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GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
Reynolds number: 500,000
Max Cl/Cd: 102.16 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe79-il-500000.txt
Download as CSV file: xf-goe79-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 79 (PFALZ 11) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3035   0.09740   0.09514  -0.0118   1.0000   0.0184
  -7.750  -0.2972   0.09485   0.09262  -0.0127   1.0000   0.0187
  -7.500  -0.2915   0.09242   0.09022  -0.0136   1.0000   0.0192
  -7.250  -0.2814   0.08987   0.08770  -0.0164   1.0000   0.0195
  -7.000  -0.1925   0.07323   0.07126  -0.0299   0.9875   0.0196
  -6.750  -0.1762   0.06841   0.06644  -0.0303   0.9793   0.0197
  -6.500  -0.1569   0.06410   0.06213  -0.0334   0.9645   0.0199
  -6.250  -0.2164   0.07698   0.07487  -0.0318   0.9928   0.0197
  -6.000  -0.1909   0.07311   0.07099  -0.0359   0.9844   0.0199
  -5.750  -0.1608   0.06948   0.06734  -0.0415   0.9716   0.0202
  -5.500  -0.1267   0.06585   0.06367  -0.0480   0.9534   0.0207
  -5.250  -0.0900   0.06214   0.05988  -0.0549   0.9313   0.0213
  -5.000  -0.0588   0.05894   0.05655  -0.0599   0.9063   0.0220
  -4.750  -0.0176   0.05599   0.05341  -0.0673   0.8841   0.0225
  -4.250   0.0456   0.04983   0.04693  -0.0757   0.8470   0.0227
  -4.000   0.0634   0.04719   0.04423  -0.0760   0.8289   0.0229
  -3.750   0.0875   0.04480   0.04173  -0.0775   0.8101   0.0231
  -3.500   0.1154   0.04249   0.03931  -0.0798   0.7909   0.0234
  -3.250   0.1452   0.04024   0.03691  -0.0821   0.7709   0.0239
  -3.000   0.1764   0.03804   0.03454  -0.0845   0.7502   0.0245
  -2.750   0.2129   0.03596   0.03223  -0.0871   0.7300   0.0256
  -2.500   0.2590   0.03411   0.03001  -0.0903   0.7120   0.0259
  -2.250   0.2838   0.03152   0.02733  -0.0916   0.6955   0.0261
  -2.000   0.3092   0.02967   0.02539  -0.0926   0.6803   0.0264
  -1.750   0.3380   0.02805   0.02364  -0.0937   0.6669   0.0268
  -1.500   0.3683   0.02655   0.02199  -0.0948   0.6545   0.0273
  -1.000   0.4394   0.02408   0.01896  -0.0961   0.6318   0.0297
  -0.750   0.4686   0.02207   0.01682  -0.0972   0.6220   0.0300
  -0.500   0.4963   0.02077   0.01546  -0.0980   0.6113   0.0304
  -0.250   0.5254   0.01973   0.01431  -0.0985   0.6008   0.0312
   0.000   0.5554   0.01880   0.01320  -0.0989   0.5895   0.0325
   0.250   0.5894   0.01811   0.01214  -0.0985   0.5782   0.0343
   0.500   0.6175   0.01685   0.01085  -0.0992   0.5658   0.0349
   0.750   0.6460   0.01610   0.00999  -0.0995   0.5540   0.0358
   1.000   0.6753   0.01549   0.00923  -0.0996   0.5414   0.0376
   1.250   0.7057   0.01480   0.00830  -0.0994   0.5285   0.0401
   1.500   0.7340   0.01419   0.00764  -0.0997   0.5145   0.0417
   1.750   0.7632   0.01380   0.00702  -0.0995   0.4986   0.0464
   2.000   0.7910   0.01334   0.00650  -0.0996   0.4781   0.0491
   2.250   0.8189   0.01303   0.00601  -0.0995   0.4520   0.0553
   2.500   0.8459   0.01291   0.00569  -0.0994   0.4145   0.0646
   2.750   0.8723   0.01290   0.00548  -0.0993   0.3776   0.0768
   3.750   0.9823   0.01246   0.00450  -0.0978   0.3133   0.0515
   4.000   1.0100   0.01234   0.00434  -0.0976   0.3041   0.0466
   4.500   1.0646   0.01241   0.00439  -0.0974   0.2876   0.0474
   4.750   1.0915   0.01254   0.00450  -0.0972   0.2796   0.0472
