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GOE 619 AIRFOIL (goe619-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 619 AIRFOIL (goe619-il)
Reynolds number: 50,000
Max Cl/Cd: 33.26 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe619-il-50000-n5.txt
Download as CSV file: xf-goe619-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 619 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3214   0.10399   0.09677  -0.0437   1.0000   0.0853
  -9.250  -0.3312   0.10123   0.09410  -0.0429   1.0000   0.0851
  -9.000  -0.3436   0.09864   0.09162  -0.0418   1.0000   0.0853
  -8.750  -0.3591   0.09613   0.08922  -0.0404   1.0000   0.0855
  -8.500  -0.3777   0.09369   0.08690  -0.0388   1.0000   0.0858
  -8.250  -0.3981   0.09138   0.08471  -0.0369   1.0000   0.0857
  -8.000  -0.4217   0.08881   0.08226  -0.0354   0.9994   0.0859
  -7.750  -0.4242   0.08181   0.07525  -0.0437   0.9885   0.0867
  -7.500  -0.4313   0.07082   0.06414  -0.0561   0.9758   0.0873
  -7.250  -0.4431   0.05847   0.05133  -0.0680   0.9629   0.0880
  -7.000  -0.4425   0.04956   0.04163  -0.0749   0.9526   0.0896
  -6.750  -0.4171   0.04762   0.03963  -0.0766   0.9457   0.0917
  -6.500  -0.3962   0.04536   0.03714  -0.0779   0.9378   0.0948
  -6.250  -0.3728   0.04211   0.03338  -0.0803   0.9308   0.1000
  -6.000  -0.3503   0.03965   0.03052  -0.0815   0.9235   0.1050
  -5.750  -0.3241   0.03840   0.02917  -0.0823   0.9165   0.1104
  -5.500  -0.2920   0.03602   0.02623  -0.0845   0.9117   0.1186
  -5.250  -0.2723   0.03553   0.02583  -0.0836   0.9028   0.1252
  -5.000  -0.2407   0.03443   0.02448  -0.0850   0.8973   0.1360
  -4.750  -0.2163   0.03376   0.02357  -0.0851   0.8898   0.1474
  -4.500  -0.1883   0.03366   0.02353  -0.0855   0.8830   0.1598
  -4.250  -0.1528   0.03344   0.02323  -0.0872   0.8785   0.1754
  -4.000  -0.1347   0.03318   0.02292  -0.0859   0.8692   0.1841
  -3.750  -0.1013   0.03249   0.02198  -0.0871   0.8639   0.1957
  -3.500  -0.0766   0.03221   0.02168  -0.0867   0.8568   0.2040
  -3.250  -0.0485   0.03168   0.02097  -0.0870   0.8499   0.2135
  -3.000  -0.0120   0.03121   0.02034  -0.0885   0.8455   0.2270
  -2.750   0.0070   0.03112   0.02028  -0.0872   0.8365   0.2361
  -2.500   0.0407   0.03070   0.01976  -0.0882   0.8309   0.2499
  -2.250   0.0706   0.03047   0.01945  -0.0885   0.8248   0.2662
  -2.000   0.0939   0.03040   0.01933  -0.0878   0.8165   0.2827
  -1.750   0.1318   0.03008   0.01899  -0.0893   0.8119   0.3037
  -1.500   0.1507   0.03018   0.01905  -0.0879   0.8024   0.3203
  -1.250   0.1855   0.02998   0.01883  -0.0889   0.7967   0.3431
  -1.000   0.2109   0.02999   0.01882  -0.0884   0.7886   0.3631
  -0.750   0.2409   0.02990   0.01871  -0.0886   0.7811   0.3864
  -0.500   0.2757   0.02966   0.01852  -0.0894   0.7751   0.4142
  -0.250   0.2968   0.02972   0.01862  -0.0882   0.7650   0.4396
   0.000   0.3388   0.02915   0.01809  -0.0899   0.7602   0.4725
   0.250   0.3559   0.02921   0.01824  -0.0881   0.7482   0.4940
   0.500   0.3902   0.02869   0.01784  -0.0886   0.7407   0.5267
   0.750   0.4155   0.02833   0.01772  -0.0877   0.7304   0.5654
   1.000   0.4397   0.02775   0.01763  -0.0862   0.7205   0.6457
   1.250   0.5032   0.02664   0.01693  -0.0912   0.7120   1.0000
   1.500   0.5255   0.02681   0.01690  -0.0901   0.6996   1.0000
   1.750   0.5590   0.02660   0.01648  -0.0903   0.6898   1.0000
