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GOE 397 AIRFOIL (goe397-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 397 AIRFOIL (goe397-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.94 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe397-il-1000000.txt
Download as CSV file: xf-goe397-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 397 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4009   0.08969   0.08811  -0.0186   1.0000   0.0101
  -7.750  -0.4006   0.08686   0.08530  -0.0191   1.0000   0.0101
  -7.500  -0.4042   0.08225   0.08072  -0.0203   1.0000   0.0104
  -7.250  -0.3969   0.07988   0.07836  -0.0209   1.0000   0.0106
  -7.000  -0.3889   0.07732   0.07581  -0.0224   1.0000   0.0109
  -6.750  -0.3801   0.07486   0.07336  -0.0239   1.0000   0.0113
  -6.500  -0.3717   0.07170   0.07021  -0.0260   1.0000   0.0115
  -6.250  -0.3563   0.06846   0.06696  -0.0292   0.9994   0.0128
  -6.000  -0.3114   0.06235   0.06077  -0.0416   0.9938   0.0140
  -5.750  -0.2792   0.05717   0.05553  -0.0486   0.9868   0.0141
  -5.500  -0.2436   0.05128   0.04955  -0.0561   0.9796   0.0141
  -5.000  -0.1703   0.03766   0.03558  -0.0708   0.9576   0.0134
  -4.750  -0.1349   0.02944   0.02697  -0.0759   0.9354   0.0148
  -4.500  -0.1033   0.03473   0.03238  -0.0749   0.9145   0.0194
  -4.250  -0.0855   0.02818   0.02546  -0.0762   0.8883   0.0170
  -4.000  -0.0616   0.02288   0.01971  -0.0761   0.8701   0.0176
  -3.750  -0.0400   0.01616   0.01220  -0.0748   0.8556   0.0206
  -3.500  -0.0138   0.01782   0.01402  -0.0750   0.8425   0.0217
  -3.250   0.0126   0.01923   0.01551  -0.0750   0.8301   0.0253
  -3.000   0.0364   0.01558   0.01137  -0.0740   0.8183   0.0246
  -2.750   0.0615   0.01387   0.00933  -0.0732   0.8048   0.0256
  -2.250   0.1121   0.01210   0.00713  -0.0723   0.7767   0.0306
  -2.000   0.1382   0.01162   0.00657  -0.0720   0.7634   0.0321
  -1.750   0.1644   0.01016   0.00478  -0.0712   0.7501   0.0302
  -1.500   0.1907   0.00977   0.00431  -0.0708   0.7360   0.0316
  -1.250   0.2170   0.00913   0.00353  -0.0703   0.7222   0.0319
  -1.000   0.2434   0.00873   0.00305  -0.0700   0.7096   0.0329
  -0.750   0.2699   0.00839   0.00264  -0.0696   0.6982   0.0335
  -0.500   0.2962   0.00808   0.00226  -0.0692   0.6880   0.0336
  -0.250   0.3227   0.00780   0.00194  -0.0688   0.6786   0.0336
   0.000   0.3492   0.00757   0.00166  -0.0684   0.6701   0.0335
   0.250   0.3757   0.00742   0.00147  -0.0681   0.6623   0.0342
   0.500   0.4025   0.00726   0.00128  -0.0678   0.6558   0.0342
   0.750   0.4293   0.00713   0.00112  -0.0675   0.6492   0.0344
   1.000   0.4562   0.00704   0.00100  -0.0672   0.6430   0.0351
   1.250   0.4832   0.00697   0.00092  -0.0669   0.6365   0.0370
   1.500   0.5101   0.00696   0.00089  -0.0667   0.6306   0.0385
   1.750   0.5370   0.00694   0.00084  -0.0664   0.6201   0.0412
   2.000   0.5639   0.00694   0.00084  -0.0661   0.6091   0.0464
   2.250   0.5891   0.00658   0.00095  -0.0657   0.5992   0.2678