   5.000   1.1189   0.01260   0.00458  -0.0970   0.2723   0.0484
   5.250   1.1457   0.01277   0.00472  -0.0968   0.2647   0.0506
   5.500   1.1726   0.01290   0.00485  -0.0967   0.2585   0.0565
   5.750   1.1995   0.01304   0.00505  -0.0965   0.2515   0.1108
   6.000   1.2217   0.01204   0.00537  -0.0956   0.2451   1.0000
   6.250   1.2483   0.01224   0.00555  -0.0953   0.2377   1.0000
   6.500   1.2742   0.01252   0.00579  -0.0950   0.2302   1.0000
   6.750   1.3005   0.01273   0.00600  -0.0948   0.2221   1.0000
   7.000   1.3263   0.01302   0.00626  -0.0945   0.2136   1.0000
   7.250   1.3519   0.01331   0.00652  -0.0942   0.2025   1.0000
   7.500   1.3769   0.01367   0.00683  -0.0938   0.1867   1.0000
   7.750   1.4012   0.01411   0.00718  -0.0933   0.1645   1.0000
   8.000   1.4222   0.01499   0.00778  -0.0925   0.1220   1.0000
   8.250   1.4432   0.01583   0.00847  -0.0916   0.1028   1.0000
   8.500   1.4654   0.01647   0.00908  -0.0909   0.0970   1.0000
   8.750   1.4873   0.01711   0.00973  -0.0901   0.0923   1.0000
   9.000   1.5097   0.01766   0.01034  -0.0894   0.0890   1.0000
   9.250   1.5302   0.01839   0.01109  -0.0884   0.0851   1.0000
   9.500   1.5486   0.01930   0.01201  -0.0872   0.0810   1.0000
   9.750   1.5699   0.01984   0.01264  -0.0863   0.0792   1.0000
  10.000   1.5911   0.02037   0.01325  -0.0855   0.0772   1.0000
  10.250   1.6111   0.02098   0.01394  -0.0845   0.0747   1.0000
  10.500   1.6290   0.02174   0.01475  -0.0832   0.0721   1.0000
  10.750   1.6418   0.02290   0.01595  -0.0813   0.0690   1.0000
  11.000   1.6608   0.02346   0.01660  -0.0802   0.0672   1.0000
  11.250   1.6813   0.02385   0.01709  -0.0793   0.0649   1.0000
  11.500   1.7000   0.02434   0.01764  -0.0782   0.0620   1.0000
  11.750   1.7139   0.02513   0.01845  -0.0764   0.0591   1.0000
  12.000   1.7265   0.02588   0.01927  -0.0744   0.0566   1.0000
  12.250   1.7437   0.02627   0.01975  -0.0731   0.0533   1.0000
  12.500   1.7556   0.02703   0.02051  -0.0711   0.0496   1.0000
  12.750   1.7675   0.02785   0.02139  -0.0693   0.0455   1.0000
  13.000   1.7745   0.02908   0.02260  -0.0673   0.0408   1.0000
  13.250   1.7809   0.03046   0.02404  -0.0654   0.0368   1.0000
  13.500   1.7815   0.03248   0.02611  -0.0636   0.0335   1.0000
  13.750   1.7829   0.03460   0.02831  -0.0621   0.0309   1.0000
  14.000   1.7778   0.03755   0.03132  -0.0609   0.0289   1.0000
  14.250   1.7768   0.04029   0.03419  -0.0602   0.0274   1.0000
  14.500   1.7741   0.04338   0.03741  -0.0598   0.0261   1.0000
  14.750   1.7677   0.04709   0.04121  -0.0598   0.0251   1.0000
  15.000   1.7567   0.05160   0.04583  -0.0602   0.0243   1.0000
  15.250   1.7422   0.05670   0.05106  -0.0609   0.0236   1.0000
  15.500   1.7345   0.06100   0.05551  -0.0616   0.0231   1.0000
  15.750   1.7235   0.06580   0.06045  -0.0625   0.0226   1.0000
  16.000   1.7106   0.07097   0.06576  -0.0636   0.0221   1.0000
  16.250   1.6966   0.07649   0.07141  -0.0650   0.0217   1.0000
  16.500   1.6810   0.08239   0.07744  -0.0667   0.0214   1.0000
  16.750   1.6650   0.08853   0.08370  -0.0686   0.0210   1.0000
  17.000   1.6482   0.09496   0.09025  -0.0707   0.0207   1.0000
  17.250   1.6309   0.10155   0.09695  -0.0730   0.0205   1.0000
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