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GOE 602 MOD. AIRFOIL (goe602m-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 602 MOD. AIRFOIL (goe602m-il)
Reynolds number: 500,000
Max Cl/Cd: 105.85 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe602m-il-500000.txt
Download as CSV file: xf-goe602m-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 602 MOD. 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2962   0.09865   0.09658  -0.0350   1.0000   0.0230
  -9.750  -0.3023   0.09575   0.09371  -0.0346   1.0000   0.0232
  -9.500  -0.3086   0.09292   0.09091  -0.0337   1.0000   0.0234
  -9.250  -0.3157   0.09008   0.08810  -0.0328   1.0000   0.0234
  -9.000  -0.3101   0.08481   0.08284  -0.0361   0.9988   0.0235
  -8.750  -0.3048   0.07919   0.07722  -0.0398   0.9971   0.0235
  -8.500  -0.3002   0.07324   0.07127  -0.0439   0.9953   0.0235
  -8.250  -0.2967   0.06717   0.06521  -0.0481   0.9932   0.0236
  -8.000  -0.3049   0.05869   0.05676  -0.0536   0.9893   0.0238
  -7.750  -0.3105   0.04969   0.04777  -0.0620   0.9847   0.0240
  -7.250  -0.3678   0.03155   0.02826  -0.0920   0.9733   0.0173
  -7.000  -0.3449   0.02370   0.01952  -0.0966   0.9707   0.0179
  -6.750  -0.3221   0.02286   0.01863  -0.0966   0.9653   0.0188
  -6.500  -0.2898   0.02271   0.01850  -0.0980   0.9626   0.0202
  -6.250  -0.2576   0.02055   0.01598  -0.0997   0.9604   0.0216
  -6.000  -0.2229   0.01891   0.01400  -0.1014   0.9589   0.0229
  -5.750  -0.1889   0.01644   0.01113  -0.1034   0.9577   0.0246
  -5.500  -0.1606   0.01566   0.01033  -0.1038   0.9536   0.0265
  -5.250  -0.1289   0.01501   0.00959  -0.1047   0.9499   0.0287
  -5.000  -0.0945   0.01417   0.00862  -0.1061   0.9473   0.0307
  -4.750  -0.0580   0.01387   0.00820  -0.1077   0.9450   0.0321
  -4.500  -0.0284   0.01200   0.00621  -0.1084   0.9414   0.0355
  -4.250  -0.0018   0.01145   0.00563  -0.1080   0.9352   0.0376
  -4.000   0.0306   0.01091   0.00503  -0.1089   0.9312   0.0398
  -3.750   0.0599   0.01051   0.00456  -0.1091   0.9261   0.0418
  -3.500   0.0878   0.01015   0.00414  -0.1089   0.9196   0.0429
  -3.250   0.1182   0.00951   0.00343  -0.1094   0.9149   0.0458
  -3.000   0.1434   0.00920   0.00309  -0.1087   0.9066   0.0495
  -2.750   0.1736   0.00893   0.00275  -0.1090   0.9008   0.0530
  -2.500   0.1993   0.00870   0.00249  -0.1084   0.8921   0.0591
  -2.250   0.2274   0.00827   0.00226  -0.1084   0.8851   0.1143
  -2.000   0.2513   0.00769   0.00212  -0.1078   0.8755   0.2534
  -1.750   0.2783   0.00752   0.00205  -0.1075   0.8668   0.3041
  -1.500   0.3059   0.00738   0.00194  -0.1073   0.8578   0.3355
  -1.250   0.3316   0.00723   0.00187  -0.1068   0.8468   0.3678
  -1.000   0.3577   0.00707   0.00181  -0.1063   0.8357   0.4108
  -0.750   0.3837   0.00690   0.00178  -0.1058   0.8240   0.4719
  -0.500   0.4096   0.00678   0.00177  -0.1053   0.8114   0.5349
  -0.250   0.4348   0.00664   0.00175  -0.1046   0.7977   0.5947
   0.000   0.4585   0.00641   0.00173  -0.1036   0.7828   0.6657
