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GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 591 AIRFOIL (goe591-il)
Reynolds number: 200,000
Max Cl/Cd: 76.91 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe591-il-200000-n5.txt
Download as CSV file: xf-goe591-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 591 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2386   0.08576   0.08237  -0.0588   0.9780   0.0222
  -8.500  -0.2288   0.08079   0.07741  -0.0640   0.9703   0.0223
  -8.250  -0.2246   0.07357   0.07020  -0.0723   0.9601   0.0233
  -8.000  -0.2165   0.06569   0.06232  -0.0831   0.9486   0.0243
  -7.750  -0.1996   0.06300   0.05960  -0.0867   0.9376   0.0249
  -7.500  -0.1830   0.05833   0.05486  -0.0929   0.9266   0.0255
  -7.250  -0.1676   0.05180   0.04818  -0.1005   0.9153   0.0260
  -7.000  -0.1519   0.04543   0.04160  -0.1063   0.9037   0.0274
  -6.750  -0.1531   0.03286   0.02825  -0.1114   0.8895   0.0293
  -6.500  -0.1427   0.02704   0.02154  -0.1116   0.8782   0.0306
  -6.250  -0.1223   0.02442   0.01849  -0.1116   0.8695   0.0320
  -6.000  -0.0969   0.02332   0.01722  -0.1117   0.8610   0.0333
  -5.750  -0.0732   0.02191   0.01551  -0.1114   0.8518   0.0344
  -5.250  -0.0226   0.01958   0.01257  -0.1108   0.8345   0.0372
  -5.000   0.0036   0.01851   0.01118  -0.1105   0.8265   0.0384
  -4.750   0.0293   0.01760   0.01001  -0.1100   0.8178   0.0391
  -4.500   0.0555   0.01685   0.00905  -0.1096   0.8097   0.0397
  -4.250   0.0812   0.01598   0.00804  -0.1092   0.8015   0.0411
  -4.000   0.1069   0.01546   0.00745  -0.1087   0.7932   0.0426
  -3.750   0.1332   0.01498   0.00688  -0.1083   0.7850   0.0438
  -3.500   0.1588   0.01454   0.00635  -0.1078   0.7765   0.0449
  -3.250   0.1851   0.01415   0.00586  -0.1073   0.7684   0.0462
  -3.000   0.2105   0.01381   0.00545  -0.1067   0.7594   0.0477
  -2.750   0.2369   0.01352   0.00505  -0.1063   0.7513   0.0492
  -2.500   0.2621   0.01324   0.00476  -0.1057   0.7418   0.0519
  -2.250   0.2883   0.01305   0.00453  -0.1053   0.7333   0.0563
  -2.000   0.3141   0.01285   0.00429  -0.1047   0.7239   0.0623
  -1.750   0.3399   0.01268   0.00408  -0.1042   0.7144   0.0731
  -1.500   0.3660   0.01250   0.00387  -0.1037   0.7054   0.0884
  -1.250   0.3913   0.01234   0.00373  -0.1032   0.6952   0.1047
  -1.000   0.4169   0.01220   0.00363  -0.1027   0.6854   0.1276
  -0.750   0.4425   0.01208   0.00356  -0.1022   0.6755   0.1620
  -0.500   0.4677   0.01196   0.00352  -0.1017   0.6649   0.2055
  -0.250   0.4924   0.01177   0.00348  -0.1011   0.6548   0.2610
   0.000   0.5139   0.01124   0.00348  -0.1001   0.6448   0.4430
   0.500   0.6148   0.01022   0.00355  -0.1090   0.6215   1.0000
   0.750   0.6380   0.01034   0.00354  -0.1080   0.6110   1.0000
   1.000   0.6612   0.01048   0.00354  -0.1070   0.6002   1.0000
   1.250   0.6843   0.01061   0.00358  -0.1060   0.5893   1.0000
   1.500   0.7075   0.01076   0.00362  -0.1050   0.5788   1.0000
   1.750   0.7306   0.01092   0.00367  -0.1040   0.5685   1.0000
   2.000   0.7536   0.01108   0.00374  -0.1030   0.5570   1.0000
   2.250   0.7765   0.01125   0.00382  -0.1019   0.5454   1.0000
   2.500   0.7994   0.01143   0.00391  -0.1009   0.5343   1.0000
