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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 500,000
Max Cl/Cd: 100.02 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe325-il-500000.txt
Download as CSV file: xf-goe325-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3385   0.08795   0.08590  -0.0213   1.0000   0.0199
  -7.250  -0.3526   0.08670   0.08470  -0.0182   1.0000   0.0203
  -7.000  -0.3601   0.08464   0.08268  -0.0179   1.0000   0.0211
  -6.750  -0.3203   0.07769   0.07567  -0.0353   0.9955   0.0217
  -6.500  -0.2870   0.07168   0.06959  -0.0452   0.9920   0.0218
  -6.250  -0.2612   0.06386   0.06172  -0.0539   0.9879   0.0222
  -6.000  -0.2337   0.06039   0.05822  -0.0575   0.9854   0.0227
  -5.750  -0.1973   0.05660   0.05438  -0.0638   0.9834   0.0236
  -5.500  -0.1636   0.05259   0.05029  -0.0698   0.9782   0.0253
  -5.250  -0.1076   0.04675   0.04415  -0.0805   0.9736   0.0282
  -5.000  -0.0785   0.03860   0.03575  -0.0867   0.9692   0.0290
  -4.750  -0.0565   0.03659   0.03370  -0.0875   0.9620   0.0298
  -4.500  -0.0298   0.03464   0.03167  -0.0888   0.9565   0.0309
  -4.250  -0.0058   0.03258   0.02949  -0.0891   0.9473   0.0337
  -4.000   0.0292   0.03087   0.02736  -0.0892   0.9398   0.0369
  -3.750   0.0488   0.02525   0.02149  -0.0903   0.9305   0.0388
  -3.500   0.0719   0.02400   0.02017  -0.0899   0.9196   0.0401
  -3.250   0.0964   0.02279   0.01884  -0.0895   0.9075   0.0428
  -3.000   0.1256   0.02074   0.01624  -0.0889   0.8941   0.0490
  -2.750   0.1496   0.01896   0.01441  -0.0887   0.8765   0.0507
  -2.500   0.1747   0.01798   0.01329  -0.0882   0.8524   0.0528
  -2.250   0.2006   0.01719   0.01223  -0.0874   0.8177   0.0568
  -2.000   0.2268   0.01607   0.01066  -0.0868   0.7758   0.0635
  -1.750   0.2562   0.01296   0.00686  -0.0857   0.7394   0.0439
  -1.500   0.2830   0.01204   0.00558  -0.0852   0.6997   0.0427
  -1.250   0.3098   0.01154   0.00480  -0.0847   0.6583   0.0429
  -1.000   0.3364   0.01122   0.00424  -0.0844   0.6159   0.0437
  -0.750   0.3633   0.01086   0.00367  -0.0841   0.5840   0.0439
  -0.500   0.3904   0.01062   0.00325  -0.0838   0.5624   0.0446
  -0.250   0.4178   0.01043   0.00295  -0.0837   0.5456   0.0456
   0.000   0.4454   0.01030   0.00272  -0.0836   0.5315   0.0466
   0.250   0.4731   0.01020   0.00254  -0.0835   0.5188   0.0474
   0.500   0.5011   0.01002   0.00231  -0.0835   0.5074   0.0497
   0.750   0.5290   0.00994   0.00219  -0.0835   0.4965   0.0542
   1.000   0.5569   0.00993   0.00213  -0.0835   0.4854   0.0596
   1.250   0.5849   0.00977   0.00209  -0.0835   0.4735   0.1155
   1.500   0.6064   0.00779   0.00221  -0.0826   0.4619   1.0000
   1.750   0.6342   0.00791   0.00222  -0.0825   0.4489   1.0000
   2.000   0.6619   0.00805   0.00226  -0.0825   0.4354   1.0000
   2.250   0.6894   0.00820   0.00231  -0.0824   0.4213   1.0000
   2.500   0.7169   0.00836   0.00237  -0.0823   0.4073   1.0000
   2.750   0.7442   0.00854   0.00245  -0.0822   0.3939   1.0000
   3.000   0.7714   0.00873   0.00256  -0.0822   0.3818   1.0000
   3.500   0.8258   0.00912   0.00282  -0.0820   0.3618   1.0000
   3.750   0.8528   0.00934   0.00297  -0.0819   0.3540   1.0000
   4.000   0.8800   0.00953   0.00314  -0.0818   0.3468   1.0000
   4.250   0.9067   0.00977   0.00333  -0.0817   0.3404   1.0000
   4.500   0.9340   0.00994   0.00351  -0.0816   0.3344   1.0000