   0.250   0.4780   0.00603   0.00177  -0.1014   0.7673   0.8206
   0.500   0.5386   0.00582   0.00172  -0.1084   0.7501   1.0000
   0.750   0.5630   0.00594   0.00171  -0.1075   0.7313   1.0000
   1.000   0.5869   0.00608   0.00172  -0.1065   0.7094   1.0000
   1.250   0.6102   0.00625   0.00174  -0.1054   0.6857   1.0000
   1.500   0.6341   0.00640   0.00178  -0.1045   0.6627   1.0000
   1.750   0.6581   0.00657   0.00184  -0.1036   0.6430   1.0000
   2.000   0.6825   0.00672   0.00190  -0.1028   0.6246   1.0000
   2.250   0.7070   0.00689   0.00198  -0.1021   0.6061   1.0000
   2.500   0.7311   0.00707   0.00208  -0.1012   0.5873   1.0000
   2.750   0.7554   0.00725   0.00218  -0.1005   0.5693   1.0000
   3.000   0.7800   0.00743   0.00230  -0.0998   0.5519   1.0000
   3.250   0.8041   0.00763   0.00242  -0.0990   0.5324   1.0000
   3.500   0.8279   0.00784   0.00257  -0.0982   0.5134   1.0000
   3.750   0.8521   0.00805   0.00271  -0.0974   0.4948   1.0000
   4.000   0.8749   0.00833   0.00288  -0.0964   0.4691   1.0000
   4.250   0.8977   0.00861   0.00305  -0.0954   0.4418   1.0000
   4.500   0.9210   0.00889   0.00325  -0.0945   0.4171   1.0000
   4.750   0.9433   0.00922   0.00346  -0.0935   0.3873   1.0000
   5.000   0.9650   0.00961   0.00370  -0.0924   0.3540   1.0000
   5.250   0.9859   0.01007   0.00397  -0.0912   0.3121   1.0000
   5.500   1.0047   0.01071   0.00435  -0.0897   0.2576   1.0000
   5.750   1.0198   0.01170   0.00489  -0.0877   0.1803   1.0000
   6.000   1.0296   0.01316   0.00573  -0.0849   0.0832   1.0000
   6.250   1.0437   0.01427   0.00652  -0.0826   0.0262   1.0000
   6.500   1.0644   0.01479   0.00710  -0.0813   0.0228   1.0000
   6.750   1.0833   0.01546   0.00788  -0.0796   0.0194   1.0000
   7.000   1.1034   0.01598   0.00847  -0.0783   0.0185   1.0000
   7.250   1.1222   0.01660   0.00917  -0.0767   0.0175   1.0000
   7.500   1.1394   0.01729   0.00994  -0.0748   0.0166   1.0000
   7.750   1.1550   0.01806   0.01077  -0.0728   0.0160   1.0000
   8.000   1.1673   0.01895   0.01174  -0.0701   0.0153   1.0000
   8.250   1.1761   0.01991   0.01277  -0.0670   0.0148   1.0000
   8.500   1.1795   0.02124   0.01418  -0.0630   0.0142   1.0000
   8.750   1.1797   0.02302   0.01604  -0.0588   0.0135   1.0000
   9.000   1.1945   0.02369   0.01679  -0.0569   0.0131   1.0000
   9.250   1.2055   0.02477   0.01795  -0.0545   0.0129   1.0000
   9.500   1.2164   0.02601   0.01925  -0.0522   0.0127   1.0000
   9.750   1.2281   0.02730   0.02062  -0.0501   0.0124   1.0000
  10.000   1.2408   0.02872   0.02214  -0.0482   0.0122   1.0000
  10.250   1.2544   0.03020   0.02372  -0.0464   0.0119   1.0000
  10.500   1.2695   0.03193   0.02556  -0.0449   0.0117   1.0000
  10.750   1.2867   0.03403   0.02781  -0.0437   0.0118   1.0000
  11.000   1.3048   0.03661   0.03057  -0.0427   0.0122   1.0000
  11.250   1.3159   0.03891   0.03306  -0.0410   0.0121   1.0000
  11.500   1.3224   0.04102   0.03535  -0.0388   0.0120   1.0000
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