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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 500,000
Max Cl/Cd: 98.33 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe325-il-500000-n5.txt
Download as CSV file: xf-goe325-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3468   0.10055   0.09836  -0.0215   1.0000   0.0075
  -8.750  -0.3437   0.09674   0.09457  -0.0232   1.0000   0.0077
  -8.500  -0.3421   0.09291   0.09076  -0.0248   1.0000   0.0078
  -8.000  -0.3345   0.08563   0.08354  -0.0292   0.9951   0.0085
  -7.750  -0.3193   0.08271   0.08061  -0.0329   0.9891   0.0088
  -7.500  -0.3029   0.07873   0.07663  -0.0382   0.9830   0.0090
  -7.250  -0.2846   0.07390   0.07179  -0.0451   0.9769   0.0093
  -7.000  -0.2669   0.06894   0.06680  -0.0518   0.9699   0.0096
  -6.750  -0.2464   0.06312   0.06094  -0.0596   0.9631   0.0101
  -6.500  -0.2245   0.05277   0.05045  -0.0719   0.9540   0.0113
  -6.250  -0.2023   0.05058   0.04821  -0.0742   0.9459   0.0117
  -6.000  -0.1794   0.04791   0.04544  -0.0767   0.9371   0.0123
  -5.750  -0.1550   0.04353   0.04092  -0.0805   0.9260   0.0131
  -5.500  -0.1244   0.03138   0.02821  -0.0886   0.9172   0.0157
  -5.250  -0.1004   0.03082   0.02759  -0.0884   0.9043   0.0163
  -5.000  -0.0755   0.02916   0.02577  -0.0887   0.8889   0.0172
  -4.750  -0.0478   0.01857   0.01409  -0.0910   0.8767   0.0216
  -4.500  -0.0223   0.01814   0.01354  -0.0907   0.8559   0.0223
  -4.250   0.0032   0.01770   0.01290  -0.0902   0.8272   0.0229
  -4.000   0.0286   0.01725   0.01220  -0.0898   0.7917   0.0238
  -3.750   0.0544   0.01668   0.01131  -0.0894   0.7537   0.0250
  -3.500   0.0809   0.01558   0.00981  -0.0892   0.7200   0.0260
  -3.250   0.1079   0.01466   0.00853  -0.0890   0.6880   0.0269
  -3.000   0.1349   0.01417   0.00775  -0.0888   0.6523   0.0280
  -2.750   0.1617   0.01371   0.00697  -0.0886   0.6084   0.0286
  -2.250   0.2160   0.01301   0.00575  -0.0884   0.5499   0.0293
  -2.000   0.2437   0.01270   0.00527  -0.0883   0.5351   0.0296
  -1.750   0.2714   0.01239   0.00482  -0.0883   0.5228   0.0297
  -1.500   0.2991   0.01190   0.00419  -0.0883   0.5117   0.0300
  -1.250   0.3268   0.01131   0.00349  -0.0883   0.5016   0.0310
  -1.000   0.3547   0.01100   0.00310  -0.0883   0.4930   0.0313
  -0.750   0.3826   0.01077   0.00279  -0.0883   0.4839   0.0317
  -0.500   0.4107   0.01056   0.00253  -0.0883   0.4746   0.0322
  -0.250   0.4387   0.01042   0.00233  -0.0883   0.4648   0.0330
   0.000   0.4667   0.01033   0.00218  -0.0883   0.4543   0.0342
   0.250   0.4948   0.01026   0.00208  -0.0884   0.4444   0.0357
   0.500   0.5228   0.01024   0.00200  -0.0884   0.4337   0.0372
   0.750   0.5506   0.01025   0.00195  -0.0884   0.4213   0.0387
   1.000   0.5784   0.01028   0.00191  -0.0884   0.4076   0.0403
   1.500   0.6337   0.01037   0.00193  -0.0884   0.3809   0.0528
   1.750   0.6614   0.01037   0.00200  -0.0884   0.3697   0.0987
   2.250   0.7099   0.00867   0.00228  -0.0874   0.3514   1.0000
   2.500   0.7374   0.00882   0.00235  -0.0874   0.3430   1.0000
   2.750   0.7647   0.00901   0.00246  -0.0873   0.3350   1.0000
   3.000   0.7922   0.00915   0.00256  -0.0873   0.3283   1.0000
