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GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il)
Reynolds number: 500,000
Max Cl/Cd: 103.89 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe330-il-500000.txt
Download as CSV file: xf-goe330-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1378   0.08496   0.08273  -0.0709   0.9737   0.0233
  -8.000  -0.1237   0.08124   0.07901  -0.0753   0.9649   0.0246
  -7.750  -0.1146   0.07694   0.07468  -0.0846   0.9488   0.0254
  -7.500  -0.0995   0.07263   0.07033  -0.0909   0.9381   0.0255
  -7.250  -0.0916   0.06781   0.06549  -0.0936   0.9290   0.0258
  -7.000  -0.0806   0.06571   0.06337  -0.0925   0.9211   0.0262
  -6.750  -0.0664   0.06341   0.06103  -0.0933   0.9133   0.0267
  -6.500  -0.0499   0.06064   0.05822  -0.0960   0.9044   0.0274
  -6.250  -0.0305   0.05740   0.05490  -0.0998   0.8969   0.0284
  -6.000   0.0092   0.05117   0.04846  -0.1125   0.8878   0.0313
  -5.750   0.0301   0.04481   0.04190  -0.1178   0.8812   0.0318
  -5.500   0.0462   0.04290   0.03998  -0.1177   0.8737   0.0324
  -5.250   0.0665   0.04118   0.03818  -0.1183   0.8673   0.0331
  -5.000   0.0893   0.03893   0.03585  -0.1197   0.8599   0.0342
  -4.750   0.1154   0.03609   0.03283  -0.1217   0.8530   0.0363
  -4.500   0.1463   0.03036   0.02658  -0.1249   0.8457   0.0395
  -4.250   0.1682   0.02890   0.02508  -0.1250   0.8386   0.0403
  -4.000   0.1916   0.02770   0.02382  -0.1252   0.8312   0.0415
  -3.750   0.2167   0.02614   0.02209  -0.1253   0.8232   0.0439
  -3.500   0.2444   0.02321   0.01862  -0.1254   0.8156   0.0486
  -3.250   0.2684   0.02187   0.01724  -0.1254   0.8078   0.0496
  -3.000   0.2934   0.02086   0.01615  -0.1253   0.8001   0.0511
  -2.750   0.3196   0.01993   0.01505  -0.1250   0.7919   0.0545
  -2.500   0.3463   0.01845   0.01318  -0.1245   0.7831   0.0594
  -2.250   0.3717   0.01733   0.01198  -0.1244   0.7742   0.0608
  -2.000   0.3994   0.01419   0.00828  -0.1231   0.7644   0.0450
  -1.750   0.4259   0.01235   0.00608  -0.1224   0.7547   0.0416
  -1.500   0.4525   0.01173   0.00533  -0.1220   0.7438   0.0420
  -1.250   0.4789   0.01115   0.00465  -0.1215   0.7308   0.0424
  -1.000   0.5051   0.01062   0.00402  -0.1210   0.7167   0.0425
  -0.750   0.5311   0.01026   0.00357  -0.1205   0.7017   0.0432
  -0.500   0.5569   0.01000   0.00322  -0.1200   0.6867   0.0440
  -0.250   0.5828   0.00981   0.00295  -0.1195   0.6725   0.0451
   0.000   0.6085   0.00969   0.00273  -0.1189   0.6581   0.0462
   0.250   0.6343   0.00965   0.00260  -0.1184   0.6440   0.0475
   0.500   0.6599   0.00954   0.00245  -0.1180   0.6303   0.0512
   0.750   0.6860   0.00956   0.00241  -0.1175   0.6173   0.0553
   1.000   0.7119   0.00956   0.00238  -0.1171   0.6044   0.0636
   1.250   0.7376   0.00954   0.00232  -0.1167   0.5905   0.0867
   1.500   0.7632   0.00953   0.00233  -0.1162   0.5745   0.1114
   1.750   0.7814   0.00828   0.00258  -0.1150   0.5577   0.7253
   2.000   0.8260   0.00801   0.00266  -0.1184   0.5335   1.0000
   2.250   0.8493   0.00822   0.00273  -0.1175   0.5087   1.0000
   2.500   0.8717   0.00849   0.00282  -0.1165   0.4839   1.0000
   2.750   0.8948   0.00876   0.00295  -0.1156   0.4644   1.0000
   3.000   0.9182   0.00903   0.00309  -0.1147   0.4502   1.0000
   3.250   0.9417   0.00929   0.00325  -0.1140   0.4385   1.0000
