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GOE 79 (PFALZ 11) AIRFOIL (goe79-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 79 (PFALZ 11) AIRFOIL (goe79-il)
Reynolds number: 500,000
Max Cl/Cd: 97.35 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe79-il-500000-n5.txt
Download as CSV file: xf-goe79-il-500000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2363   0.10129   0.09909  -0.0183   1.0000   0.0162
  -9.250  -0.2318   0.09812   0.09593  -0.0193   1.0000   0.0162
  -9.000  -0.2276   0.09499   0.09282  -0.0202   1.0000   0.0162
  -8.750  -0.2222   0.09184   0.08968  -0.0206   1.0000   0.0163
  -8.500  -0.2162   0.08895   0.08682  -0.0208   0.9997   0.0164
  -8.250  -0.2029   0.08540   0.08327  -0.0234   0.9723   0.0167
  -8.000  -0.1852   0.08147   0.07930  -0.0272   0.9337   0.0173
  -7.750  -0.1749   0.07817   0.07592  -0.0291   0.9039   0.0180
  -7.500  -0.1687   0.07524   0.07291  -0.0300   0.8820   0.0183
  -7.000  -0.1568   0.06940   0.06694  -0.0326   0.8476   0.0186
  -6.750  -0.1459   0.06609   0.06358  -0.0355   0.8327   0.0186
  -6.500  -0.1326   0.06268   0.06012  -0.0390   0.8184   0.0187
  -6.000  -0.1056   0.05581   0.05314  -0.0435   0.7910   0.0189
  -5.750  -0.1227   0.06724   0.06447  -0.0501   0.8231   0.0188
  -5.500  -0.1028   0.06450   0.06166  -0.0525   0.8075   0.0190
  -5.250  -0.0800   0.06181   0.05888  -0.0556   0.7892   0.0192
  -5.000  -0.0551   0.05912   0.05609  -0.0590   0.7684   0.0196
  -4.750  -0.0284   0.05642   0.05325  -0.0625   0.7465   0.0201
  -4.500   0.0008   0.05365   0.05033  -0.0665   0.7255   0.0209
  -4.250   0.0389   0.05066   0.04716  -0.0722   0.7055   0.0213
  -4.000   0.0768   0.04771   0.04402  -0.0774   0.6869   0.0214
  -3.750   0.1127   0.04485   0.04095  -0.0816   0.6708   0.0215
  -3.500   0.1393   0.04220   0.03818  -0.0836   0.6554   0.0215
  -3.000   0.1908   0.03796   0.03375  -0.0867   0.6266   0.0219
  -2.750   0.2210   0.03602   0.03168  -0.0887   0.6137   0.0223
  -2.500   0.2521   0.03418   0.02970  -0.0906   0.6017   0.0229
  -2.250   0.2864   0.03231   0.02768  -0.0927   0.5911   0.0241
  -2.000   0.3247   0.03039   0.02553  -0.0948   0.5825   0.0244
  -1.750   0.3602   0.02849   0.02341  -0.0964   0.5736   0.0245
  -1.500   0.3933   0.02673   0.02145  -0.0975   0.5648   0.0246
  -1.250   0.4225   0.02485   0.01946  -0.0987   0.5550   0.0247
  -1.000   0.4505   0.02347   0.01801  -0.0996   0.5463   0.0250
  -0.750   0.4791   0.02239   0.01683  -0.1004   0.5368   0.0255
  -0.500   0.5093   0.02132   0.01563  -0.1011   0.5250   0.0263
  -0.250   0.5403   0.02024   0.01435  -0.1015   0.5098   0.0271
   0.250   0.5884   0.00646   0.00021  -0.0971   0.4693   0.0282
   0.750   0.6633   0.01633   0.00950  -0.1025   0.4383   0.0287
   1.000   0.6912   0.01582   0.00881  -0.1027   0.4077   0.0292
   1.250   0.7191   0.01545   0.00819  -0.1028   0.3753   0.0299
   1.500   0.7481   0.01572   0.00805  -0.1022   0.3502   0.0325
   1.750   0.7762   0.01476   0.00698  -0.1025   0.3311   0.0331
   2.000   0.8048   0.01408   0.00613  -0.1024   0.3172   0.0274
   2.250   0.8330   0.01371   0.00564  -0.1023   0.3064   0.0269
   2.500   0.8610   0.01341   0.00522  -0.1022   0.2971   0.0268
   2.750   0.8887   0.01320   0.00490  -0.1020   0.2866   0.0269
   3.000   0.9164   0.01304   0.00466  -0.1019   0.2771   0.0274
   3.250   0.9438   0.01307   0.00458  -0.1017   0.2689   0.0282
   3.500   0.9714   0.01289   0.00443  -0.1016   0.2624   0.0292