   3.250   0.8194   0.00933   0.00268  -0.0872   0.3223   1.0000
   3.500   0.8468   0.00948   0.00281  -0.0872   0.3173   1.0000
   3.750   0.8742   0.00964   0.00294  -0.0871   0.3122   1.0000
   4.000   0.9012   0.00982   0.00310  -0.0871   0.3074   1.0000
   4.250   0.9284   0.00998   0.00326  -0.0870   0.3032   1.0000
   4.500   0.9556   0.01015   0.00342  -0.0869   0.2986   1.0000
   4.750   0.9825   0.01034   0.00360  -0.0869   0.2940   1.0000
   5.000   1.0093   0.01053   0.00380  -0.0868   0.2889   1.0000
   5.250   1.0361   0.01072   0.00398  -0.0867   0.2801   1.0000
   5.500   1.0627   0.01093   0.00417  -0.0866   0.2719   1.0000
   5.750   1.0891   0.01115   0.00438  -0.0864   0.2640   1.0000
   6.000   1.1156   0.01135   0.00460  -0.0863   0.2561   1.0000
   6.250   1.1416   0.01161   0.00483  -0.0861   0.2451   1.0000
   6.500   1.1672   0.01190   0.00508  -0.0859   0.2277   1.0000
   6.750   1.1913   0.01237   0.00541  -0.0856   0.1986   1.0000
   7.000   1.2026   0.01454   0.00675  -0.0837   0.0687   1.0000
   7.250   1.2212   0.01570   0.00767  -0.0826   0.0224   1.0000
   7.500   1.2440   0.01628   0.00826  -0.0819   0.0154   1.0000
   7.750   1.2667   0.01684   0.00888  -0.0812   0.0129   1.0000
   8.000   1.2886   0.01749   0.00963  -0.0804   0.0109   1.0000
   8.250   1.3111   0.01800   0.01022  -0.0797   0.0102   1.0000
   8.500   1.3327   0.01859   0.01090  -0.0789   0.0095   1.0000
   8.750   1.3534   0.01924   0.01162  -0.0780   0.0087   1.0000
   9.000   1.3726   0.02000   0.01245  -0.0769   0.0080   1.0000
   9.250   1.3890   0.02097   0.01353  -0.0754   0.0073   1.0000
   9.500   1.4069   0.02174   0.01440  -0.0742   0.0070   1.0000
   9.750   1.4229   0.02260   0.01537  -0.0726   0.0066   1.0000
  10.000   1.4370   0.02355   0.01641  -0.0709   0.0063   1.0000
  10.250   1.4489   0.02456   0.01751  -0.0688   0.0060   1.0000
  10.500   1.4566   0.02560   0.01865  -0.0661   0.0058   1.0000
  10.750   1.4630   0.02678   0.01991  -0.0634   0.0056   1.0000
  11.000   1.4679   0.02811   0.02134  -0.0609   0.0055   1.0000
  11.250   1.4697   0.02976   0.02308  -0.0583   0.0053   1.0000
  11.500   1.4654   0.03202   0.02547  -0.0556   0.0051   1.0000
  11.750   1.4672   0.03399   0.02757  -0.0539   0.0049   1.0000
  12.000   1.4681   0.03620   0.02992  -0.0525   0.0048   1.0000
  12.250   1.4686   0.03868   0.03253  -0.0516   0.0047   1.0000
  12.500   1.4665   0.04169   0.03567  -0.0511   0.0045   1.0000
  12.750   1.4627   0.04516   0.03928  -0.0511   0.0045   1.0000
  13.000   1.4579   0.04900   0.04326  -0.0515   0.0044   1.0000
  13.250   1.4523   0.05312   0.04751  -0.0523   0.0043   1.0000
  13.500   1.4467   0.05741   0.05193  -0.0532   0.0042   1.0000
  13.750   1.4400   0.06189   0.05653  -0.0543   0.0042   1.0000
  14.000   1.4330   0.06638   0.06114  -0.0553   0.0041   1.0000
  14.250   1.4252   0.07096   0.06584  -0.0563   0.0040   1.0000
  14.500   1.4179   0.07549   0.07048  -0.0574   0.0040   1.0000
  14.750   1.4104   0.08007   0.07517  -0.0585   0.0039   1.0000
  15.000   1.4033   0.08469   0.07989  -0.0596   0.0039   1.0000
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