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GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 428 AIRFOIL (goe428-il)
Reynolds number: 1,000,000
Max Cl/Cd: 124.98 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe428-il-1000000.txt
Download as CSV file: xf-goe428-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 428 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2993   0.09603   0.09450  -0.0277   1.0000   0.0092
  -8.250  -0.3036   0.09313   0.09164  -0.0284   1.0000   0.0097
  -8.000  -0.3023   0.09051   0.08904  -0.0287   0.9997   0.0098
  -7.750  -0.2832   0.08575   0.08428  -0.0350   0.9970   0.0098
  -7.500  -0.2652   0.08137   0.07991  -0.0407   0.9922   0.0098
  -7.250  -0.2492   0.07560   0.07414  -0.0470   0.9863   0.0102
  -7.000  -0.2258   0.07248   0.07101  -0.0518   0.9808   0.0106
  -6.750  -0.2009   0.06860   0.06712  -0.0582   0.9723   0.0110
  -6.500  -0.1687   0.06407   0.06255  -0.0669   0.9624   0.0117
  -6.250  -0.1190   0.05732   0.05571  -0.0817   0.9480   0.0135
  -6.000  -0.0797   0.05175   0.05001  -0.0916   0.9194   0.0136
  -5.750  -0.0561   0.04719   0.04523  -0.0965   0.8805   0.0137
  -5.500  -0.0673   0.01489   0.01111  -0.1075   0.8541   0.0103
  -5.250  -0.0440   0.01357   0.00947  -0.1069   0.8361   0.0107
  -5.000  -0.0187   0.01300   0.00871  -0.1065   0.8236   0.0112
  -4.750   0.0065   0.01213   0.00760  -0.1060   0.8127   0.0117
  -4.500   0.0320   0.01132   0.00656  -0.1055   0.8019   0.0124
  -4.250   0.0585   0.01097   0.00607  -0.1051   0.7911   0.0133
  -4.000   0.0836   0.00988   0.00472  -0.1045   0.7809   0.0145
  -3.750   0.1101   0.00964   0.00441  -0.1042   0.7703   0.0155
  -3.500   0.1370   0.00946   0.00415  -0.1039   0.7594   0.0167
  -3.250   0.1638   0.00922   0.00382  -0.1035   0.7482   0.0180
  -3.000   0.1910   0.00922   0.00375  -0.1032   0.7363   0.0189
  -2.750   0.2165   0.00856   0.00299  -0.1027   0.7236   0.0217
  -2.500   0.2433   0.00846   0.00282  -0.1024   0.7095   0.0238
  -2.250   0.2700   0.00837   0.00266  -0.1020   0.6955   0.0255
  -2.000   0.2963   0.00811   0.00229  -0.1016   0.6823   0.0273
  -1.750   0.3224   0.00781   0.00191  -0.1012   0.6696   0.0309
  -1.500   0.3490   0.00770   0.00172  -0.1008   0.6573   0.0331
  -1.250   0.3758   0.00763   0.00158  -0.1005   0.6454   0.0352
  -1.000   0.4027   0.00758   0.00148  -0.1003   0.6341   0.0365
  -0.750   0.4294   0.00743   0.00124  -0.0999   0.6230   0.0402
  -0.500   0.4562   0.00737   0.00113  -0.0996   0.6116   0.0451
  -0.250   0.4829   0.00735   0.00106  -0.0993   0.5998   0.0520
   0.000   0.5093   0.00720   0.00108  -0.0990   0.5880   0.1223
   0.250   0.5362   0.00721   0.00108  -0.0987   0.5747   0.1400
   0.500   0.5626   0.00726   0.00108  -0.0984   0.5561   0.1543
   0.750   0.5886   0.00732   0.00109  -0.0980   0.5317   0.1695
   1.000   0.6143   0.00730   0.00112  -0.0977   0.5085   0.2276
   1.250   0.6368   0.00681   0.00127  -0.0970   0.4859   0.5386
   1.500   0.6778   0.00602   0.00140  -0.1001   0.4592   1.0000
   1.750   0.7030   0.00620   0.00146  -0.0996   0.4386   1.0000
   2.000   0.7282   0.00640   0.00154  -0.0990   0.4189   1.0000
   2.250   0.7533   0.00660   0.00164  -0.0985   0.4013   1.0000
   2.500   0.7788   0.00678   0.00172  -0.0980   0.3867   1.0000
   2.750   0.8047   0.00693   0.00181  -0.0977   0.3755   1.0000
   3.000   0.8307   0.00707   0.00191  -0.0973   0.3669   1.0000
   3.500   0.8827   0.00735   0.00212  -0.0966   0.3521   1.0000
   4.000   0.9346   0.00763   0.00236  -0.0959   0.3392   1.0000
   4.250   0.9604   0.00778   0.00250  -0.0955   0.3329   1.0000
