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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 200,000
Max Cl/Cd: 72.91 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe325-il-200000.txt
Download as CSV file: xf-goe325-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 325 (PFALZ 54) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3348   0.09190   0.08864  -0.0238   1.0000   0.0358
  -7.250  -0.3424   0.09045   0.08727  -0.0256   1.0000   0.0363
  -7.000  -0.3438   0.08841   0.08526  -0.0289   1.0000   0.0366
  -6.750  -0.3404   0.08578   0.08264  -0.0318   1.0000   0.0368
  -6.500  -0.3345   0.08282   0.07966  -0.0339   1.0000   0.0369
  -6.250  -0.3377   0.07749   0.07439  -0.0325   1.0000   0.0375
  -6.000  -0.3381   0.07468   0.07164  -0.0281   1.0000   0.0383
  -5.750  -0.3347   0.07234   0.06933  -0.0262   1.0000   0.0394
  -5.500  -0.3286   0.06977   0.06676  -0.0262   1.0000   0.0407
  -5.250  -0.3199   0.06692   0.06390  -0.0274   1.0000   0.0422
  -5.000  -0.2620   0.06207   0.05874  -0.0419   0.9962   0.0475
  -4.750  -0.2230   0.05484   0.05132  -0.0503   0.9916   0.0488
  -4.500  -0.1936   0.05114   0.04766  -0.0531   0.9866   0.0508
  -4.250  -0.1471   0.04746   0.04382  -0.0598   0.9811   0.0570
  -4.000  -0.0931   0.04188   0.03781  -0.0686   0.9745   0.0624
  -3.750  -0.0521   0.03874   0.03465  -0.0732   0.9707   0.0662
  -3.500  -0.0061   0.03534   0.03072  -0.0781   0.9631   0.0761
  -3.250   0.0331   0.03247   0.02789  -0.0820   0.9588   0.0806
  -3.000   0.0793   0.02966   0.02465  -0.0863   0.9533   0.0912
  -2.750   0.1306   0.01122   0.00632  -0.0875   0.9222   0.1058
  -2.500   0.1604   0.00976   0.00466  -0.0882   0.9106   0.1198
  -2.250   0.1861   0.00844   0.00333  -0.0881   0.8966   0.1266
  -2.000   0.2118   0.00740   0.00213  -0.0878   0.8785   0.1414
  -1.750   0.2589   0.01919   0.01273  -0.0925   0.9011   0.0915
  -1.500   0.2906   0.01773   0.01081  -0.0913   0.8837   0.0739
  -1.250   0.3179   0.01593   0.00884  -0.0905   0.8604   0.0709
  -1.000   0.3458   0.01480   0.00749  -0.0896   0.8319   0.0696
  -0.750   0.3730   0.01396   0.00640  -0.0885   0.7962   0.0695
  -0.500   0.3991   0.01342   0.00557  -0.0874   0.7555   0.0703
  -0.250   0.4249   0.01320   0.00508  -0.0864   0.7159   0.0731
   0.000   0.4505   0.01288   0.00455  -0.0856   0.6808   0.0757
   0.250   0.4763   0.01256   0.00411  -0.0850   0.6493   0.0790
   0.500   0.5025   0.01243   0.00384  -0.0845   0.6219   0.0844
   0.750   0.5291   0.01228   0.00358  -0.0841   0.5986   0.0945
   1.000   0.5518   0.01071   0.00347  -0.0837   0.5797   0.6257
   1.250   0.5774   0.01022   0.00332  -0.0823   0.5616   1.0000
   1.500   0.6040   0.01050   0.00338  -0.0820   0.5440   1.0000
   1.750   0.6306   0.01079   0.00347  -0.0817   0.5277   1.0000
   2.000   0.6573   0.01109   0.00360  -0.0814   0.5124   1.0000
   2.250   0.6840   0.01137   0.00375  -0.0812   0.4978   1.0000
   2.500   0.7107   0.01165   0.00390  -0.0809   0.4836   1.0000
   2.750   0.7373   0.01192   0.00406  -0.0807   0.4703   1.0000
   3.000   0.7640   0.01219   0.00422  -0.0805   0.4581   1.0000
   3.250   0.7908   0.01242   0.00440  -0.0803   0.4459   1.0000
