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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 1,000,000
Max Cl/Cd: 134.25 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe456-il-1000000-n5.txt
Download as CSV file: xf-goe456-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 456 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3209   0.12966   0.12799  -0.0326   1.0000   0.0023
 -11.000  -0.3182   0.12639   0.12474  -0.0328   1.0000   0.0023
 -10.750  -0.3144   0.12402   0.12238  -0.0328   1.0000   0.0026
 -10.500  -0.3093   0.12108   0.11945  -0.0336   0.9999   0.0026
 -10.250  -0.2971   0.11725   0.11562  -0.0365   0.9990   0.0026
 -10.000  -0.2847   0.11315   0.11152  -0.0397   0.9973   0.0025
  -9.750  -0.2739   0.10987   0.10825  -0.0420   0.9931   0.0027
  -9.500  -0.2625   0.10628   0.10466  -0.0447   0.9892   0.0029
  -9.250  -0.2514   0.10270   0.10108  -0.0474   0.9836   0.0028
  -9.000  -0.2383   0.09893   0.09731  -0.0506   0.9788   0.0028
  -8.750  -0.2247   0.09522   0.09360  -0.0540   0.9727   0.0030
  -8.500  -0.2077   0.09119   0.08956  -0.0585   0.9678   0.0033
  -8.250  -0.1887   0.08702   0.08538  -0.0637   0.9614   0.0030
  -8.000  -0.1626   0.08188   0.08022  -0.0714   0.9559   0.0039
  -7.750  -0.1366   0.07691   0.07522  -0.0792   0.9455   0.0040
  -7.500  -0.1135   0.07214   0.07040  -0.0862   0.9301   0.0040
  -7.250  -0.1018   0.06870   0.06688  -0.0896   0.9098   0.0040
  -7.000  -0.0952   0.06619   0.06429  -0.0913   0.8926   0.0032
  -5.500  -0.0077   0.04286   0.04058  -0.1140   0.8246   0.0038
  -5.250   0.0160   0.03766   0.03524  -0.1190   0.8168   0.0035
  -5.000   0.0425   0.03148   0.02888  -0.1237   0.8088   0.0033
  -4.750   0.0686   0.02182   0.01871  -0.1279   0.8020   0.0030
  -4.500   0.0908   0.01460   0.01057  -0.1281   0.7944   0.0027
  -4.250   0.1152   0.01174   0.00714  -0.1275   0.7869   0.0028
  -4.000   0.1409   0.01045   0.00553  -0.1271   0.7784   0.0029
  -3.750   0.1671   0.00961   0.00447  -0.1267   0.7703   0.0031
  -3.500   0.1934   0.00900   0.00367  -0.1264   0.7615   0.0035
  -3.250   0.2201   0.00861   0.00313  -0.1261   0.7514   0.0039
  -3.000   0.2465   0.00814   0.00251  -0.1257   0.7402   0.0043
  -2.750   0.2730   0.00795   0.00226  -0.1255   0.7279   0.0052
  -2.500   0.2995   0.00775   0.00195  -0.1252   0.7147   0.0061
  -2.250   0.3260   0.00759   0.00167  -0.1249   0.7013   0.0068
  -2.000   0.3525   0.00738   0.00134  -0.1245   0.6876   0.0096
  -1.750   0.3789   0.00732   0.00118  -0.1242   0.6737   0.0130
  -1.500   0.4053   0.00722   0.00105  -0.1239   0.6605   0.0283
  -1.000   0.4578   0.00692   0.00092  -0.1235   0.6380   0.1310
  -0.750   0.4844   0.00694   0.00090  -0.1233   0.6262   0.1454
  -0.500   0.5107   0.00700   0.00089  -0.1230   0.6113   0.1540
  -0.250   0.5370   0.00705   0.00088  -0.1227   0.5968   0.1606
   0.000   0.5636   0.00710   0.00088  -0.1225   0.5856   0.1694
   0.250   0.5901   0.00714   0.00089  -0.1223   0.5760   0.1782
   0.500   0.6171   0.00715   0.00090  -0.1222   0.5671   0.1889
   0.750   0.6438   0.00718   0.00093  -0.1220   0.5589   0.2043
