.03425   0.02603  -0.0573   0.4691   1.0000
   3.000   0.7653   0.03413   0.02575  -0.0563   0.4668   1.0000
   3.250   0.5223   0.05190   0.04430  -0.0373   0.4500   1.0000
   3.500   0.6065   0.04804   0.04029  -0.0398   0.4502   1.0000
   3.750   0.6578   0.04614   0.03824  -0.0404   0.4494   1.0000
   4.000   0.7144   0.04398   0.03593  -0.0415   0.4486   1.0000
   4.250   0.7572   0.04287   0.03467  -0.0419   0.4474   1.0000
   4.500   0.3115   0.07886   0.07130  -0.0220   0.4451   1.0000
   4.750   0.3333   0.08078   0.07316  -0.0215   0.4465   1.0000
   5.000   0.2256   0.09011   0.08268  -0.0205   0.4759   1.0000
   5.250   0.2425   0.09157   0.08408  -0.0198   0.4715   1.0000
   5.500   0.2692   0.09340   0.08584  -0.0196   0.4687   1.0000
   5.750   0.3066   0.09596   0.08833  -0.0199   0.4670   1.0000
   6.000   0.2598   0.09689   0.08927  -0.0170   0.4560   1.0000
   6.250   0.2798   0.09845   0.09076  -0.0164   0.4516   1.0000
   6.500   0.3082   0.10053   0.09278  -0.0163   0.4492   1.0000
   6.750   0.3449   0.10346   0.09566  -0.0167   0.4478   1.0000
   7.000   0.2953   0.10415   0.09637  -0.0142   0.4364   1.0000
   7.250   0.3173   0.10582   0.09799  -0.0139   0.4323   1.0000
   7.500   0.3488   0.10818   0.10030  -0.0139   0.4300   1.0000
   7.750   0.3860   0.11152   0.10360  -0.0144   0.4288   1.0000
   8.000   0.3309   0.11188   0.10398  -0.0123   0.4172   1.0000
   8.250   0.3532   0.11370   0.10577  -0.0120   0.4134   1.0000
   8.500   0.3849   0.11626   0.10828  -0.0120   0.4113   1.0000
   8.750   0.4263   0.12012   0.11211  -0.0127   0.4101   1.0000
   9.000   0.3666   0.11998   0.11200  -0.0110   0.3984   1.0000
   9.250   0.3869   0.12197   0.11397  -0.0108   0.3952   1.0000
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