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GOE 445 AIRFOIL (goe445-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 445 AIRFOIL (goe445-il)
Reynolds number: 100,000
Max Cl/Cd: 24.2 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe445-il-100000.txt
Download as CSV file: xf-goe445-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 445 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.6648   0.09061   0.08596  -0.0086   1.0000   0.0969
  -8.250  -0.6797   0.08658   0.08189  -0.0126   1.0000   0.0973
  -8.000  -0.6975   0.08336   0.07845  -0.0158   1.0000   0.0978
  -7.750  -0.6732   0.07811   0.07344  -0.0126   1.0000   0.1097
  -7.500  -0.6657   0.07369   0.06907  -0.0113   1.0000   0.1156
  -7.250  -0.6811   0.07068   0.06572  -0.0153   1.0000   0.1238
  -7.000  -0.6620   0.06600   0.06128  -0.0125   1.0000   0.1322
  -6.750  -0.6580   0.06221   0.05743  -0.0125   1.0000   0.1437
  -6.500  -0.6516   0.05884   0.05390  -0.0121   1.0000   0.1581
  -5.500  -0.6143   0.04701   0.04197  -0.0062   1.0000   0.2504
  -5.250  -0.5745   0.03482   0.02678  -0.0084   1.0000   0.0722
  -5.000  -0.5491   0.03104   0.02253  -0.0064   1.0000   0.0572
  -4.750  -0.5275   0.02748   0.01868  -0.0049   1.0000   0.0529
  -4.500  -0.5031   0.02484   0.01552  -0.0031   1.0000   0.0493
  -4.250  -0.4795   0.02310   0.01359  -0.0019   1.0000   0.0540
  -4.000  -0.4542   0.02133   0.01155  -0.0005   1.0000   0.0563
  -3.750  -0.4291   0.01959   0.00968   0.0009   1.0000   0.0575
  -3.500  -0.4076   0.01775   0.00791   0.0025   1.0000   0.0608
  -3.250  -0.3876   0.01651   0.00661   0.0044   1.0000   0.0684
  -3.000  -0.3686   0.01524   0.00541   0.0062   1.0000   0.0930
  -2.750  -0.2776   0.01278   0.00635   0.0015   1.0000   0.9580
  -2.500  -0.1997   0.01270   0.00573  -0.0087   1.0000   0.9836
  -2.250  -0.1380   0.01227   0.00489  -0.0166   1.0000   1.0000
  -2.000  -0.1244   0.01190   0.00441  -0.0150   1.0000   1.0000
  -1.750  -0.1100   0.01160   0.00402  -0.0134   1.0000   1.0000
  -1.500  -0.0951   0.01138   0.00371  -0.0116   1.0000   1.0000
  -1.250  -0.0799   0.01120   0.00346  -0.0097   1.0000   1.0000
  -1.000  -0.0645   0.01106   0.00327  -0.0077   1.0000   1.0000
  -0.750  -0.0488   0.01096   0.00311  -0.0058   1.0000   1.0000
  -0.500  -0.0328   0.01089   0.00300  -0.0038   1.0000   1.0000
  -0.250  -0.0164   0.01085   0.00294  -0.0019   1.0000   1.0000
   0.000   0.0000   0.01083   0.00292   0.0000   1.0000   1.0000
   0.250   0.0164   0.01085   0.00294   0.0019   1.0000   1.0000
   0.500   0.0328   0.01089   0.00300   0.0038   1.0000   1.0000
   0.750   0.0488   0.01096   0.00310   0.0058   1.0000   1.0000
   1.000   0.0645   0.01106   0.00327   0.0077   1.0000   1.0000
   1.250   0.0800   0.01120   0.00346   0.0097   1.0000   1.0000
   1.500   0.0952   0.01137   0.00371   0.0115   1.0000   1.0000
   1.750   0.1101   0.01160   0.00402   0.0133   1.0000   1.0000
   2.000   0.1245   0.01189   0.00441   0.0150   1.0000   1.0000
   2.250   0.1381   0.01226   0.00489   0.0166   1.0000   1.0000
   2.500   0.1996   0.01269   0.00573   0.0087   0.9837   1.0000
   2.750   0.2763   0.01279   0.00634  -0.0012   0.9584   1.0000
   3.000   0.3685   0.01523   0.00540  -0.0062   0.0937   1.0000
   3.250   0.3875   0.01651   0.00661  -0.0044   0.0687   1.0000
   3.500   0.4075   0.01775   0.00792  -0.0025   0.0608   1.0000
   3.750   0.4290   0.01959   0.00968  -0.0009   0.0575   1.0000
   4.000   0.4541   0.02132   0.01154   0.0005   0.0564   1.0000
   4.250   0.4795   0.02314   0.01362   0.0019   0.0544   1.0000
   4.500   0.5032   0.02484   0.01556   0.0032   0.0500   1.0000
   4.750   0.5274   0.02747   0.01867   0.0049   0.0529   1.0000
   5.000   0.5491   0.03102   0.02252   0.0064   0.0572   1.0000
   5.250   0.5745   0.03478   0.02675   0.0084   0.0723   1.0000
   6.500   0.6518   0.05883   0.05389   0.0121   0.1582   1.0000
   6.750   0.6581   0.06223   0.05744   0.0126   0.1433   1.0000
   7.000   0.6620   0.06602   0.06130   0.0125   0.1320   1.0000
   7.250   0.6806   0.07065   0.06570   0.0152   0.1237   1.0000
   8.250   0.6023   0.07863   0.07429   0.0133   0.1105   1.0000
   8.500   0.5804   0.08336   0.07898   0.0091   0.1103   1.0000
   8.750   0.5587   0.08808   0.08362   0.0039   0.1093   1.0000
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