   3.750   0.9988   0.01284   0.00436  -0.1015   0.2551   0.0294
   4.000   1.0261   0.01284   0.00434  -0.1014   0.2489   0.0297
   4.250   1.0535   0.01285   0.00436  -0.1013   0.2423   0.0302
   4.750   1.1077   0.01302   0.00451  -0.1010   0.2279   0.0318
   5.000   1.1345   0.01315   0.00464  -0.1008   0.2201   0.0337
   5.250   1.1614   0.01327   0.00477  -0.1007   0.2141   0.0350
   5.500   1.1880   0.01344   0.00493  -0.1005   0.2068   0.0363
   5.750   1.2144   0.01363   0.00511  -0.1002   0.2001   0.0379
   6.000   1.2406   0.01384   0.00530  -0.1000   0.1915   0.0420
   6.250   1.2665   0.01410   0.00553  -0.0997   0.1805   0.0518
   6.500   1.2880   0.01323   0.00595  -0.0988   0.1655   1.0000
   6.750   1.3122   0.01372   0.00630  -0.0983   0.1437   1.0000
   7.250   1.3568   0.01520   0.00741  -0.0969   0.0904   1.0000
   7.500   1.3808   0.01566   0.00787  -0.0964   0.0865   1.0000
   7.750   1.4046   0.01613   0.00833  -0.0958   0.0830   1.0000
   8.000   1.4288   0.01651   0.00874  -0.0953   0.0815   1.0000
   8.250   1.4528   0.01689   0.00917  -0.0948   0.0801   1.0000
   8.500   1.4763   0.01731   0.00965  -0.0942   0.0785   1.0000
   8.750   1.4993   0.01777   0.01015  -0.0936   0.0769   1.0000
   9.000   1.5217   0.01828   0.01070  -0.0928   0.0754   1.0000
   9.250   1.5431   0.01887   0.01133  -0.0920   0.0733   1.0000
   9.500   1.5630   0.01957   0.01206  -0.0909   0.0705   1.0000
   9.750   1.5860   0.01991   0.01247  -0.0903   0.0691   1.0000
  10.000   1.6080   0.02034   0.01296  -0.0896   0.0672   1.0000
  10.250   1.6291   0.02082   0.01350  -0.0887   0.0650   1.0000
  10.500   1.6489   0.02139   0.01409  -0.0877   0.0625   1.0000
  10.750   1.6667   0.02211   0.01484  -0.0864   0.0603   1.0000
  11.000   1.6868   0.02256   0.01539  -0.0855   0.0588   1.0000
  11.250   1.7060   0.02306   0.01596  -0.0844   0.0565   1.0000
  11.500   1.7237   0.02365   0.01659  -0.0831   0.0538   1.0000
  11.750   1.7390   0.02436   0.01731  -0.0815   0.0511   1.0000
  12.000   1.7539   0.02500   0.01804  -0.0798   0.0488   1.0000
  12.250   1.7650   0.02575   0.01883  -0.0776   0.0457   1.0000
  12.500   1.7743   0.02666   0.01977  -0.0753   0.0426   1.0000
  12.750   1.7829   0.02768   0.02085  -0.0731   0.0391   1.0000
  13.000   1.7893   0.02895   0.02215  -0.0710   0.0356   1.0000
  13.250   1.7947   0.03042   0.02367  -0.0691   0.0321   1.0000
  13.500   1.7982   0.03217   0.02548  -0.0674   0.0291   1.0000
  13.750   1.8002   0.03419   0.02757  -0.0659   0.0262   1.0000
  14.000   1.8013   0.03645   0.02992  -0.0647   0.0238   1.0000
  14.250   1.8004   0.03906   0.03261  -0.0638   0.0217   1.0000
  14.500   1.7984   0.04195   0.03559  -0.0632   0.0201   1.0000
  14.750   1.7954   0.04511   0.03885  -0.0628   0.0188   1.0000
  15.000   1.7900   0.04871   0.04256  -0.0628   0.0177   1.0000
  15.250   1.7831   0.05262   0.04658  -0.0631   0.0169   1.0000
  15.500   1.7762   0.05666   0.05075  -0.0635   0.0163   1.0000
  15.750   1.7671   0.06107   0.05529  -0.0641   0.0157   1.0000
  16.000   1.7556   0.06587   0.06022  -0.0649   0.0153   1.0000
  16.250   1.7422   0.07108   0.06557  -0.0660   0.0149   1.0000
  16.500   1.7275   0.07667   0.07129  -0.0674   0.0145   1.0000
  16.750   1.7113   0.08263   0.07738  -0.0690   0.0143   1.0000
  17.000   1.6940   0.08898   0.08387  -0.0710   0.0140   1.0000
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