   2.750   0.8224   0.01162   0.00402  -0.1000   0.5238   1.0000
   3.000   0.8457   0.01180   0.00415  -0.0991   0.5139   1.0000
   3.250   0.8690   0.01200   0.00429  -0.0982   0.5053   1.0000
   3.500   0.8924   0.01220   0.00445  -0.0973   0.4962   1.0000
   3.750   0.9158   0.01240   0.00461  -0.0965   0.4882   1.0000
   4.000   0.9393   0.01261   0.00479  -0.0957   0.4803   1.0000
   4.250   0.9626   0.01282   0.00498  -0.0949   0.4724   1.0000
   4.500   0.9855   0.01305   0.00518  -0.0940   0.4636   1.0000
   4.750   1.0082   0.01328   0.00540  -0.0931   0.4538   1.0000
   5.000   1.0305   0.01353   0.00561  -0.0921   0.4449   1.0000
   5.250   1.0527   0.01376   0.00586  -0.0911   0.4350   1.0000
   5.500   1.0749   0.01401   0.00611  -0.0901   0.4258   1.0000
   5.750   1.0963   0.01429   0.00636  -0.0890   0.4167   1.0000
   6.000   1.1182   0.01454   0.00665  -0.0880   0.4070   1.0000
   6.250   1.1394   0.01483   0.00694  -0.0869   0.3984   1.0000
   6.500   1.1603   0.01511   0.00724  -0.0857   0.3885   1.0000
   6.750   1.1810   0.01540   0.00756  -0.0845   0.3786   1.0000
   7.000   1.2008   0.01572   0.00790  -0.0832   0.3697   1.0000
   7.250   1.2212   0.01602   0.00826  -0.0820   0.3604   1.0000
   7.500   1.2403   0.01636   0.00863  -0.0806   0.3505   1.0000
   7.750   1.2571   0.01674   0.00901  -0.0788   0.3374   1.0000
   8.000   1.2714   0.01715   0.00942  -0.0765   0.3210   1.0000
   8.250   1.2834   0.01762   0.00986  -0.0739   0.3036   1.0000
   8.500   1.2944   0.01817   0.01036  -0.0713   0.2861   1.0000
   8.750   1.3043   0.01880   0.01094  -0.0685   0.2686   1.0000
   9.000   1.3138   0.01950   0.01159  -0.0659   0.2516   1.0000
   9.250   1.3229   0.02027   0.01233  -0.0633   0.2332   1.0000
   9.500   1.3298   0.02120   0.01318  -0.0605   0.2126   1.0000
   9.750   1.3357   0.02223   0.01413  -0.0578   0.1927   1.0000
  10.000   1.3423   0.02329   0.01514  -0.0554   0.1708   1.0000
  10.250   1.3471   0.02452   0.01629  -0.0529   0.1508   1.0000
  10.500   1.3482   0.02606   0.01771  -0.0503   0.1291   1.0000
  10.750   1.3495   0.02768   0.01926  -0.0478   0.1121   1.0000
  11.250   1.3355   0.03251   0.02373  -0.0426   0.0508   1.0000
  11.500   1.3271   0.03528   0.02642  -0.0403   0.0275   1.0000
  11.750   1.3246   0.03770   0.02884  -0.0387   0.0222   1.0000
  12.000   1.3249   0.03997   0.03118  -0.0374   0.0201   1.0000
  12.250   1.3238   0.04246   0.03378  -0.0363   0.0183   1.0000
  12.500   1.3230   0.04504   0.03648  -0.0354   0.0173   1.0000
  12.750   1.3239   0.04754   0.03912  -0.0347   0.0165   1.0000
  13.000   1.3239   0.05022   0.04195  -0.0342   0.0158   1.0000
  13.250   1.3223   0.05319   0.04507  -0.0338   0.0152   1.0000
  13.500   1.3197   0.05641   0.04843  -0.0337   0.0148   1.0000
  13.750   1.3160   0.05987   0.05204  -0.0337   0.0144   1.0000
  14.000   1.3110   0.06362   0.05596  -0.0340   0.0141   1.0000
  14.250   1.3046   0.06770   0.06018  -0.0345   0.0138   1.0000
  14.500   1.2969   0.07209   0.06471  -0.0353   0.0135   1.0000
  14.750   1.2860   0.07706   0.06982  -0.0364   0.0132   1.0000
  15.000   1.2756   0.08213   0.07502  -0.0376   0.0129   1.0000
  15.250   1.2663   0.08711   0.08013  -0.0390   0.0128   1.0000
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