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GOE 92 AIRFOIL (goe92-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 92 AIRFOIL (goe92-il)
Reynolds number: 500,000
Max Cl/Cd: 99.58 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe92-il-500000.txt
Download as CSV file: xf-goe92-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 92 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2954   0.10718   0.10512  -0.0204   1.0000   0.0116
  -8.750  -0.2904   0.10428   0.10225  -0.0228   1.0000   0.0116
  -8.500  -0.2859   0.10137   0.09937  -0.0251   1.0000   0.0116
  -8.250  -0.2772   0.09669   0.09470  -0.0239   1.0000   0.0118
  -8.000  -0.2704   0.09365   0.09169  -0.0240   1.0000   0.0121
  -7.750  -0.2652   0.09105   0.08913  -0.0248   0.9992   0.0123
  -7.500  -0.2468   0.08731   0.08539  -0.0296   0.9806   0.0128
  -7.250  -0.2281   0.08345   0.08151  -0.0347   0.9593   0.0133
  -7.000  -0.2116   0.07978   0.07780  -0.0393   0.9407   0.0137
  -6.750  -0.1972   0.07636   0.07432  -0.0431   0.9252   0.0141
  -6.500  -0.1812   0.07292   0.07081  -0.0473   0.9132   0.0146
  -6.250  -0.1573   0.06923   0.06706  -0.0541   0.9026   0.0152
  -6.000  -0.1297   0.06526   0.06300  -0.0616   0.8934   0.0153
  -5.750  -0.1035   0.06130   0.05891  -0.0670   0.8852   0.0154
  -5.500  -0.0781   0.05743   0.05493  -0.0709   0.8765   0.0154
  -5.250  -0.0603   0.05255   0.04997  -0.0735   0.8687   0.0157
  -5.000  -0.0457   0.04957   0.04696  -0.0739   0.8596   0.0160
  -4.750  -0.0249   0.04678   0.04411  -0.0753   0.8501   0.0165
  -4.500  -0.0003   0.04388   0.04109  -0.0774   0.8405   0.0173
  -4.250   0.0275   0.04084   0.03790  -0.0795   0.8297   0.0186
  -4.000   0.0700   0.03833   0.03504  -0.0818   0.8185   0.0202
  -3.750   0.0981   0.03557   0.03204  -0.0826   0.8061   0.0203
  -3.500   0.1228   0.03095   0.02716  -0.0837   0.7925   0.0206
  -3.250   0.1442   0.02816   0.02427  -0.0843   0.7743   0.0212
  -3.000   0.1682   0.02630   0.02224  -0.0845   0.7502   0.0219
  -2.750   0.1938   0.02460   0.02026  -0.0844   0.7169   0.0234
  -2.500   0.2251   0.02421   0.01936  -0.0831   0.6767   0.0268
  -2.250   0.2522   0.02313   0.01777  -0.0824   0.6432   0.0271
  -2.000   0.2757   0.01917   0.01351  -0.0828   0.6196   0.0285
  -1.750   0.3012   0.01810   0.01223  -0.0827   0.5981   0.0301
  -1.500   0.3288   0.01738   0.01125  -0.0823   0.5794   0.0338
   0.500   0.5463   0.01202   0.00419  -0.0799   0.4290   0.0492
   0.750   0.5728   0.01192   0.00395  -0.0795   0.4098   0.0484
   1.000   0.5993   0.01160   0.00356  -0.0792   0.3948   0.0463
   1.250   0.6258   0.01136   0.00324  -0.0790   0.3827   0.0454
   1.500   0.6527   0.01124   0.00305  -0.0788   0.3731   0.0456
   1.750   0.6795   0.01121   0.00295  -0.0786   0.3656   0.0461
   2.000   0.7066   0.01118   0.00289  -0.0785   0.3594   0.0466
   2.250   0.7334   0.01124   0.00289  -0.0783   0.3540   0.0480
   2.500   0.7607   0.01126   0.00287  -0.0783   0.3495   0.0487
   2.750   0.7879   0.01131   0.00289  -0.0782   0.3450   0.0505
   3.000   0.8147   0.01143   0.00296  -0.0780   0.3406   0.0561
   3.250   0.8407   0.00977   0.00324  -0.0782   0.3366   1.0000