   1.000   0.6703   0.00721   0.00098  -0.1218   0.5492   0.2259
   1.250   0.6966   0.00724   0.00103  -0.1216   0.5368   0.2540
   1.500   0.7228   0.00728   0.00110  -0.1214   0.5235   0.2868
   1.750   0.7490   0.00731   0.00117  -0.1212   0.5122   0.3211
   2.000   0.7752   0.00731   0.00126  -0.1210   0.5039   0.3662
   2.250   0.7993   0.00687   0.00143  -0.1206   0.4961   0.6395
   2.750   0.8592   0.00640   0.00166  -0.1218   0.4770   1.0000
   3.000   0.8842   0.00659   0.00178  -0.1213   0.4539   1.0000
   3.250   0.9041   0.00720   0.00203  -0.1200   0.3786   1.0000
   3.500   0.9186   0.00831   0.00254  -0.1178   0.2597   1.0000
   3.750   0.9386   0.00897   0.00292  -0.1166   0.2000   1.0000
   4.000   0.9588   0.00961   0.00327  -0.1154   0.1452   1.0000
   4.250   0.9711   0.01099   0.00409  -0.1128   0.0138   1.0000
   4.500   0.9952   0.01126   0.00438  -0.1122   0.0087   1.0000
   4.750   1.0190   0.01157   0.00473  -0.1115   0.0064   1.0000
   5.000   1.0425   0.01189   0.00507  -0.1108   0.0051   1.0000
   5.250   1.0649   0.01230   0.00552  -0.1098   0.0041   1.0000
   5.500   1.0878   0.01265   0.00591  -0.1090   0.0034   1.0000
   5.750   1.1100   0.01306   0.00634  -0.1081   0.0030   1.0000
   6.000   1.1296   0.01370   0.00707  -0.1067   0.0025   1.0000
   6.250   1.1499   0.01426   0.00771  -0.1054   0.0024   1.0000
   6.500   1.1685   0.01495   0.00849  -0.1037   0.0021   1.0000
   6.750   1.1847   0.01580   0.00944  -0.1017   0.0020   1.0000
   7.000   1.1988   0.01676   0.01051  -0.0993   0.0019   1.0000
   7.250   1.2153   0.01749   0.01130  -0.0975   0.0017   1.0000
   7.500   1.2291   0.01837   0.01227  -0.0952   0.0016   1.0000
   7.750   1.2480   0.01873   0.01264  -0.0939   0.0015   1.0000
   8.000   1.2548   0.01990   0.01394  -0.0904   0.0014   1.0000
   8.250   1.2591   0.02151   0.01568  -0.0865   0.0013   1.0000
   8.500   1.2693   0.02293   0.01722  -0.0837   0.0013   1.0000
   8.750   1.2876   0.02565   0.02011  -0.0821   0.0010   1.0000
   9.000   1.3294   0.03065   0.02538  -0.0842   0.0009   1.0000
   9.250   1.3496   0.03436   0.02937  -0.0827   0.0008   1.0000
   9.500   1.3624   0.03799   0.03329  -0.0803   0.0008   1.0000
   9.750   1.3685   0.04170   0.03729  -0.0770   0.0008   1.0000
  10.000   1.3695   0.04516   0.04102  -0.0733   0.0008   1.0000
  10.250   1.3652   0.04837   0.04448  -0.0691   0.0009   1.0000
  10.500   1.3547   0.05110   0.04741  -0.0642   0.0009   1.0000
  10.750   1.3414   0.05390   0.05041  -0.0596   0.0009   1.0000
  11.000   1.3273   0.05680   0.05349  -0.0558   0.0009   1.0000
  11.250   1.3109   0.06016   0.05704  -0.0526   0.0009   1.0000
  11.500   1.2944   0.06376   0.06080  -0.0501   0.0010   1.0000
  11.750   1.2767   0.06773   0.06494  -0.0485   0.0010   1.0000
  12.000   1.2589   0.07202   0.06938  -0.0476   0.0010   1.0000
  12.250   1.2397   0.07682   0.07434  -0.0477   0.0010   1.0000
  12.500   1.2206   0.08202   0.07968  -0.0485   0.0010   1.0000
  12.750   1.2012   0.08775   0.08555  -0.0503   0.0010   1.0000
  13.000   1.1818   0.09404   0.09197  -0.0529   0.0010   1.0000
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