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GOE 478 AIRFOIL (goe478-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 478 AIRFOIL (goe478-il)
Reynolds number: 500,000
Max Cl/Cd: 101.26 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe478-il-500000.txt
Download as CSV file: xf-goe478-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 478 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2032   0.08510   0.08263  -0.0726   0.9677   0.0451
  -9.000  -0.1881   0.08136   0.07888  -0.0767   0.9583   0.0461
  -8.750  -0.3608   0.02711   0.02240  -0.1236   0.8976   0.0386
  -8.500  -0.3456   0.02529   0.02026  -0.1226   0.8835   0.0385
  -8.250  -0.3297   0.02334   0.01802  -0.1215   0.8721   0.0387
  -8.000  -0.3131   0.02187   0.01636  -0.1200   0.8614   0.0389
  -7.750  -0.2925   0.02073   0.01505  -0.1191   0.8530   0.0391
  -7.500  -0.2712   0.01997   0.01422  -0.1182   0.8446   0.0396
  -7.250  -0.2480   0.01926   0.01339  -0.1175   0.8381   0.0401
  -7.000  -0.2257   0.01855   0.01259  -0.1166   0.8315   0.0405
  -6.750  -0.2035   0.01772   0.01159  -0.1156   0.8251   0.0409
  -6.500  -0.1797   0.01697   0.01068  -0.1149   0.8197   0.0412
  -6.250  -0.1561   0.01629   0.00987  -0.1141   0.8144   0.0416
  -6.000  -0.1319   0.01567   0.00915  -0.1133   0.8095   0.0420
  -5.750  -0.1069   0.01515   0.00850  -0.1126   0.8048   0.0426
  -5.500  -0.0808   0.01471   0.00793  -0.1122   0.8005   0.0430
  -5.250  -0.0560   0.01421   0.00735  -0.1115   0.7961   0.0435
  -5.000  -0.0320   0.01348   0.00663  -0.1108   0.7913   0.0443
  -4.750  -0.0065   0.01309   0.00624  -0.1102   0.7870   0.0452
  -4.500   0.0199   0.01280   0.00590  -0.1098   0.7826   0.0462
  -4.250   0.0453   0.01250   0.00558  -0.1091   0.7781   0.0473
  -4.000   0.0708   0.01222   0.00526  -0.1085   0.7737   0.0482
  -3.750   0.0963   0.01187   0.00489  -0.1079   0.7698   0.0492
  -3.500   0.1216   0.01149   0.00450  -0.1073   0.7658   0.0506
  -3.250   0.1476   0.01126   0.00427  -0.1068   0.7617   0.0521
  -3.000   0.1729   0.01104   0.00405  -0.1060   0.7572   0.0539
  -2.750   0.1980   0.01075   0.00377  -0.1053   0.7525   0.0562
  -2.500   0.2241   0.01055   0.00356  -0.1048   0.7482   0.0594
  -2.250   0.2507   0.01037   0.00337  -0.1044   0.7439   0.0639
  -2.000   0.2756   0.01015   0.00321  -0.1036   0.7391   0.0709
  -1.750   0.3009   0.00994   0.00311  -0.1029   0.7337   0.0889
  -1.500   0.3272   0.00980   0.00302  -0.1024   0.7284   0.1139
  -1.250   0.3529   0.00967   0.00295  -0.1018   0.7230   0.1322
  -1.000   0.3782   0.00955   0.00291  -0.1011   0.7170   0.1505
  -0.750   0.4044   0.00946   0.00288  -0.1005   0.7109   0.1726
  -0.500   0.4305   0.00940   0.00286  -0.1000   0.7046   0.1943
  -0.250   0.4554   0.00929   0.00282  -0.0992   0.6969   0.2142
   0.000   0.4813   0.00923   0.00275  -0.0986   0.6892   0.2349
   0.250   0.5050   0.00906   0.00271  -0.0976   0.6799   0.2613
   0.500   0.5284   0.00883   0.00264  -0.0966   0.6707   0.3245
   0.750   0.5440   0.00811   0.00267  -0.0942   0.6588   0.5600
   1.000   0.5548   0.00740   0.00273  -0.0902   0.6455   0.8040
   1.250   0.6265   0.00738   0.00291  -0.0989   0.6223   0.9576
   1.500   0.6692   0.00756   0.00294  -0.1018   0.5952   0.9759
   2.000   0.7718   0.00813   0.00310  -0.1117   0.5472   1.0000
   2.250   0.7888   0.00835   0.00318  -0.1094   0.5324   1.0000
   2.500   0.8073   0.00853   0.00328  -0.1075   0.5197   1.0000
   2.750   0.8265   0.00871   0.00338  -0.1056   0.5095   1.0000
   3.000   0.8459   0.00889   0.00349  -0.1038   0.5008   1.0000
   3.250   0.8660   0.00905   0.00361  -0.1022   0.4934   1.0000
   3.500   0.8863   0.00920   0.00372  -0.1006   0.4855   1.0000
   3.750   0.9057   0.00941   0.00385  -0.0988   0.4782   1.0000
   4.000   0.9271   0.00951   0.00396  -0.0974   0.4716   1.0000
   4.250   0.9473   0.00968   0.00409  -0.0957   0.4648   1.0000