   2.250   0.6093   0.02666   0.01627  -0.0883   0.6654   1.0000
   2.500   0.6364   0.02662   0.01610  -0.0876   0.6537   1.0000
   2.750   0.6703   0.02633   0.01569  -0.0878   0.6432   1.0000
   3.000   0.6896   0.02656   0.01584  -0.0860   0.6291   1.0000
   3.250   0.7112   0.02671   0.01593  -0.0846   0.6153   1.0000
   3.500   0.7351   0.02679   0.01593  -0.0834   0.6019   1.0000
   3.750   0.7608   0.02679   0.01585  -0.0825   0.5884   1.0000
   4.000   0.7873   0.02677   0.01575  -0.0816   0.5746   1.0000
   4.250   0.8091   0.02692   0.01585  -0.0802   0.5594   1.0000
   4.500   0.8291   0.02716   0.01603  -0.0786   0.5435   1.0000
   4.750   0.8495   0.02740   0.01622  -0.0770   0.5274   1.0000
   5.000   0.8701   0.02767   0.01642  -0.0755   0.5114   1.0000
   5.250   0.8908   0.02796   0.01665  -0.0741   0.4955   1.0000
   5.500   0.9114   0.02830   0.01691  -0.0726   0.4797   1.0000
   5.750   0.9318   0.02870   0.01724  -0.0712   0.4647   1.0000
   6.000   0.9520   0.02915   0.01761  -0.0699   0.4504   1.0000
   6.250   0.9731   0.02963   0.01803  -0.0687   0.4374   1.0000
   6.500   0.9972   0.03008   0.01836  -0.0679   0.4259   1.0000
   6.750   1.0163   0.03073   0.01899  -0.0666   0.4142   1.0000
   7.000   1.0353   0.03145   0.01969  -0.0653   0.4035   1.0000
   7.250   1.0622   0.03194   0.02008  -0.0651   0.3943   1.0000
   7.500   1.0766   0.03288   0.02109  -0.0633   0.3847   1.0000
   7.750   1.1048   0.03346   0.02161  -0.0634   0.3772   1.0000
   8.000   1.1186   0.03450   0.02277  -0.0617   0.3693   1.0000
   8.250   1.1465   0.03512   0.02335  -0.0617   0.3626   1.0000
   8.500   1.1595   0.03624   0.02459  -0.0599   0.3557   1.0000
   8.750   1.1791   0.03714   0.02556  -0.0590   0.3493   1.0000
   9.000   1.2057   0.03792   0.02635  -0.0590   0.3438   1.0000
   9.250   1.2127   0.03932   0.02792  -0.0566   0.3380   1.0000
   9.500   1.2323   0.04022   0.02888  -0.0557   0.3321   1.0000
   9.750   1.2500   0.04122   0.02994  -0.0547   0.3263   1.0000
  10.000   1.2521   0.04278   0.03170  -0.0520   0.3202   1.0000
  10.250   1.2757   0.04341   0.03233  -0.0514   0.3140   1.0000
  10.500   1.2768   0.04507   0.03415  -0.0489   0.3084   1.0000
  10.750   1.2781   0.04669   0.03592  -0.0465   0.3021   1.0000
  11.000   1.3040   0.04702   0.03621  -0.0460   0.2953   1.0000
  11.250   1.2857   0.04983   0.03930  -0.0425   0.2899   1.0000
  11.500   1.2945   0.05102   0.04055  -0.0410   0.2831   1.0000
  11.750   1.2996   0.05255   0.04216  -0.0393   0.2771   1.0000
  12.000   1.2782   0.05614   0.04600  -0.0369   0.2715   1.0000
  12.250   1.3138   0.05507   0.04479  -0.0364   0.2633   1.0000
  12.500   1.2709   0.06083   0.05090  -0.0342   0.2585   1.0000
  12.750   1.2524   0.06491   0.05515  -0.0332   0.2523   1.0000
  13.000   1.2752   0.06469   0.05492  -0.0322   0.2454   1.0000
  13.250   1.1901   0.07763   0.06820  -0.0340   0.2402   1.0000
  13.500   1.1948   0.07969   0.07034  -0.0336   0.2337   1.0000
  13.750   1.0770   0.10193   0.09275  -0.0421   0.2221   1.0000
  14.000   1.1016   0.10075   0.09167  -0.0405   0.2173   1.0000
  14.250   1.1619   0.09358   0.08455  -0.0361   0.2147   1.0000
  14.500   1.0728   0.11287   0.10395  -0.0446   0.2007   1.0000
  15.000   1.0624   0.12186   0.11309  -0.0476   0.1846   1.0000
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