   3.500   0.9660   0.00952   0.00342  -0.1133   0.4284   1.0000
   3.750   0.9903   0.00975   0.00359  -0.1127   0.4203   1.0000
   4.000   1.0147   0.00997   0.00376  -0.1121   0.4125   1.0000
   4.250   1.0392   0.01020   0.00394  -0.1116   0.4058   1.0000
   4.500   1.0640   0.01040   0.00413  -0.1111   0.3991   1.0000
   4.750   1.0877   0.01067   0.00434  -0.1104   0.3927   1.0000
   5.000   1.1131   0.01082   0.00452  -0.1100   0.3867   1.0000
   5.250   1.1374   0.01105   0.00473  -0.1095   0.3809   1.0000
   5.500   1.1616   0.01128   0.00495  -0.1089   0.3756   1.0000
   5.750   1.1864   0.01145   0.00514  -0.1084   0.3691   1.0000
   6.000   1.2095   0.01172   0.00537  -0.1077   0.3613   1.0000
   6.250   1.2341   0.01188   0.00557  -0.1072   0.3530   1.0000
   6.500   1.2572   0.01213   0.00580  -0.1065   0.3446   1.0000
   6.750   1.2809   0.01233   0.00601  -0.1059   0.3358   1.0000
   7.000   1.3041   0.01256   0.00626  -0.1052   0.3268   1.0000
   7.250   1.3260   0.01285   0.00652  -0.1044   0.3149   1.0000
   7.500   1.3476   0.01315   0.00679  -0.1034   0.3008   1.0000
   7.750   1.3687   0.01348   0.00709  -0.1024   0.2831   1.0000
   8.000   1.3867   0.01399   0.00748  -0.1010   0.2578   1.0000
   8.250   1.3991   0.01476   0.00803  -0.0986   0.2170   1.0000
   8.500   1.4047   0.01596   0.00891  -0.0952   0.1741   1.0000
   8.750   1.4103   0.01719   0.00989  -0.0919   0.1346   1.0000
   9.000   1.3922   0.01998   0.01202  -0.0855   0.0365   1.0000
   9.250   1.4003   0.02113   0.01317  -0.0828   0.0264   1.0000
   9.500   1.4122   0.02204   0.01417  -0.0808   0.0239   1.0000
   9.750   1.4212   0.02317   0.01538  -0.0785   0.0219   1.0000
  10.000   1.4304   0.02432   0.01663  -0.0764   0.0208   1.0000
  10.250   1.4407   0.02541   0.01780  -0.0745   0.0198   1.0000
  10.500   1.4493   0.02665   0.01913  -0.0726   0.0188   1.0000
  10.750   1.4557   0.02811   0.02067  -0.0706   0.0180   1.0000
  11.000   1.4585   0.02991   0.02256  -0.0685   0.0173   1.0000
  11.250   1.4559   0.03223   0.02501  -0.0661   0.0168   1.0000
  11.500   1.4501   0.03495   0.02785  -0.0638   0.0164   1.0000
  11.750   1.4543   0.03688   0.02989  -0.0624   0.0161   1.0000
  12.000   1.4555   0.03915   0.03226  -0.0610   0.0158   1.0000
  12.250   1.4550   0.04168   0.03490  -0.0597   0.0155   1.0000
  12.500   1.4537   0.04442   0.03774  -0.0586   0.0151   1.0000
  12.750   1.4515   0.04736   0.04079  -0.0578   0.0148   1.0000
  13.000   1.4494   0.05043   0.04396  -0.0572   0.0144   1.0000
  13.250   1.4466   0.05369   0.04732  -0.0567   0.0141   1.0000
  13.500   1.4430   0.05714   0.05086  -0.0565   0.0138   1.0000
  13.750   1.4380   0.06083   0.05463  -0.0563   0.0135   1.0000
  14.000   1.4317   0.06472   0.05860  -0.0562   0.0133   1.0000
  14.250   1.4244   0.06873   0.06269  -0.0561   0.0131   1.0000
  14.500   1.4167   0.07266   0.06668  -0.0558   0.0129   1.0000
  14.750   1.4105   0.07588   0.06993  -0.0544   0.0126   1.0000
  15.000   1.4117   0.07904   0.07319  -0.0546   0.0125   1.0000
  15.250   1.4126   0.08213   0.07638  -0.0547   0.0123   1.0000
  15.500   1.4138   0.08516   0.07952  -0.0547   0.0122   1.0000
  15.750   1.4153   0.08809   0.08254  -0.0547   0.0120   1.0000
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