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GOE 379 AIRFOIL (goe379-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 379 AIRFOIL (goe379-il)
Reynolds number: 50,000
Max Cl/Cd: 39.58 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe379-il-50000.txt
Download as CSV file: xf-goe379-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 379 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3338   0.11978   0.11296  -0.0224   1.0000   0.0892
  -9.000  -0.3371   0.11932   0.11260  -0.0243   1.0000   0.0901
  -8.750  -0.3443   0.11949   0.11292  -0.0261   1.0000   0.0905
  -8.500  -0.3182   0.11003   0.10335  -0.0236   1.0000   0.0948
  -8.250  -0.3142   0.10732   0.10071  -0.0237   1.0000   0.0992
  -8.000  -0.3156   0.10581   0.09930  -0.0245   1.0000   0.1020
  -7.750  -0.3226   0.10527   0.09890  -0.0252   1.0000   0.1033
  -7.500  -0.3303   0.10528   0.09906  -0.0274   1.0000   0.1040
  -7.250  -0.3139   0.09804   0.09184  -0.0237   1.0000   0.1087
  -7.000  -0.3125   0.09565   0.08955  -0.0234   1.0000   0.1123
  -6.750  -0.3144   0.09417   0.08818  -0.0245   1.0000   0.1156
  -6.500  -0.3184   0.09423   0.08834  -0.0279   1.0000   0.1174
  -6.250  -0.3140   0.08973   0.08394  -0.0255   1.0000   0.1195
  -6.000  -0.3105   0.08636   0.08064  -0.0232   1.0000   0.1239
  -5.750  -0.3105   0.08458   0.07893  -0.0235   1.0000   0.1285
  -5.500  -0.3091   0.08531   0.07964  -0.0286   1.0000   0.1315
  -5.250  -0.3091   0.07998   0.07446  -0.0230   1.0000   0.1346
  -5.000  -0.3072   0.07755   0.07209  -0.0216   1.0000   0.1401
  -4.750  -0.2999   0.07662   0.07110  -0.0255   1.0000   0.1460
  -4.500  -0.3000   0.07280   0.06739  -0.0215   1.0000   0.1508
  -4.000  -0.2873   0.06790   0.06250  -0.0215   1.0000   0.1666
  -3.750  -0.2771   0.06554   0.06006  -0.0226   1.0000   0.1764
  -3.500  -0.2660   0.06320   0.05768  -0.0235   1.0000   0.1890
  -3.250  -0.2560   0.06063   0.05509  -0.0234   1.0000   0.2030
  -3.000  -0.2478   0.05793   0.05241  -0.0223   1.0000   0.2205
  -2.750  -0.2372   0.05558   0.05003  -0.0222   1.0000   0.2457
  -2.500  -0.2294   0.05330   0.04775  -0.0212   1.0000   0.2855
  -2.250  -0.2261   0.05063   0.04519  -0.0181   1.0000   0.3297
  -2.000  -0.2251   0.04816   0.04283  -0.0143   1.0000   0.3858
  -1.750  -0.2239   0.04550   0.04028  -0.0100   1.0000   0.4425
  -1.500  -0.2173   0.04315   0.03797  -0.0072   1.0000   0.4942
  -1.250  -0.2087   0.04070   0.03554  -0.0045   1.0000   0.5333
  -1.000  -0.1821   0.03815   0.03296  -0.0057   0.9955   0.5683
  -0.750  -0.1048   0.03588   0.03027  -0.0185   0.9814   0.5669
  -0.500   0.0701   0.03700   0.02861  -0.0494   0.9623   0.1955
  -0.250   0.1271   0.03553   0.02623  -0.0535   0.9480   0.1730
   0.000   0.1782   0.03381   0.02400  -0.0574   0.9339   0.1754
   0.250   0.2263   0.03261   0.02243  -0.0609   0.9189   0.1951
   0.500   0.2885   0.03153   0.02080  -0.0665   0.9046   0.2185
   0.750   0.3442   0.03062   0.01974  -0.0712   0.8901   0.2490
   1.000   0.3929   0.02977   0.01905  -0.0748   0.8753   0.3067
   1.250   0.4701   0.02791   0.01810  -0.0831   0.8617   1.0000