   3.500   0.8176   0.01267   0.00461  -0.0802   0.4349   1.0000
   3.750   0.8443   0.01295   0.00481  -0.0800   0.4254   1.0000
   4.000   0.8710   0.01321   0.00504  -0.0798   0.4160   1.0000
   4.250   0.8977   0.01348   0.00530  -0.0796   0.4068   1.0000
   4.750   0.9511   0.01409   0.00586  -0.0793   0.3917   1.0000
   5.000   0.9777   0.01447   0.00618  -0.0792   0.3855   1.0000
   5.250   1.0043   0.01478   0.00657  -0.0790   0.3787   1.0000
   5.500   1.0309   0.01513   0.00690  -0.0789   0.3727   1.0000
   5.750   1.0574   0.01552   0.00735  -0.0787   0.3667   1.0000
   6.000   1.0839   0.01589   0.00777  -0.0786   0.3612   1.0000
   6.250   1.1102   0.01631   0.00817  -0.0784   0.3550   1.0000
   6.500   1.1350   0.01649   0.00841  -0.0780   0.3445   1.0000
   6.750   1.1596   0.01673   0.00873  -0.0775   0.3340   1.0000
   7.000   1.1845   0.01706   0.00905  -0.0771   0.3255   1.0000
   7.250   1.2084   0.01722   0.00928  -0.0766   0.3140   1.0000
   7.500   1.2324   0.01742   0.00962  -0.0760   0.3034   1.0000
   7.750   1.2562   0.01766   0.00997  -0.0754   0.2931   1.0000
   8.000   1.2788   0.01774   0.01016  -0.0746   0.2765   1.0000
   8.250   1.3007   0.01784   0.01031  -0.0737   0.2521   1.0000
   8.500   1.3205   0.01829   0.01064  -0.0726   0.1967   1.0000
   8.750   1.3158   0.02182   0.01305  -0.0690   0.0519   1.0000
   9.000   1.3282   0.02338   0.01463  -0.0669   0.0373   1.0000
   9.250   1.3424   0.02459   0.01593  -0.0651   0.0322   1.0000
   9.500   1.3514   0.02613   0.01761  -0.0627   0.0297   1.0000
   9.750   1.3609   0.02746   0.01912  -0.0603   0.0285   1.0000
  10.000   1.3653   0.02891   0.02072  -0.0573   0.0275   1.0000
  10.250   1.3667   0.03052   0.02246  -0.0541   0.0267   1.0000
  10.500   1.3666   0.03236   0.02442  -0.0511   0.0260   1.0000
  10.750   1.3656   0.03441   0.02658  -0.0485   0.0254   1.0000
  11.000   1.3639   0.03670   0.02898  -0.0463   0.0248   1.0000
  11.250   1.3607   0.03931   0.03168  -0.0445   0.0241   1.0000
  11.500   1.3559   0.04230   0.03475  -0.0427   0.0234   1.0000
  11.750   1.3536   0.04531   0.03781  -0.0409   0.0228   1.0000
  12.000   1.3583   0.04764   0.04026  -0.0397   0.0225   1.0000
  12.250   1.3641   0.04999   0.04273  -0.0384   0.0223   1.0000
  12.500   1.3708   0.05237   0.04524  -0.0370   0.0221   1.0000
  12.750   1.3783   0.05483   0.04784  -0.0356   0.0220   1.0000
  13.000   1.3853   0.05751   0.05069  -0.0343   0.0219   1.0000
  13.250   1.3907   0.06052   0.05391  -0.0330   0.0219   1.0000
  13.500   1.3936   0.06392   0.05752  -0.0320   0.0220   1.0000
  13.750   1.3937   0.06778   0.06160  -0.0313   0.0222   1.0000
  14.000   1.3903   0.07207   0.06611  -0.0308   0.0224   1.0000
  14.250   1.3831   0.07670   0.07096  -0.0309   0.0225   1.0000
  14.500   1.3732   0.08168   0.07617  -0.0314   0.0226   1.0000
  14.750   1.3627   0.08715   0.08184  -0.0321   0.0228   1.0000
  15.000   1.3515   0.09229   0.08719  -0.0335   0.0229   1.0000
  15.250   1.3370   0.09764   0.09273  -0.0358   0.0229   1.0000
  15.500   1.3221   0.10321   0.09849  -0.0385   0.0230   1.0000
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