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GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: GOE 493 AIRFOIL (goe493-il)
Reynolds number: 50,000
Max Cl/Cd: 24.25 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe493-il-50000.txt
Download as CSV file: xf-goe493-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 493 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  -0.3847   0.11344   0.10662  -0.0246   1.0000   0.3413
  -9.000  -0.3653   0.10923   0.10237  -0.0229   1.0000   0.3532
  -8.750  -0.4014   0.10919   0.10249  -0.0202   1.0000   0.3578
  -8.500  -0.6697   0.07418   0.06789  -0.0452   1.0000   0.1517
  -8.250  -0.6807   0.07023   0.06390  -0.0435   1.0000   0.1526
  -8.000  -0.6902   0.06639   0.05997  -0.0420   1.0000   0.1539
  -7.750  -0.6972   0.06270   0.05615  -0.0405   1.0000   0.1561
  -7.500  -0.7044   0.05861   0.05181  -0.0393   1.0000   0.1591
  -7.250  -0.7114   0.05384   0.04656  -0.0386   1.0000   0.1629
  -7.000  -0.7118   0.04939   0.04153  -0.0377   1.0000   0.1680
  -6.750  -0.6993   0.04780   0.03991  -0.0361   1.0000   0.1781
  -6.500  -0.6883   0.04551   0.03746  -0.0348   1.0000   0.1882
  -6.250  -0.6775   0.04292   0.03444  -0.0338   1.0000   0.2002
  -6.000  -0.6639   0.04105   0.03225  -0.0326   1.0000   0.2142
  -5.750  -0.6488   0.03963   0.03063  -0.0313   1.0000   0.2290
  -5.500  -0.6330   0.03841   0.02932  -0.0300   1.0000   0.2446
  -5.250  -0.6168   0.03734   0.02815  -0.0287   1.0000   0.2608
  -5.000  -0.6002   0.03637   0.02708  -0.0275   1.0000   0.2770
  -4.750  -0.5832   0.03552   0.02613  -0.0264   1.0000   0.2933
  -4.500  -0.5659   0.03478   0.02537  -0.0252   1.0000   0.3101
  -4.250  -0.5486   0.03415   0.02473  -0.0240   1.0000   0.3274
  -4.000  -0.5313   0.03366   0.02428  -0.0227   1.0000   0.3460
  -3.750  -0.5139   0.03321   0.02385  -0.0214   1.0000   0.3661
  -3.500  -0.4961   0.03277   0.02329  -0.0203   1.0000   0.3907
  -3.250  -0.4796   0.03258   0.02327  -0.0187   1.0000   0.4155
  -3.000  -0.4624   0.03238   0.02314  -0.0173   1.0000   0.4457
  -2.750  -0.4459   0.03231   0.02317  -0.0156   1.0000   0.4803
  -2.500  -0.4306   0.03227   0.02320  -0.0136   1.0000   0.5193
  -2.250  -0.4166   0.03228   0.02333  -0.0113   1.0000   0.5598
  -2.000  -0.4033   0.03231   0.02348  -0.0086   1.0000   0.6013
  -1.750  -0.3899   0.03240   0.02365  -0.0060   1.0000   0.6434
  -1.500  -0.3772   0.03253   0.02387  -0.0031   1.0000   0.6843
  -1.250  -0.3650   0.03266   0.02404  -0.0002   1.0000   0.7266
  -1.000  -0.3536   0.03275   0.02421   0.0030   1.0000   0.7695
  -0.750  -0.3415   0.03278   0.02433   0.0060   1.0000   0.8172
  -0.500  -0.3204   0.03289   0.02458   0.0072   1.0000   0.8779
  -0.250  -0.2390   0.03425   0.02596  -0.0049   1.0000   0.9669
   0.000  -0.2134   0.03411   0.02555  -0.0095   1.0000   1.0000
   0.250  -0.1973   0.03421   0.02536  -0.0109   1.0000   1.0000
   0.500  -0.1779   0.03474   0.02561  -0.0122   1.0000   1.0000
   0.750  -0.1585   0.03542   0.02605  -0.0131   1.0000   1.0000
   1.000  -0.1397   0.03619   0.02660  -0.0137   1.0000   1.0000
   1.250  -0.1214   0.03703   0.02725  -0.0141   1.0000   1.0000
   1.500  -0.1034   0.03793   0.02798  -0.0145   1.0000   1.0000
   1.750  -0.0858   0.03887   0.02878  -0.0147   1.0000   1.0000
   2.000  -0.0685   0.03987   0.02964  -0.0149   1.0000   1.0000
   2.250  -0.0509   0.04094   0.03061  -0.0153   0.9997   1.0000
