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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 100,000
Max Cl/Cd: 56.11 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe330-il-100000.txt
Download as CSV file: xf-goe330-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 330 (PFALZ 59) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3418   0.10739   0.10324  -0.0190   1.0000   0.0671
  -7.250  -0.3596   0.10688   0.10282  -0.0166   1.0000   0.0677
  -7.000  -0.3750   0.10625   0.10227  -0.0162   1.0000   0.0684
  -6.750  -0.3864   0.10556   0.10164  -0.0186   1.0000   0.0689
  -6.500  -0.3594   0.10083   0.09686  -0.0325   0.9931   0.0698
  -6.250  -0.3489   0.09555   0.09163  -0.0268   0.9904   0.0711
  -6.000  -0.3261   0.09146   0.08750  -0.0288   0.9851   0.0738
  -5.750  -0.3008   0.08759   0.08359  -0.0354   0.9772   0.0784
  -5.500  -0.2559   0.08261   0.07839  -0.0545   0.9667   0.0828
  -5.250  -0.2424   0.07852   0.07438  -0.0522   0.9610   0.0846
  -5.000  -0.2129   0.07475   0.07055  -0.0561   0.9553   0.0885
  -4.750  -0.1619   0.07014   0.06558  -0.0718   0.9443   0.0966
  -4.500  -0.1468   0.06648   0.06203  -0.0698   0.9366   0.0996
  -4.250  -0.0925   0.06208   0.05729  -0.0816   0.9284   0.1117
  -4.000  -0.0724   0.05886   0.05414  -0.0812   0.9186   0.1154
  -3.750  -0.0213   0.05474   0.04973  -0.0898   0.9129   0.1283
  -3.500   0.0101   0.05245   0.04717  -0.0934   0.9024   0.1420
  -3.250   0.0493   0.04910   0.04376  -0.0974   0.8981   0.1583
  -3.000   0.0717   0.04703   0.04163  -0.0981   0.8881   0.1741
  -2.750   0.1133   0.04466   0.03913  -0.1018   0.8836   0.2006
  -2.500   0.1348   0.04257   0.03705  -0.1019   0.8741   0.2236
  -2.250   0.1716   0.04041   0.03489  -0.1041   0.8691   0.2704
  -1.250   0.3676   0.02994   0.02187  -0.1179   0.8433   0.1217
  -1.000   0.4146   0.02822   0.01958  -0.1197   0.8388   0.1094
  -0.750   0.4454   0.02724   0.01838  -0.1196   0.8295   0.1099
  -0.500   0.4859   0.02579   0.01673  -0.1209   0.8236   0.1099
  -0.250   0.5166   0.02483   0.01564  -0.1207   0.8142   0.1100
   0.000   0.5548   0.02341   0.01420  -0.1216   0.8076   0.1122
   0.250   0.5822   0.02264   0.01350  -0.1209   0.7967   0.1170
   0.500   0.6205   0.02146   0.01234  -0.1217   0.7904   0.1301
   0.750   0.6460   0.02088   0.01177  -0.1205   0.7778   0.1458
   1.000   0.6884   0.01812   0.01099  -0.1224   0.7676   1.0000
   1.250   0.7219   0.01778   0.01028  -0.1223   0.7575   1.0000
   1.500   0.7508   0.01757   0.00986  -0.1218   0.7447   1.0000
   1.750   0.7779   0.01742   0.00955  -0.1210   0.7302   1.0000
   2.000   0.8055   0.01727   0.00925  -0.1203   0.7153   1.0000
   2.250   0.8336   0.01714   0.00896  -0.1197   0.7001   1.0000
   2.500   0.8618   0.01708   0.00874  -0.1192   0.6847   1.0000
   2.750   0.8900   0.01710   0.00861  -0.1187   0.6691   1.0000
   3.000   0.9163   0.01727   0.00863  -0.1181   0.6527   1.0000
   3.250   0.9428   0.01752   0.00873  -0.1176   0.6370   1.0000
   3.500   0.9694   0.01782   0.00890  -0.1171   0.6223   1.0000
   3.750   0.9951   0.01817   0.00912  -0.1166   0.6079   1.0000
   4.000   1.0190   0.01855   0.00943  -0.1157   0.5934   1.0000
   4.250   1.0423   0.01894   0.00978  -0.1149   0.5796   1.0000
   4.500   1.0658   0.01934   0.01016  -0.1140   0.5670   1.0000
   4.750   1.0902   0.01970   0.01048  -0.1134   0.5555   1.0000
   5.000   1.1165   0.02001   0.01068  -0.1130   0.5450   1.0000
   5.250   1.1382   0.02040   0.01113  -0.1119   0.5332   1.0000
