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GOE 381 AIRFOIL (goe381-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 381 AIRFOIL (goe381-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.87 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe381-il-1000000.txt
Download as CSV file: xf-goe381-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 381 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.2495   0.08589   0.08441  -0.0313   0.9482   0.0087
  -7.000  -0.2363   0.08262   0.08110  -0.0347   0.9359   0.0087
  -6.750  -0.2267   0.07818   0.07662  -0.0373   0.9258   0.0089
  -6.500  -0.2128   0.07524   0.07365  -0.0395   0.9161   0.0091
  -6.250  -0.1955   0.07222   0.07059  -0.0427   0.9065   0.0093
  -6.000  -0.1764   0.06911   0.06743  -0.0463   0.8971   0.0095
  -5.750  -0.1549   0.06588   0.06415  -0.0502   0.8871   0.0098
  -5.500  -0.1315   0.06256   0.06078  -0.0544   0.8778   0.0103
  -5.250  -0.1062   0.05913   0.05726  -0.0586   0.8689   0.0110
  -5.000  -0.0441   0.03728   0.03537  -0.0629   0.8312   0.0121
  -4.750  -0.0187   0.03307   0.03106  -0.0670   0.8224   0.0122
  -4.250   0.0157   0.04322   0.04096  -0.0770   0.8301   0.0129
  -4.000   0.0421   0.04113   0.03876  -0.0789   0.8171   0.0136
  -3.750   0.0719   0.03860   0.03610  -0.0812   0.8019   0.0149
  -3.500   0.1126   0.03583   0.03310  -0.0841   0.7866   0.0165
  -3.250   0.1436   0.03263   0.02970  -0.0859   0.7699   0.0165
  -2.500   0.2275   0.02483   0.02124  -0.0895   0.6912   0.0191
  -2.250   0.2592   0.02413   0.02023  -0.0892   0.6505   0.0223
  -1.500   0.3468   0.01651   0.01162  -0.0908   0.5807   0.0249
  -1.250   0.3739   0.01643   0.01145  -0.0909   0.5656   0.0287
  -1.000   0.4031   0.01629   0.01116  -0.0904   0.5517   0.0311
  -0.750   0.4320   0.01471   0.00931  -0.0904   0.5399   0.0312
  -0.500   0.4607   0.01174   0.00593  -0.0909   0.5305   0.0344
  -0.250   0.4886   0.01138   0.00548  -0.0909   0.5213   0.0365
   0.000   0.5171   0.00997   0.00375  -0.0906   0.5128   0.0328
   0.250   0.5451   0.00970   0.00340  -0.0906   0.5039   0.0322
   0.500   0.5728   0.00929   0.00290  -0.0905   0.4953   0.0323
   0.750   0.6005   0.00905   0.00260  -0.0905   0.4857   0.0320
   1.000   0.6283   0.00872   0.00222  -0.0904   0.4760   0.0322
   1.250   0.6560   0.00844   0.00185  -0.0904   0.4655   0.0337
   1.500   0.6837   0.00836   0.00171  -0.0904   0.4531   0.0350
   1.750   0.7113   0.00835   0.00164  -0.0904   0.4376   0.0358
   2.000   0.7386   0.00840   0.00160  -0.0903   0.4158   0.0364
   2.250   0.7655   0.00855   0.00161  -0.0902   0.3859   0.0370
   2.500   0.7917   0.00882   0.00169  -0.0900   0.3454   0.0385
   2.750   0.8178   0.00910   0.00180  -0.0899   0.3101   0.0396
   3.000   0.8442   0.00935   0.00191  -0.0897   0.2854   0.0416
   3.250   0.8710   0.00949   0.00207  -0.0897   0.2689   0.0843
   3.500   0.8978   0.00967   0.00225  -0.0896   0.2566   0.1042
   4.000   0.9510   0.01005   0.00255  -0.0894   0.2312   0.1262
   4.250   0.9779   0.01017   0.00270  -0.0894   0.2218   0.1554
   4.500   1.0006   0.00895   0.00302  -0.0889   0.2108   1.0000
   4.750   1.0270   0.00918   0.00318  -0.0888   0.2001   1.0000
   5.000   1.0532   0.00945   0.00336  -0.0886   0.1836   1.0000
   5.250   1.0759   0.01020   0.00375  -0.0881   0.1282   1.0000
   5.500   1.1002   0.01071   0.00414  -0.0878   0.1083   1.0000
   5.750   1.1243   0.01123   0.00450  -0.0874   0.0838   1.0000
   6.000   1.1445   0.01234   0.00530  -0.0864   0.0157   1.0000
   6.250   1.1698   0.01268   0.00570  -0.0861   0.0141   1.0000
   6.500   1.1944   0.01310   0.00618  -0.0856   0.0124   1.0000
   6.750   1.2182   0.01364   0.00681  -0.0851   0.0110   1.0000
   7.000   1.2403   0.01440   0.00769  -0.0842   0.0101   1.0000
   7.250   1.2644   0.01483   0.00816  -0.0837   0.0096   1.0000
   7.500   1.2877   0.01533   0.00871  -0.0832   0.0088   1.0000
   7.750   1.3100   0.01596   0.00939  -0.0825   0.0082   1.0000
   8.000   1.3314   0.01667   0.01018  -0.0816   0.0078   1.0000
   8.250   1.3516   0.01745   0.01104  -0.0806   0.0074   1.0000
   8.500   1.3696   0.01845   0.01211  -0.0794   0.0070   1.0000
   8.750   1.3793   0.02019   0.01398  -0.0769   0.0066   1.0000
   9.000   1.3849   0.02214   0.01606  -0.0740   0.0063   1.0000
   9.250   1.4028   0.02285   0.01684  -0.0727   0.0061   1.0000
   9.500   1.4150   0.02400   0.01808  -0.0707   0.0059   1.0000
   9.750   1.4243   0.02512   0.01928  -0.0682   0.0057   1.0000
  10.000   1.4322   0.02628   0.02051  -0.0656   0.0055   1.0000
  10.250   1.4384   0.02763   0.02195  -0.0631   0.0053   1.0000
  10.500   1.4420   0.02934   0.02374  -0.0604   0.0052   1.0000
  10.750   1.4458   0.03120   0.02569  -0.0580   0.0052   1.0000
  11.000   1.4503   0.03312   0.02769  -0.0559   0.0051   1.0000
  11.250   1.4554   0.03509   0.02975  -0.0539   0.0050   1.0000
  11.500   1.4610   0.03712   0.03189  -0.0521   0.0050   1.0000
  11.750   1.4666   0.03929   0.03415  -0.0503   0.0049   1.0000
  12.000   1.4712   0.04140   0.03637  -0.0488   0.0048   1.0000
  12.250   1.4752   0.04376   0.03883  -0.0473   0.0047   1.0000
  12.500   1.4772   0.04605   0.04121  -0.0462   0.0045   1.0000
  12.750   1.4790   0.04835   0.04357  -0.0454   0.0044   1.0000
  13.000   1.4787   0.05100   0.04631  -0.0447   0.0043   1.0000
  13.250   1.4781   0.05396   0.04936  -0.0438   0.0041   1.0000
  13.500   1.4762   0.05746   0.05298  -0.0426   0.0041   1.0000
  13.750   1.4711   0.06127   0.05696  -0.0419   0.0041   1.0000
  14.000   1.4204   0.07686   0.07329  -0.0382   0.0062   1.0000
  14.250   1.4039   0.08151   0.07809  -0.0393   0.0062   1.0000
  14.500   1.3871   0.08643   0.08316  -0.0410   0.0062   1.0000
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