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GOE 456 AIRFOIL (goe456-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 456 AIRFOIL (goe456-il)
Reynolds number: 50,000
Max Cl/Cd: 42.53 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe456-il-50000-n5.txt
Download as CSV file: xf-goe456-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.3313   0.10529   0.09940  -0.0287   1.0000   0.0939
  -7.000  -0.3465   0.10514   0.09940  -0.0279   1.0000   0.0947
  -6.750  -0.3574   0.10465   0.09903  -0.0291   1.0000   0.0952
  -6.500  -0.3531   0.10002   0.09447  -0.0255   1.0000   0.0967
  -6.250  -0.3518   0.09697   0.09148  -0.0230   1.0000   0.0987
  -6.000  -0.3537   0.09479   0.08936  -0.0217   1.0000   0.1009
  -5.750  -0.3560   0.09270   0.08734  -0.0213   1.0000   0.1035
  -5.500  -0.3486   0.09120   0.08586  -0.0292   0.9975   0.1089
  -5.250  -0.3234   0.08608   0.08072  -0.0350   0.9906   0.1104
  -4.750  -0.2553   0.07257   0.06686  -0.0506   0.9770   0.0532
  -4.500  -0.2274   0.06799   0.06220  -0.0554   0.9698   0.0500
  -4.000  -0.1354   0.05504   0.04864  -0.0761   0.9564   0.0417
  -3.750  -0.1027   0.05048   0.04386  -0.0807   0.9490   0.0410
  -3.500  -0.0615   0.04549   0.03851  -0.0867   0.9435   0.0398
  -3.250  -0.0216   0.04078   0.03328  -0.0918   0.9371   0.0389
  -3.000   0.0208   0.03643   0.02822  -0.0963   0.9316   0.0387
  -2.750   0.0636   0.03293   0.02383  -0.0998   0.9269   0.0407
  -2.500   0.0975   0.03054   0.02086  -0.1014   0.9197   0.0450
  -2.250   0.1380   0.02854   0.01830  -0.1037   0.9151   0.0491
  -2.000   0.1684   0.02722   0.01649  -0.1038   0.9069   0.0556
  -1.750   0.2097   0.02596   0.01502  -0.1062   0.9020   0.0743
  -1.500   0.2424   0.02522   0.01442  -0.1070   0.8938   0.1436
  -1.250   0.2789   0.02524   0.01455  -0.1090   0.8876   0.2843
  -1.000   0.3078   0.02499   0.01407  -0.1093   0.8784   0.3167
  -0.750   0.3475   0.02455   0.01339  -0.1114   0.8734   0.3466
  -0.500   0.3746   0.02432   0.01313  -0.1115   0.8640   0.3822
  -0.250   0.4089   0.02361   0.01279  -0.1128   0.8582   0.4759
   0.000   0.4384   0.02267   0.01248  -0.1128   0.8495   1.0000
   0.250   0.4679   0.02293   0.01237  -0.1132   0.8412   1.0000
   0.500   0.5007   0.02310   0.01225  -0.1140   0.8342   1.0000
   0.750   0.5263   0.02343   0.01237  -0.1138   0.8248   1.0000
   1.000   0.5609   0.02355   0.01228  -0.1150   0.8191   1.0000
   1.250   0.5837   0.02397   0.01257  -0.1143   0.8090   1.0000
   1.500   0.6141   0.02419   0.01267  -0.1148   0.8022   1.0000
   2.000   0.6657   0.02490   0.01327  -0.1144   0.7854   1.0000
   2.250   0.6951   0.02514   0.01348  -0.1147   0.7784   1.0000
   2.500   0.7179   0.02562   0.01400  -0.1141   0.7694   1.0000
   2.750   0.7492   0.02578   0.01418  -0.1146   0.7632   1.0000
   3.000   0.7700   0.02634   0.01479  -0.1137   0.7535   1.0000
   3.250   0.8034   0.02640   0.01493  -0.1144   0.7480   1.0000
   3.750   0.8485   0.02718   0.01598  -0.1126   0.7268   1.0000
   4.000   0.8781   0.02693   0.01586  -0.1119   0.7138   1.0000
   4.250   0.9072   0.02658   0.01572  -0.1110   0.6987   1.0000
   4.500   0.9354   0.02631   0.01563  -0.1101   0.6836   1.0000
   4.750   0.9625   0.02628   0.01582  -0.1092   0.6705   1.0000
   5.000   0.9895   0.02632   0.01612  -0.1084   0.6580   1.0000
   5.250   1.0163   0.02638   0.01654  -0.1076   0.6450   1.0000
   5.500   1.0410   0.02572   0.01608  -0.1050   0.6146   1.0000
   5.750   1.0564   0.02494   0.01522  -0.1004   0.5552   1.0000
   6.000   1.0645   0.02503   0.01517  -0.0957   0.4820   1.0000
   6.250   1.0691   0.02583   0.01523  -0.0909   0.3495   1.0000
   6.500   1.0636   0.02814   0.01648  -0.0862   0.2333   1.0000
   7.000   1.0523   0.03366   0.02057  -0.0785   0.0449   1.0000
   7.250   1.0600   0.03547   0.02254  -0.0760   0.0390   1.0000
   7.500   1.0664   0.03744   0.02467  -0.0735   0.0352   1.0000
   7.750   1.0733   0.03937   0.02685  -0.0713   0.0318   1.0000
   8.000   1.0774   0.04156   0.02924  -0.0690   0.0298   1.0000
   8.250   1.0793   0.04401   0.03189  -0.0668   0.0288   1.0000
   8.500   1.0828   0.04634   0.03443  -0.0647   0.0282   1.0000
   8.750   1.0880   0.04860   0.03693  -0.0628   0.0276   1.0000
   9.000   1.0957   0.05076   0.03932  -0.0610   0.0270   1.0000
   9.250   1.1084   0.05276   0.04157  -0.0591   0.0257   1.0000
   9.500   1.1299   0.05455   0.04359  -0.0574   0.0240   1.0000
   9.750   1.1684   0.05652   0.04590  -0.0562   0.0229   1.0000
  10.000   1.2073   0.05942   0.04917  -0.0557   0.0228   1.0000
  10.250   1.2296   0.06281   0.05298  -0.0547   0.0230   1.0000
  10.500   1.2396   0.06632   0.05691  -0.0531   0.0232   1.0000
  10.750   1.2415   0.06990   0.06088  -0.0513   0.0235   1.0000
  11.000   1.2380   0.07358   0.06492  -0.0495   0.0238   1.0000
  11.250   1.2305   0.07747   0.06916  -0.0481   0.0240   1.0000
  11.500   1.2200   0.08157   0.07357  -0.0470   0.0242   1.0000
  11.750   1.2073   0.08595   0.07825  -0.0466   0.0244   1.0000
  12.000   1.1933   0.09064   0.08321  -0.0468   0.0246   1.0000
  12.250   1.1777   0.09573   0.08854  -0.0477   0.0248   1.0000
  12.500   1.1611   0.10122   0.09426  -0.0494   0.0249   1.0000
  12.750   1.1440   0.10718   0.10043  -0.0519   0.0251   1.0000
  13.000   1.1269   0.11360   0.10703  -0.0551   0.0254   1.0000
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