   4.750   0.9606   0.01020   0.00373  -0.0815   0.3286   1.0000
   5.000   0.9876   0.01039   0.00393  -0.0814   0.3230   1.0000
   5.250   1.0142   0.01060   0.00412  -0.0813   0.3153   1.0000
   5.500   1.0410   0.01078   0.00430  -0.0812   0.3068   1.0000
   5.750   1.0673   0.01102   0.00453  -0.0810   0.2996   1.0000
   6.000   1.0942   0.01118   0.00473  -0.0809   0.2926   1.0000
   6.250   1.1203   0.01143   0.00494  -0.0807   0.2843   1.0000
   6.500   1.1472   0.01157   0.00514  -0.0807   0.2759   1.0000
   6.750   1.1733   0.01178   0.00535  -0.0805   0.2653   1.0000
   7.000   1.1993   0.01200   0.00556  -0.0803   0.2528   1.0000
   7.250   1.2252   0.01225   0.00579  -0.0801   0.2361   1.0000
   7.500   1.2488   0.01277   0.00612  -0.0797   0.1988   1.0000
   7.750   1.2557   0.01546   0.00786  -0.0773   0.0520   1.0000
   8.000   1.2738   0.01665   0.00887  -0.0760   0.0218   1.0000
   8.250   1.2953   0.01737   0.00964  -0.0751   0.0192   1.0000
   8.500   1.3154   0.01822   0.01062  -0.0740   0.0173   1.0000
   8.750   1.3355   0.01901   0.01151  -0.0729   0.0166   1.0000
   9.000   1.3546   0.01983   0.01245  -0.0717   0.0158   1.0000
   9.250   1.3720   0.02076   0.01348  -0.0703   0.0148   1.0000
   9.500   1.3871   0.02182   0.01463  -0.0686   0.0140   1.0000
   9.750   1.3982   0.02311   0.01602  -0.0665   0.0134   1.0000
  10.000   1.4033   0.02473   0.01776  -0.0635   0.0129   1.0000
  10.250   1.3994   0.02657   0.01973  -0.0592   0.0126   1.0000
  10.500   1.3965   0.02846   0.02175  -0.0555   0.0124   1.0000
  10.750   1.4026   0.02982   0.02322  -0.0532   0.0123   1.0000
  11.000   1.4068   0.03144   0.02494  -0.0509   0.0121   1.0000
  11.250   1.4093   0.03330   0.02691  -0.0488   0.0119   1.0000
  11.500   1.4110   0.03538   0.02910  -0.0470   0.0117   1.0000
  11.750   1.4121   0.03766   0.03150  -0.0455   0.0115   1.0000
  12.000   1.4136   0.04006   0.03400  -0.0442   0.0113   1.0000
  12.250   1.4152   0.04257   0.03662  -0.0433   0.0111   1.0000
  12.500   1.4166   0.04520   0.03935  -0.0426   0.0108   1.0000
  12.750   1.4180   0.04793   0.04219  -0.0422   0.0105   1.0000
  13.000   1.4188   0.05078   0.04513  -0.0418   0.0103   1.0000
  13.250   1.4195   0.05367   0.04812  -0.0414   0.0101   1.0000
  13.500   1.4197   0.05670   0.05124  -0.0411   0.0099   1.0000
  13.750   1.4195   0.05979   0.05444  -0.0408   0.0098   1.0000
  14.000   1.4190   0.06298   0.05773  -0.0406   0.0097   1.0000
  14.250   1.4180   0.06628   0.06115  -0.0404   0.0096   1.0000
  14.500   1.4161   0.06973   0.06471  -0.0404   0.0096   1.0000
  14.750   1.4133   0.07340   0.06852  -0.0405   0.0095   1.0000
  15.000   1.4092   0.07735   0.07261  -0.0409   0.0095   1.0000
  15.250   1.4036   0.08161   0.07701  -0.0416   0.0094   1.0000
  15.500   1.3964   0.08623   0.08178  -0.0427   0.0094   1.0000
  15.750   1.3869   0.09140   0.08714  -0.0443   0.0095   1.0000
  16.000   1.3749   0.09716   0.09312  -0.0464   0.0096   1.0000
  16.250   1.3445   0.10682   0.10316  -0.0513   0.0101   1.0000
  16.500   1.3176   0.11625   0.11290  -0.0559   0.0106   1.0000
  16.750   1.2975   0.12451   0.12137  -0.0601   0.0109   1.0000
  17.000   1.2786   0.13281   0.12985  -0.0647   0.0113   1.0000
  17.250   1.2603   0.14139   0.13859  -0.0698   0.0115   1.0000
  17.500   1.2417   0.15029   0.14763  -0.0752   0.0119   1.0000
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