   4.500   0.9678   0.00986   0.00423  -0.0942   0.4589   1.0000
   4.750   0.9892   0.00997   0.00436  -0.0927   0.4527   1.0000
   5.000   1.0092   0.01014   0.00449  -0.0911   0.4460   1.0000
   5.250   1.0294   0.01030   0.00464  -0.0895   0.4387   1.0000
   5.500   1.0495   0.01043   0.00477  -0.0878   0.4309   1.0000
   5.750   1.0683   0.01063   0.00493  -0.0860   0.4231   1.0000
   6.000   1.0881   0.01076   0.00506  -0.0843   0.4142   1.0000
   6.250   1.1059   0.01097   0.00523  -0.0822   0.4058   1.0000
   6.500   1.1250   0.01111   0.00539  -0.0804   0.3960   1.0000
   6.750   1.1413   0.01132   0.00556  -0.0781   0.3864   1.0000
   7.000   1.1568   0.01151   0.00574  -0.0756   0.3761   1.0000
   7.250   1.1727   0.01172   0.00593  -0.0732   0.3654   1.0000
   7.500   1.1870   0.01199   0.00616  -0.0706   0.3532   1.0000
   7.750   1.2009   0.01230   0.00642  -0.0680   0.3380   1.0000
   8.000   1.2147   0.01265   0.00671  -0.0654   0.3209   1.0000
   8.250   1.2274   0.01308   0.00706  -0.0628   0.3001   1.0000
   8.500   1.2379   0.01362   0.00750  -0.0599   0.2778   1.0000
   8.750   1.2474   0.01426   0.00802  -0.0569   0.2567   1.0000
   9.000   1.2579   0.01491   0.00857  -0.0542   0.2374   1.0000
   9.250   1.2685   0.01559   0.00917  -0.0517   0.2206   1.0000
   9.500   1.2794   0.01629   0.00980  -0.0492   0.2065   1.0000
   9.750   1.2902   0.01703   0.01049  -0.0469   0.1934   1.0000
  10.000   1.3016   0.01777   0.01118  -0.0448   0.1815   1.0000
  10.250   1.3140   0.01848   0.01187  -0.0428   0.1709   1.0000
  10.500   1.3253   0.01930   0.01265  -0.0408   0.1613   1.0000
  10.750   1.3356   0.02019   0.01350  -0.0389   0.1518   1.0000
  11.000   1.3479   0.02100   0.01432  -0.0372   0.1431   1.0000
  11.250   1.3576   0.02200   0.01529  -0.0353   0.1347   1.0000
  11.500   1.3672   0.02304   0.01631  -0.0336   0.1261   1.0000
  11.750   1.3773   0.02409   0.01736  -0.0320   0.1179   1.0000
  12.000   1.3846   0.02537   0.01861  -0.0302   0.1101   1.0000
  12.250   1.3922   0.02666   0.01989  -0.0286   0.1029   1.0000
  12.500   1.3999   0.02800   0.02124  -0.0271   0.0971   1.0000
  12.750   1.4063   0.02946   0.02270  -0.0257   0.0923   1.0000
  13.000   1.4122   0.03101   0.02427  -0.0242   0.0883   1.0000
  13.250   1.4198   0.03246   0.02576  -0.0230   0.0850   1.0000
  13.500   1.4238   0.03424   0.02755  -0.0217   0.0820   1.0000
  13.750   1.4273   0.03611   0.02945  -0.0205   0.0795   1.0000
  14.000   1.4351   0.03764   0.03106  -0.0195   0.0775   1.0000
  14.250   1.4402   0.03947   0.03293  -0.0186   0.0757   1.0000
  14.500   1.4436   0.04149   0.03499  -0.0176   0.0741   1.0000
  14.750   1.4436   0.04386   0.03739  -0.0167   0.0724   1.0000
  15.000   1.4451   0.04616   0.03975  -0.0159   0.0709   1.0000
  15.250   1.4506   0.04815   0.04183  -0.0153   0.0697   1.0000
  15.500   1.4553   0.05025   0.04400  -0.0149   0.0683   1.0000
  15.750   1.4585   0.05254   0.04635  -0.0145   0.0668   1.0000
  16.000   1.4589   0.05520   0.04904  -0.0142   0.0654   1.0000
  16.250   1.4557   0.05827   0.05214  -0.0139   0.0641   1.0000
  16.500   1.4564   0.06097   0.05491  -0.0137   0.0631   1.0000
  16.750   1.4606   0.06337   0.05741  -0.0137   0.0623   1.0000
  17.000   1.4632   0.06595   0.06007  -0.0138   0.0613   1.0000
  17.250   1.4651   0.06864   0.06284  -0.0139   0.0604   1.0000
  17.500   1.4662   0.07148   0.06574  -0.0141   0.0593   1.0000
  17.750   1.4660   0.07444   0.06876  -0.0143   0.0585   1.0000
  18.000   1.4646   0.07750   0.07185  -0.0145   0.0575   1.0000
  18.250   1.4624   0.08048   0.07484  -0.0145   0.0564   1.0000
  18.500   1.4641   0.08335   0.07782  -0.0150   0.0557   1.0000
  18.750   1.4648   0.08640   0.08098  -0.0157   0.0549   1.0000
  19.000   1.4654   0.08937   0.08404  -0.0162   0.0541   1.0000
  19.250   1.4651   0.09250   0.08724  -0.0168   0.0532   1.0000
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