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GOE 403 AIRFOIL (goe403-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 403 AIRFOIL (goe403-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.08 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe403-il-1000000.txt
Download as CSV file: xf-goe403-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 403 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3661   0.10737   0.10574  -0.0209   1.0000   0.0076
  -9.250  -0.3621   0.10394   0.10232  -0.0219   1.0000   0.0076
  -9.000  -0.3657   0.09886   0.09727  -0.0231   1.0000   0.0079
  -8.750  -0.3592   0.09681   0.09523  -0.0232   1.0000   0.0084
  -8.500  -0.3559   0.09380   0.09224  -0.0240   1.0000   0.0084
  -8.250  -0.3508   0.09158   0.09003  -0.0243   1.0000   0.0089
  -8.000  -0.3476   0.08914   0.08762  -0.0247   1.0000   0.0097
  -7.750  -0.3473   0.08652   0.08502  -0.0248   1.0000   0.0100
  -6.250  -0.2417   0.01564   0.01242  -0.0942   0.9613   0.0079
  -6.000  -0.2129   0.01184   0.00788  -0.0956   0.9499   0.0089
  -5.750  -0.1814   0.01126   0.00716  -0.0964   0.9357   0.0098
  -5.500  -0.1522   0.01068   0.00639  -0.0967   0.9170   0.0108
  -5.250  -0.1252   0.01013   0.00563  -0.0965   0.8966   0.0116
  -5.000  -0.0989   0.00977   0.00508  -0.0960   0.8784   0.0121
  -4.750  -0.0734   0.00897   0.00409  -0.0955   0.8639   0.0151
  -4.500  -0.0462   0.00908   0.00417  -0.0952   0.8518   0.0172
  -4.250  -0.0188   0.00928   0.00433  -0.0950   0.8416   0.0184
  -3.750   0.0346   0.00874   0.00362  -0.0944   0.8234   0.0253
  -3.500   0.0621   0.00890   0.00373  -0.0943   0.8153   0.0269
  -3.250   0.0887   0.00857   0.00329  -0.0940   0.8070   0.0287
  -3.000   0.1150   0.00801   0.00262  -0.0936   0.7990   0.0312
  -2.500   0.1690   0.00766   0.00217  -0.0931   0.7824   0.0358
  -2.250   0.1961   0.00754   0.00199  -0.0929   0.7739   0.0379
  -2.000   0.2231   0.00743   0.00181  -0.0926   0.7643   0.0388
  -1.750   0.2503   0.00731   0.00164  -0.0924   0.7541   0.0393
  -1.500   0.2771   0.00706   0.00130  -0.0921   0.7429   0.0410
  -1.250   0.3040   0.00692   0.00109  -0.0918   0.7298   0.0434
  -1.000   0.3308   0.00683   0.00095  -0.0914   0.7142   0.0478
  -0.750   0.3571   0.00670   0.00085  -0.0911   0.6952   0.0747
  -0.500   0.3835   0.00667   0.00082  -0.0907   0.6718   0.1047
  -0.250   0.4096   0.00672   0.00080  -0.0903   0.6450   0.1184
   0.000   0.4356   0.00679   0.00078  -0.0899   0.6164   0.1318
   0.250   0.4615   0.00685   0.00079  -0.0895   0.5899   0.1511
   0.500   0.4876   0.00687   0.00082  -0.0892   0.5688   0.1908
   0.750   0.5135   0.00676   0.00089  -0.0890   0.5517   0.2865
   1.000   0.5378   0.00634   0.00100  -0.0886   0.5372   0.5224
   1.250   0.5754   0.00539   0.00109  -0.0909   0.5223   1.0000
   1.500   0.6016   0.00551   0.00115  -0.0905   0.5104   1.0000
   1.750   0.6275   0.00567   0.00120  -0.0901   0.4916   1.0000
   2.000   0.6533   0.00583   0.00126  -0.0897   0.4725   1.0000
   2.250   0.6796   0.00596   0.00132  -0.0894   0.4595   1.0000
   2.500   0.7058   0.00609   0.00140  -0.0890   0.4421   1.0000
   2.750   0.7313   0.00630   0.00148  -0.0886   0.4153   1.0000
   3.000   0.7560   0.00660   0.00159  -0.0880   0.3757   1.0000
   3.250   0.7777   0.00723   0.00182  -0.0871   0.2941   1.0000
   3.500   0.7867   0.00949   0.00282  -0.0843   0.0238   1.0000
   3.750   0.8125   0.00971   0.00307  -0.0838   0.0160   1.0000
   4.000   0.8382   0.00996   0.00336  -0.0834   0.0145   1.0000
   4.250   0.8633   0.01026   0.00371  -0.0828   0.0131   1.0000
   4.500   0.8877   0.01069   0.00420  -0.0821   0.0115   1.0000
   4.750   0.9105   0.01132   0.00492  -0.0811   0.0106   1.0000
   5.000   0.9320   0.01210   0.00582  -0.0799   0.0097   1.0000
   5.250   0.9557   0.01254   0.00630  -0.0791   0.0094   1.0000
   5.500   0.9786   0.01308   0.00688  -0.0782   0.0089   1.0000
   5.750   1.0006   0.01370   0.00756  -0.0772   0.0084   1.0000
   6.000   1.0212   0.01446   0.00838  -0.0759   0.0078   1.0000
   6.250   1.0404   0.01540   0.00937  -0.0743   0.0074   1.0000
   6.500   1.0568   0.01683   0.01091  -0.0721   0.0076   1.0000
   7.000   1.0754   0.01359   0.00800  -0.0669   0.0098   1.0000
   7.250   1.0969   0.01526   0.00981  -0.0659   0.0098   1.0000
   7.500   1.1169   0.01699   0.01170  -0.0647   0.0098   1.0000
   7.750   1.1357   0.01830   0.01317  -0.0634   0.0096   1.0000
   8.000   1.1569   0.01684   0.01177  -0.0621   0.0083   1.0000
   8.250   1.1757   0.01813   0.01320  -0.0608   0.0075   1.0000
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