   1.500   0.5179   0.02814   0.01792  -0.0863   0.8460   1.0000
   1.750   0.5644   0.02825   0.01777  -0.0891   0.8306   1.0000
   2.000   0.5921   0.02874   0.01812  -0.0891   0.8125   1.0000
   2.250   0.6256   0.02903   0.01831  -0.0897   0.7957   1.0000
   2.500   0.6595   0.02927   0.01848  -0.0902   0.7798   1.0000
   2.750   0.6923   0.02950   0.01868  -0.0904   0.7644   1.0000
   3.000   0.7242   0.02971   0.01885  -0.0903   0.7492   1.0000
   3.250   0.7543   0.02998   0.01910  -0.0900   0.7344   1.0000
   3.500   0.7828   0.03030   0.01943  -0.0894   0.7198   1.0000
   3.750   0.8099   0.03067   0.01987  -0.0887   0.7053   1.0000
   4.000   0.8300   0.03148   0.02072  -0.0874   0.6899   1.0000
   4.250   0.8519   0.03218   0.02148  -0.0862   0.6752   1.0000
   4.500   0.8751   0.03285   0.02221  -0.0851   0.6614   1.0000
   4.750   0.8976   0.03350   0.02294  -0.0839   0.6472   1.0000
   5.000   0.9196   0.03415   0.02376  -0.0825   0.6327   1.0000
   5.250   0.9417   0.03474   0.02446  -0.0811   0.6180   1.0000
   5.500   0.9639   0.03536   0.02521  -0.0797   0.6037   1.0000
   5.750   0.9859   0.03607   0.02605  -0.0784   0.5901   1.0000
   6.000   1.0079   0.03684   0.02698  -0.0771   0.5769   1.0000
   6.250   1.0303   0.03765   0.02804  -0.0759   0.5642   1.0000
   6.500   1.0548   0.03832   0.02890  -0.0747   0.5518   1.0000
   6.750   1.0762   0.03929   0.03010  -0.0734   0.5393   1.0000
   7.000   1.0873   0.04123   0.03228  -0.0718   0.5265   1.0000
   7.250   1.0971   0.04331   0.03461  -0.0701   0.5137   1.0000
   7.500   1.1314   0.04222   0.03379  -0.0681   0.4952   1.0000
   7.750   1.1897   0.03410   0.02564  -0.0627   0.4400   1.0000
   8.000   1.2030   0.03150   0.02307  -0.0572   0.3935   1.0000
   8.250   1.2008   0.03034   0.02183  -0.0509   0.3385   1.0000
   8.500   1.1911   0.03089   0.02221  -0.0448   0.2643   1.0000
   8.750   1.1772   0.03318   0.02369  -0.0396   0.1630   1.0000
   9.000   1.1656   0.03608   0.02609  -0.0354   0.1204   1.0000
   9.250   1.1555   0.03900   0.02873  -0.0319   0.1043   1.0000
   9.500   1.1506   0.04167   0.03137  -0.0292   0.0963   1.0000
   9.750   1.1443   0.04462   0.03424  -0.0269   0.0910   1.0000
  10.000   1.1435   0.04735   0.03707  -0.0248   0.0848   1.0000
  10.250   1.1443   0.05011   0.03973  -0.0228   0.0797   1.0000
  10.500   1.1578   0.05222   0.04214  -0.0206   0.0737   1.0000
  10.750   1.2694   0.05630   0.04620  -0.0226   0.0671   1.0000
  11.000   1.2984   0.06100   0.05134  -0.0225   0.0671   1.0000
  11.250   1.3086   0.06535   0.05610  -0.0211   0.0671   1.0000
  11.500   1.3080   0.06934   0.06047  -0.0190   0.0671   1.0000
  11.750   1.3002   0.07297   0.06447  -0.0164   0.0672   1.0000
  12.000   1.2873   0.07661   0.06840  -0.0140   0.0672   1.0000
  12.250   1.2684   0.07967   0.07177  -0.0120   0.0676   1.0000
  12.500   1.2305   0.08279   0.07532  -0.0112   0.0694   1.0000
  12.750   1.1952   0.08836   0.08122  -0.0129   0.0707   1.0000
  13.000   1.1620   0.09521   0.08832  -0.0162   0.0722   1.0000
  13.250   1.1304   0.10309   0.09638  -0.0208   0.0733   1.0000
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