   2.500  -0.0065   0.04371   0.03324  -0.0207   0.9862   1.0000
   2.750   0.1658   0.04807   0.03736  -0.0438   0.8573   1.0000
   3.000   0.1982   0.04929   0.03850  -0.0456   0.8434   1.0000
   3.250   0.2322   0.05050   0.03965  -0.0475   0.8292   1.0000
   3.500   0.2519   0.05151   0.04064  -0.0475   0.8172   1.0000
   3.750   0.2723   0.05259   0.04169  -0.0476   0.8042   1.0000
   4.000   0.2961   0.05378   0.04286  -0.0481   0.7914   1.0000
   4.250   0.3240   0.05502   0.04409  -0.0492   0.7789   1.0000
   4.500   0.3616   0.05632   0.04539  -0.0513   0.7668   1.0000
   4.750   0.3678   0.05756   0.04665  -0.0498   0.7554   1.0000
   5.000   0.3848   0.05895   0.04806  -0.0497   0.7441   1.0000
   5.250   0.4131   0.06032   0.04945  -0.0507   0.7328   1.0000
   5.500   0.4296   0.06182   0.05098  -0.0506   0.7229   1.0000
   5.750   0.4402   0.06350   0.05269  -0.0500   0.7134   1.0000
   6.000   0.4760   0.06492   0.05417  -0.0516   0.7034   1.0000
   6.250   0.4695   0.06700   0.05628  -0.0498   0.6964   1.0000
   6.500   0.5054   0.06861   0.05797  -0.0515   0.6878   1.0000
   6.750   0.4956   0.07093   0.06032  -0.0496   0.6827   1.0000
   7.000   0.5033   0.07317   0.06263  -0.0494   0.6785   1.0000
   7.250   0.5298   0.07517   0.06471  -0.0504   0.6711   1.0000
   7.500   0.5289   0.07779   0.06739  -0.0498   0.6699   1.0000
   7.750   0.5351   0.08060   0.07027  -0.0500   0.6707   1.0000
   8.000   0.5461   0.08357   0.07332  -0.0506   0.6721   1.0000
   8.250   0.5635   0.08500   0.07486  -0.0503   0.6557   1.0000
   8.500   0.6090   0.08498   0.07498  -0.0506   0.6248   1.0000
   8.750   0.5940   0.08751   0.07756  -0.0489   0.6181   1.0000
   9.000   0.6428   0.08764   0.07787  -0.0494   0.5917   1.0000
   9.250   0.6646   0.08900   0.07938  -0.0491   0.5761   1.0000
   9.500   0.6834   0.09041   0.08092  -0.0486   0.5600   1.0000
   9.750   0.6992   0.09192   0.08259  -0.0480   0.5436   1.0000
  10.000   0.7116   0.09354   0.08436  -0.0472   0.5262   1.0000
  10.250   0.7256   0.09487   0.08584  -0.0462   0.5061   1.0000
  10.500   0.7704   0.09296   0.08420  -0.0443   0.4779   1.0000
  10.750   0.8244   0.08856   0.08013  -0.0412   0.4466   1.0000
  11.000   1.0825   0.04464   0.03631  -0.0216   0.2912   1.0000
  11.250   1.0656   0.04759   0.03863  -0.0178   0.2374   1.0000
  11.500   1.0603   0.05029   0.04075  -0.0152   0.2040   1.0000
  11.750   1.0688   0.05246   0.04258  -0.0133   0.1796   1.0000
  12.000   1.1063   0.05363   0.04348  -0.0124   0.1582   1.0000
  12.250   1.1585   0.05511   0.04490  -0.0129   0.1424   1.0000
  12.500   1.2161   0.05759   0.04736  -0.0147   0.1313   1.0000
  12.750   1.2249   0.06051   0.05069  -0.0133   0.1273   1.0000
  13.000   1.2781   0.06421   0.05428  -0.0158   0.1192   1.0000
  13.250   1.2681   0.06736   0.05783  -0.0130   0.1183   1.0000
  13.500   1.2567   0.07087   0.06170  -0.0106   0.1176   1.0000
  13.750   1.2408   0.07469   0.06586  -0.0084   0.1171   1.0000
  14.000   1.2211   0.07889   0.07038  -0.0067   0.1170   1.0000
  14.250   1.1978   0.08356   0.07533  -0.0055   0.1170   1.0000
  14.500   1.1713   0.08882   0.08084  -0.0050   0.1174   1.0000
  14.750   1.1436   0.09467   0.08691  -0.0054   0.1179   1.0000
  15.000   1.1157   0.10123   0.09366  -0.0066   0.1186   1.0000
  15.250   1.0897   0.10834   0.10092  -0.0085   0.1193   1.0000
  15.500   0.8787   0.15316   0.14574  -0.0372   0.1469   1.0000
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