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GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il)
Reynolds number: 50,000
Max Cl/Cd: 37.76 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe325-il-50000-n5.txt
Download as CSV file: xf-goe325-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3266   0.09685   0.09054  -0.0239   1.0000   0.0894
  -7.000  -0.3269   0.09446   0.08824  -0.0245   1.0000   0.0922
  -6.750  -0.3293   0.09265   0.08652  -0.0271   1.0000   0.0955
  -6.500  -0.3293   0.09133   0.08523  -0.0331   1.0000   0.0970
  -6.250  -0.3245   0.08655   0.08057  -0.0285   1.0000   0.0997
  -6.000  -0.3197   0.08363   0.07770  -0.0269   1.0000   0.1048
  -5.750  -0.3124   0.08187   0.07589  -0.0338   1.0000   0.1113
  -5.500  -0.3074   0.07793   0.07204  -0.0323   1.0000   0.1136
  -5.250  -0.3012   0.07480   0.06896  -0.0305   1.0000   0.1173
  -5.000  -0.2814   0.07273   0.06668  -0.0389   1.0000   0.1264
  -4.500  -0.2647   0.06596   0.05999  -0.0362   1.0000   0.1387
  -4.250  -0.2549   0.06288   0.05696  -0.0357   1.0000   0.1481
  -4.000  -0.2410   0.06011   0.05415  -0.0367   1.0000   0.1627
  -3.750  -0.2245   0.05729   0.05129  -0.0381   0.9997   0.1772
  -3.500  -0.1393   0.04853   0.04136  -0.0536   0.9930   0.0809
  -3.250  -0.0899   0.04464   0.03692  -0.0600   0.9849   0.0817
  -3.000  -0.0466   0.04099   0.03297  -0.0647   0.9766   0.0793
  -2.750  -0.0011   0.03782   0.02935  -0.0693   0.9671   0.0776
  -2.500   0.0451   0.03529   0.02626  -0.0735   0.9565   0.0797
  -2.250   0.0914   0.03316   0.02347  -0.0773   0.9451   0.0817
  -2.000   0.1365   0.03108   0.02096  -0.0806   0.9326   0.0814
  -1.750   0.1806   0.02930   0.01877  -0.0834   0.9184   0.0816
  -1.500   0.2222   0.02781   0.01688  -0.0855   0.9020   0.0823
  -1.250   0.2601   0.02638   0.01525  -0.0869   0.8841   0.0837
  -1.000   0.2966   0.02520   0.01397  -0.0880   0.8659   0.0881
  -0.750   0.3295   0.02440   0.01292  -0.0881   0.8439   0.0954
  -0.500   0.3649   0.02342   0.01178  -0.0885   0.8237   0.1000
  -0.250   0.3973   0.02263   0.01086  -0.0886   0.8002   0.1050
   0.000   0.4313   0.02191   0.00991  -0.0887   0.7779   0.1123
   0.250   0.4630   0.02128   0.00917  -0.0887   0.7535   0.1248
   0.500   0.4940   0.02061   0.00855  -0.0887   0.7296   0.1606
   0.750   0.5197   0.01825   0.00805  -0.0874   0.7068   1.0000
   1.000   0.5475   0.01844   0.00778  -0.0867   0.6826   1.0000
   1.250   0.5748   0.01867   0.00763  -0.0860   0.6604   1.0000
   1.500   0.6010   0.01896   0.00762  -0.0854   0.6381   1.0000
   1.750   0.6272   0.01927   0.00764  -0.0847   0.6181   1.0000
   2.000   0.6533   0.01960   0.00771  -0.0841   0.6000   1.0000
   2.250   0.6796   0.01998   0.00789  -0.0837   0.5823   1.0000
   2.500   0.7060   0.02038   0.00809  -0.0833   0.5659   1.0000
   2.750   0.7324   0.02081   0.00836  -0.0829   0.5508   1.0000
   3.000   0.7589   0.02127   0.00869  -0.0826   0.5367   1.0000
   3.250   0.7855   0.02175   0.00905  -0.0823   0.5234   1.0000
   3.500   0.8123   0.02225   0.00944  -0.0821   0.5111   1.0000
   3.750   0.8384   0.02277   0.00995  -0.0819   0.4989   1.0000
   4.000   0.8643   0.02332   0.01050  -0.0816   0.4873   1.0000
   4.250   0.8903   0.02388   0.01105  -0.0814   0.4769   1.0000
   4.500   0.9167   0.02442   0.01160  -0.0811   0.4677   1.0000
   4.750   0.9417   0.02504   0.01232  -0.0809   0.4576   1.0000
   5.000   0.9674   0.02564   0.01295  -0.0806   0.4492   1.0000
   5.500   1.0175   0.02695   0.01449  -0.0800   0.4330   1.0000
   5.750   1.0426   0.02762   0.01526  -0.0797   0.4258   1.0000
   6.000   1.0670   0.02836   0.01615  -0.0794   0.4188   1.0000
   6.250   1.0913   0.02909   0.01707  -0.0790   0.4119   1.0000
   6.500   1.1159   0.02986   0.01798  -0.0786   0.4060   1.0000
   6.750   1.1388   0.03078   0.01915  -0.0782   0.3996   1.0000
   7.000   1.1641   0.03151   0.02000  -0.0779   0.3946   1.0000
   7.250   1.1850   0.03261   0.02146  -0.0773   0.3881   1.0000
   7.500   1.2081   0.03353   0.02260  -0.0768   0.3826   1.0000
   7.750   1.2321   0.03445   0.02373  -0.0764   0.3781   1.0000
   8.000   1.2503   0.03583   0.02551  -0.0756   0.3719   1.0000
   8.250   1.2734   0.03675   0.02668  -0.0750   0.3668   1.0000
   8.500   1.2908   0.03764   0.02793  -0.0737   0.3569   1.0000
   8.750   1.3106   0.03715   0.02753  -0.0718   0.3392   1.0000
   9.000   1.3289   0.03681   0.02729  -0.0698   0.3218   1.0000
   9.250   1.3436   0.03694   0.02761  -0.0677   0.3055   1.0000
   9.500   1.3473   0.03719   0.02813  -0.0644   0.2801   1.0000
   9.750   1.3454   0.03764   0.02869  -0.0608   0.2453   1.0000
  10.000   1.3425   0.03898   0.03020  -0.0576   0.1999   1.0000
  10.500   1.3063   0.04515   0.03541  -0.0509   0.0913   1.0000
  10.750   1.2879   0.04955   0.03974  -0.0494   0.0765   1.0000
  11.000   1.2708   0.05439   0.04464  -0.0492   0.0686   1.0000
  11.250   1.2537   0.05979   0.05017  -0.0500   0.0638   1.0000
  11.500   1.2367   0.06567   0.05615  -0.0516   0.0609   1.0000
  11.750   1.2223   0.07148   0.06221  -0.0533   0.0578   1.0000
  12.000   1.2080   0.07734   0.06821  -0.0551   0.0553   1.0000
  12.250   1.1945   0.08308   0.07407  -0.0567   0.0532   1.0000
  12.500   1.1817   0.08865   0.07972  -0.0583   0.0512   1.0000
  12.750   1.1699   0.09401   0.08510  -0.0596   0.0494   1.0000
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