   3.500   0.8678   0.00990   0.00334  -0.0781   0.3326   1.0000
   3.750   0.8944   0.01008   0.00348  -0.0779   0.3290   1.0000
   4.000   0.9207   0.01031   0.00364  -0.0777   0.3257   1.0000
   4.250   0.9472   0.01052   0.00382  -0.0776   0.3227   1.0000
   4.500   0.9741   0.01066   0.00397  -0.0775   0.3197   1.0000
   4.750   1.0008   0.01081   0.00415  -0.0774   0.3160   1.0000
   5.000   1.0270   0.01103   0.00433  -0.0772   0.3119   1.0000
   5.250   1.0536   0.01115   0.00446  -0.0772   0.3046   1.0000
   5.500   1.0797   0.01132   0.00459  -0.0770   0.2972   1.0000
   5.750   1.1062   0.01146   0.00477  -0.0769   0.2912   1.0000
   6.000   1.1323   0.01162   0.00491  -0.0768   0.2820   1.0000
   6.250   1.1589   0.01172   0.00504  -0.0767   0.2718   1.0000
   6.500   1.1850   0.01190   0.00520  -0.0766   0.2597   1.0000
   6.750   1.2090   0.01227   0.00539  -0.0763   0.2225   1.0000
   7.000   1.2203   0.01419   0.00656  -0.0744   0.1168   1.0000
   7.250   1.2306   0.01620   0.00804  -0.0724   0.0242   1.0000
   7.500   1.2528   0.01678   0.00864  -0.0716   0.0186   1.0000
   7.750   1.2752   0.01730   0.00928  -0.0709   0.0168   1.0000
   8.000   1.2965   0.01792   0.01005  -0.0700   0.0154   1.0000
   8.250   1.3163   0.01866   0.01092  -0.0690   0.0144   1.0000
   8.500   1.3338   0.01959   0.01199  -0.0677   0.0136   1.0000
   8.750   1.3482   0.02075   0.01329  -0.0659   0.0129   1.0000
   9.000   1.3577   0.02220   0.01490  -0.0636   0.0125   1.0000
   9.250   1.3571   0.02412   0.01700  -0.0600   0.0120   1.0000
   9.500   1.3706   0.02487   0.01784  -0.0582   0.0115   1.0000
   9.750   1.3762   0.02616   0.01923  -0.0557   0.0112   1.0000
  10.000   1.3784   0.02780   0.02099  -0.0533   0.0110   1.0000
  10.250   1.3787   0.02975   0.02305  -0.0511   0.0109   1.0000
  10.500   1.3779   0.03197   0.02539  -0.0493   0.0107   1.0000
  10.750   1.3759   0.03448   0.02802  -0.0478   0.0106   1.0000
  11.000   1.3729   0.03728   0.03092  -0.0467   0.0105   1.0000
  11.250   1.3694   0.04031   0.03406  -0.0458   0.0104   1.0000
  11.500   1.3660   0.04350   0.03735  -0.0452   0.0104   1.0000
  11.750   1.3630   0.04671   0.04067  -0.0446   0.0104   1.0000
  12.000   1.3612   0.04978   0.04381  -0.0438   0.0106   1.0000
  12.250   1.3613   0.05244   0.04653  -0.0424   0.0109   1.0000
  12.500   1.3770   0.05318   0.04724  -0.0395   0.0129   1.0000
  12.750   1.1644   0.06133   0.05622  -0.0341   0.0107   1.0000
  13.000   1.1603   0.06512   0.06007  -0.0333   0.0108   1.0000
  13.250   1.1604   0.06809   0.06310  -0.0319   0.0109   1.0000
  13.500   1.1879   0.06655   0.06147  -0.0276   0.0128   1.0000
  14.250   1.2225   0.07178   0.06713  -0.0210   0.0163   1.0000
  14.500   1.2157   0.07567   0.07115  -0.0211   0.0159   1.0000
  14.750   1.2084   0.07954   0.07515  -0.0212   0.0156   1.0000
  15.000   1.1980   0.08358   0.07932  -0.0215   0.0152   1.0000
  15.250   1.1876   0.08749   0.08336  -0.0220   0.0149   1.0000
  15.500   1.1742   0.09139   0.08739  -0.0225   0.0146   1.0000
  15.750   1.1532   0.09486   0.09102  -0.0227   0.0145   1.0000
  16.000   1.1367   0.09848   0.09478  -0.0236   0.0144   1.0000
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