   5.500   1.1610   0.02080   0.01156  -0.1110   0.5224   1.0000
   5.750   1.1867   0.02115   0.01185  -0.1106   0.5133   1.0000
   6.000   1.2092   0.02159   0.01235  -0.1097   0.5035   1.0000
   6.250   1.2325   0.02206   0.01289  -0.1090   0.4943   1.0000
   6.500   1.2586   0.02246   0.01325  -0.1087   0.4859   1.0000
   6.750   1.2793   0.02305   0.01396  -0.1077   0.4766   1.0000
   7.000   1.3057   0.02353   0.01441  -0.1074   0.4684   1.0000
   7.250   1.3266   0.02413   0.01517  -0.1064   0.4590   1.0000
   7.500   1.3498   0.02476   0.01586  -0.1057   0.4502   1.0000
   7.750   1.3748   0.02531   0.01643  -0.1053   0.4409   1.0000
   8.000   1.3932   0.02588   0.01712  -0.1038   0.4286   1.0000
   8.250   1.4119   0.02623   0.01750  -0.1022   0.4136   1.0000
   8.500   1.4290   0.02651   0.01778  -0.1003   0.3975   1.0000
   8.750   1.4450   0.02690   0.01824  -0.0983   0.3832   1.0000
   9.000   1.4595   0.02724   0.01866  -0.0961   0.3690   1.0000
   9.250   1.4725   0.02757   0.01911  -0.0936   0.3550   1.0000
   9.500   1.4835   0.02789   0.01953  -0.0909   0.3412   1.0000
   9.750   1.4900   0.02819   0.01995  -0.0875   0.3261   1.0000
  10.000   1.4954   0.02859   0.02049  -0.0840   0.3119   1.0000
  10.250   1.4943   0.02909   0.02112  -0.0795   0.2957   1.0000
  10.500   1.4917   0.02983   0.02195  -0.0752   0.2762   1.0000
  10.750   1.4860   0.03099   0.02312  -0.0710   0.2487   1.0000
  11.000   1.4781   0.03275   0.02476  -0.0672   0.2150   1.0000
  11.250   1.4673   0.03519   0.02699  -0.0637   0.1801   1.0000
  11.500   1.4525   0.03836   0.02994  -0.0605   0.1440   1.0000
  11.750   1.4323   0.04233   0.03357  -0.0577   0.0895   1.0000
  12.000   1.4131   0.04656   0.03763  -0.0555   0.0751   1.0000
  12.250   1.3993   0.05054   0.04166  -0.0539   0.0675   1.0000
  12.500   1.3853   0.05479   0.04599  -0.0529   0.0632   1.0000
  12.750   1.3731   0.05911   0.05043  -0.0523   0.0601   1.0000
  13.000   1.3621   0.06350   0.05499  -0.0521   0.0574   1.0000
  13.250   1.3499   0.06825   0.05990  -0.0523   0.0554   1.0000
  13.500   1.3364   0.07335   0.06513  -0.0528   0.0539   1.0000
  13.750   1.3225   0.07865   0.07054  -0.0535   0.0527   1.0000
  14.000   1.3102   0.08378   0.07576  -0.0542   0.0516   1.0000
  14.250   1.3043   0.08797   0.08009  -0.0545   0.0506   1.0000
  14.500   1.3014   0.09159   0.08384  -0.0546   0.0494   1.0000
  14.750   1.3027   0.09438   0.08671  -0.0541   0.0482   1.0000
  15.000   1.3092   0.09612   0.08851  -0.0529   0.0469   1.0000
  15.250   1.3201   0.09701   0.08937  -0.0511   0.0452   1.0000
  15.500   1.3529   0.09372   0.08579  -0.0454   0.0424   1.0000
  15.750   1.3660   0.09508   0.08731  -0.0439   0.0415   1.0000
  16.000   1.3843   0.09590   0.08829  -0.0418   0.0410   1.0000
  16.250   1.3979   0.09771   0.09029  -0.0403   0.0407   1.0000
  16.500   1.4055   0.10051   0.09332  -0.0395   0.0407   1.0000
  16.750   1.4078   0.10408   0.09714  -0.0395   0.0407   1.0000
  17.000   1.4041   0.10842   0.10172  -0.0401   0.0408   1.0000
  17.250   1.3954   0.11347   0.10702  -0.0416   0.0409   1.0000
  17.500   1.3836   0.11906   0.11287  -0.0438   0.0410   1.0000
  17.750   1.3701   0.12511   0.11915  -0.0466   0.0412   1.0000
  18.000   1.3548   0.13167   0.12595  -0.0500   0.0413   1.0000
  18.250   1.3385   0.13868   0.13318  -0.0540   0.0416   1.0000
  18.500   1.3219   0.14610   0.14079  -0.0584   0.0419   1.0000
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