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GOE 464 AIRFOIL (goe464-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 464 AIRFOIL (goe464-il)
Reynolds number: 50,000
Max Cl/Cd: 19.5 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe464-il-50000.txt
Download as CSV file: xf-goe464-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 464 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1752   0.12517   0.11883  -0.0256   1.0000   0.0758
  -9.000  -0.1774   0.12342   0.11718  -0.0238   1.0000   0.0765
  -8.750  -0.1817   0.12222   0.11607  -0.0218   1.0000   0.0772
  -8.500  -0.1874   0.12125   0.11520  -0.0196   1.0000   0.0780
  -8.250  -0.1940   0.12049   0.11454  -0.0174   1.0000   0.0787
  -8.000  -0.2019   0.11992   0.11408  -0.0151   1.0000   0.0795
  -7.750  -0.2113   0.11963   0.11389  -0.0127   1.0000   0.0802
  -7.500  -0.2224   0.11964   0.11401  -0.0102   1.0000   0.0807
  -7.250  -0.2341   0.11993   0.11443  -0.0080   1.0000   0.0810
  -7.000  -0.2432   0.12033   0.11494  -0.0069   1.0000   0.0813
  -6.750  -0.2508   0.12075   0.11545  -0.0063   1.0000   0.0815
  -6.250  -0.2599   0.11831   0.11320  -0.0047   1.0000   0.0819
  -6.000  -0.2631   0.11533   0.11028  -0.0027   1.0000   0.0824
  -5.750  -0.2663   0.11335   0.10837  -0.0015   1.0000   0.0829
  -5.500  -0.2686   0.11173   0.10682  -0.0008   1.0000   0.0835
  -5.250  -0.2697   0.11018   0.10533  -0.0005   1.0000   0.0843
  -5.000  -0.2640   0.10843   0.10362  -0.0019   0.9986   0.0851
  -4.750  -0.2248   0.10508   0.10021  -0.0107   0.9869   0.0871
  -4.500  -0.1773   0.10313   0.09818  -0.0225   0.9735   0.0887
  -4.250  -0.1363   0.10043   0.09542  -0.0319   0.9606   0.0895
  -4.000  -0.1148   0.09542   0.09041  -0.0340   0.9502   0.0910
  -3.750  -0.0762   0.09189   0.08683  -0.0410   0.9387   0.0931
  -3.500  -0.0436   0.08940   0.08428  -0.0470   0.9253   0.0952
  -3.250   0.0101   0.08831   0.08303  -0.0583   0.9109   0.0971
  -3.000   0.0414   0.08458   0.07927  -0.0629   0.8992   0.0982
  -2.750   0.0773   0.08065   0.07530  -0.0676   0.8884   0.1011
  -2.500   0.1122   0.07874   0.07331  -0.0730   0.8744   0.1041
  -2.250   0.1708   0.07764   0.07201  -0.0835   0.8601   0.1063
  -2.000   0.2020   0.07335   0.06771  -0.0863   0.8502   0.1092
  -1.750   0.2737   0.07287   0.06695  -0.0982   0.8364   0.1154
  -1.500   0.2839   0.06962   0.06374  -0.0973   0.8232   0.1172
  -1.250   0.3209   0.06756   0.06160  -0.1013   0.8111   0.1223
  -1.000   0.3823   0.06475   0.05862  -0.1092   0.8012   0.1294
  -0.750   0.4262   0.06477   0.05842  -0.1145   0.7865   0.1381
  -0.500   0.4437   0.06240   0.05608  -0.1146   0.7742   0.1429
  -0.250   0.5107   0.05956   0.05303  -0.1222   0.7663   0.1566
   0.000   0.5357   0.05925   0.05261  -0.1237   0.7521   0.1678
   0.250   0.5633   0.05858   0.05185  -0.1254   0.7396   0.1814
   0.500   0.6286   0.05544   0.04851  -0.1315   0.7328   0.2092
   0.750   0.6455   0.05587   0.04883  -0.1316   0.7190   0.2324
   1.000   0.6623   0.05475   0.04772  -0.1314   0.7077   0.2658
   1.500   0.7054   0.05096   0.04396  -0.1310   0.6887   0.4436
   1.750   0.7546   0.04683   0.03974  -0.1323   0.6836   0.5613
   2.000   0.7596   0.04783   0.04068  -0.1309   0.6709   0.5974
   2.250   0.8402   0.04410   0.03654  -0.1363   0.6662   0.6791
   2.500   0.8494   0.04642   0.03876  -0.1363   0.6527   0.6813
   2.750   0.8644   0.04861   0.04083  -0.1368   0.6413   0.6716
   3.000   0.9280   0.04797   0.03983  -0.1408   0.6342   0.6394
   3.250   0.9134   0.05212   0.04397  -0.1388   0.6215   0.6330
   3.500   0.9876   0.05064   0.04210  -0.1425   0.6158   0.5759
   3.750   0.9470   0.05668   0.04826  -0.1391   0.6025   0.5841
   4.000   1.0312   0.05411   0.04530  -0.1423   0.5976   0.5238
   4.250   0.9702   0.06193   0.05329  -0.1384   0.5841   0.5412
   4.500   1.0572   0.05860   0.04964  -0.1407   0.5787   0.4875
   4.750   0.9875   0.06753   0.05874  -0.1374   0.5661   0.5069
   5.000   0.9987   0.07014   0.06128  -0.1369   0.5573   0.4901
   5.250   1.0070   0.07288   0.06398  -0.1364   0.5481   0.4755
   5.500   1.0083   0.07623   0.06733  -0.1357   0.5390   0.4656
   5.750   1.0332   0.07754   0.06856  -0.1353   0.5298   0.4482
   6.000   1.0191   0.08233   0.07338  -0.1347   0.5208   0.4449
   6.250   1.0710   0.08105   0.07197  -0.1340   0.5111   0.4252
   6.500   1.0297   0.08857   0.07960  -0.1338   0.5027   0.4299
   6.750   1.0898   0.08645   0.07735  -0.1326   0.4926   0.4070
   7.000   1.0407   0.09491   0.08595  -0.1331   0.4844   0.4155
   7.250   1.0775   0.09511   0.08609  -0.1320   0.4745   0.3981
   7.500   1.0500   0.10166   0.09273  -0.1325   0.4666   0.4002
   7.750   1.0758   0.10301   0.09403  -0.1316   0.4569   0.3866
   8.000   1.0508   0.10984   0.10094  -0.1327   0.4522   0.3880
   8.250   1.0865   0.11012   0.10117  -0.1313   0.4410   0.3730
   8.500   1.0584   0.11743   0.10856  -0.1328   0.4376   0.3748
   8.750   1.0486   0.12328   0.11448  -0.1342   0.4374   0.3732
   9.000   1.0504   0.12868   0.11994  -0.1356   0.4404   0.3691
   9.250   1.0652   0.13343   0.12473  -0.1367   0.4429   0.3615
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