   4.500   0.9862   0.00793   0.00263  -0.0952   0.3235   1.0000
   4.750   1.0116   0.00812   0.00277  -0.0948   0.3134   1.0000
   5.000   1.0368   0.00832   0.00293  -0.0943   0.3014   1.0000
   5.250   1.0623   0.00850   0.00309  -0.0939   0.2901   1.0000
   5.500   1.0869   0.00875   0.00326  -0.0934   0.2717   1.0000
   5.750   1.1105   0.00908   0.00348  -0.0928   0.2450   1.0000
   6.000   1.1258   0.01018   0.00410  -0.0909   0.1597   1.0000
   6.250   1.1400   0.01141   0.00489  -0.0888   0.0833   1.0000
   6.500   1.1566   0.01243   0.00563  -0.0870   0.0280   1.0000
   6.750   1.1777   0.01300   0.00620  -0.0859   0.0172   1.0000
   7.000   1.2002   0.01340   0.00666  -0.0850   0.0152   1.0000
   7.250   1.2224   0.01382   0.00712  -0.0841   0.0138   1.0000
   7.500   1.2430   0.01437   0.00771  -0.0830   0.0120   1.0000
   7.750   1.2608   0.01515   0.00861  -0.0813   0.0107   1.0000
   8.000   1.2819   0.01559   0.00909  -0.0802   0.0102   1.0000
   8.250   1.3011   0.01616   0.00972  -0.0789   0.0096   1.0000
   8.500   1.3193   0.01678   0.01039  -0.0774   0.0090   1.0000
   8.750   1.3367   0.01741   0.01107  -0.0758   0.0085   1.0000
   9.000   1.3523   0.01812   0.01185  -0.0740   0.0080   1.0000
   9.250   1.3543   0.01957   0.01342  -0.0699   0.0074   1.0000
   9.500   1.3546   0.02079   0.01475  -0.0655   0.0071   1.0000
   9.750   1.3702   0.02123   0.01524  -0.0637   0.0069   1.0000
  10.000   1.3778   0.02214   0.01622  -0.0608   0.0066   1.0000
  10.250   1.3835   0.02320   0.01736  -0.0579   0.0064   1.0000
  10.500   1.3902   0.02426   0.01850  -0.0553   0.0062   1.0000
  10.750   1.3914   0.02577   0.02011  -0.0523   0.0060   1.0000
  11.000   1.3939   0.02732   0.02176  -0.0498   0.0059   1.0000
  11.250   1.3982   0.02884   0.02335  -0.0477   0.0058   1.0000
  11.500   1.4029   0.03042   0.02502  -0.0460   0.0056   1.0000
  11.750   1.4049   0.03236   0.02705  -0.0443   0.0055   1.0000
  12.000   1.4073   0.03438   0.02915  -0.0428   0.0054   1.0000
  12.250   1.4156   0.03581   0.03061  -0.0422   0.0051   1.0000
  12.500   1.4141   0.03841   0.03332  -0.0408   0.0051   1.0000
  12.750   1.4124   0.04113   0.03612  -0.0397   0.0049   1.0000
  13.000   1.4083   0.04429   0.03939  -0.0384   0.0048   1.0000
  13.250   1.4000   0.04863   0.04393  -0.0364   0.0046   1.0000
  13.500   1.4008   0.05118   0.04662  -0.0363   0.0045   1.0000
  13.750   1.4001   0.05425   0.04982  -0.0360   0.0045   1.0000
  14.000   1.3987   0.05737   0.05308  -0.0362   0.0043   1.0000
  14.250   1.3976   0.06054   0.05638  -0.0365   0.0043   1.0000
  14.500   1.3925   0.06453   0.06053  -0.0369   0.0042   1.0000
  14.750   1.3877   0.06853   0.06468  -0.0377   0.0041   1.0000
  15.000   1.3806   0.07306   0.06937  -0.0387   0.0040   1.0000
  15.250   1.3707   0.07826   0.07474  -0.0400   0.0040   1.0000
  15.500   1.3576   0.08420   0.08087  -0.0418   0.0039   1.0000
  15.750   1.3448   0.09032   0.08716  -0.0442   0.0040   1.0000
  16.000   1.3304   0.09699   0.09401  -0.0471   0.0040   1.0000
  16.250   1.3162   0.10384   0.10101  -0.0504   0.0039   1.0000
  16.500   1.2994   0.11152   0.10888  -0.0543   0.0040   1.0000
  16.750   1.2827   0.11947   0.11699  -0.0586   0.0040   1.0000
  17.000   1.2645   0.12806   0.12573  -0.0635   0.0040   1.0000
  17.250   1.2466   0.13688   0.13471  -0.0687   0.0041   1.0000
  17.500   1.2330   0.14498   0.14293  -0.0737   0.0041   1.0000
  17.750   1.2142   0.15481   0.15290  -0.0798   0.0041   1.0000
  18.000   1.1963   0.16489   0.16311  -0.0863   0.0042   1.0000
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