   2.500   0.6414   0.00508   0.00110  -0.0720   0.5803   1.0000
   2.750   0.6671   0.00520   0.00114  -0.0714   0.5588   1.0000
   3.000   0.6926   0.00533   0.00121  -0.0709   0.5326   1.0000
   3.250   0.7172   0.00555   0.00128  -0.0702   0.4907   1.0000
   3.500   0.7401   0.00597   0.00144  -0.0693   0.4298   1.0000
   3.750   0.7626   0.00646   0.00167  -0.0684   0.3696   1.0000
   4.000   0.7850   0.00698   0.00192  -0.0675   0.3066   1.0000
   4.250   0.8023   0.00812   0.00240  -0.0659   0.1614   1.0000
   4.500   0.8222   0.00899   0.00286  -0.0647   0.0753   1.0000
   4.750   0.8462   0.00936   0.00313  -0.0640   0.0571   1.0000
   5.000   0.8710   0.00961   0.00339  -0.0635   0.0493   1.0000
   5.250   0.8952   0.00994   0.00369  -0.0628   0.0401   1.0000
   5.500   0.9199   0.01021   0.00392  -0.0623   0.0323   1.0000
   5.750   0.9433   0.01064   0.00430  -0.0615   0.0211   1.0000
   6.000   0.9673   0.01100   0.00468  -0.0608   0.0177   1.0000
   6.250   0.9896   0.01160   0.00531  -0.0598   0.0143   1.0000
   6.500   1.0128   0.01204   0.00582  -0.0590   0.0131   1.0000
   6.750   1.0362   0.01244   0.00626  -0.0582   0.0120   1.0000
   7.000   1.0588   0.01293   0.00679  -0.0574   0.0110   1.0000
   7.250   1.0801   0.01359   0.00750  -0.0563   0.0101   1.0000
   7.500   1.0952   0.01503   0.00911  -0.0541   0.0092   1.0000
   7.750   1.1157   0.01578   0.00996  -0.0530   0.0089   1.0000
   8.000   1.1367   0.01645   0.01070  -0.0519   0.0086   1.0000
   8.250   1.1574   0.01715   0.01148  -0.0508   0.0081   1.0000
   8.500   1.1778   0.01788   0.01228  -0.0497   0.0075   1.0000
   8.750   1.1985   0.01852   0.01298  -0.0487   0.0070   1.0000
   9.000   1.2181   0.01929   0.01380  -0.0476   0.0067   1.0000
   9.250   1.2356   0.02037   0.01500  -0.0462   0.0064   1.0000
   9.500   1.2495   0.02214   0.01693  -0.0442   0.0062   1.0000
   9.750   1.2592   0.02496   0.02002  -0.0419   0.0059   1.0000
  10.000   1.2659   0.02830   0.02371  -0.0393   0.0057   1.0000
  10.250   1.2796   0.02967   0.02527  -0.0375   0.0057   1.0000
  10.500   1.2907   0.03128   0.02708  -0.0356   0.0055   1.0000
  10.750   1.2987   0.03313   0.02913  -0.0333   0.0054   1.0000
  11.000   1.3005   0.03548   0.03173  -0.0304   0.0053   1.0000
  11.250   1.2919   0.03814   0.03463  -0.0262   0.0052   1.0000
  11.500   1.2837   0.04061   0.03732  -0.0227   0.0050   1.0000
  11.750   1.2664   0.04423   0.04120  -0.0195   0.0050   1.0000
  12.000   1.2458   0.04855   0.04577  -0.0175   0.0049   1.0000
  12.250   1.2267   0.05310   0.05053  -0.0169   0.0049   1.0000
  12.500   1.1979   0.05959   0.05725  -0.0177   0.0049   1.0000
  12.750   1.1737   0.06618   0.06403  -0.0201   0.0050   1.0000
  13.000   1.1479   0.07385   0.07187  -0.0239   0.0050   1.0000
  13.250   1.1257   0.08184   0.08000  -0.0287   0.0051   1.0000
  13.500   1.0990   0.09231   0.09061  -0.0357   0.0052   1.0000
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