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GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 54 AIRFOIL (goe54-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.69 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe54-il-1000000-n5.txt
Download as CSV file: xf-goe54-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 54 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5666   0.09794   0.09643   0.0374   0.9771   0.0091
  -8.000  -0.5640   0.09536   0.09304   0.0362   0.6898   0.0093
  -7.750  -0.5618   0.08855   0.08615   0.0296   0.6613   0.0102
  -7.500  -0.5476   0.08565   0.08299   0.0260   0.5728   0.0103
  -7.250  -0.5318   0.08259   0.07974   0.0221   0.5147   0.0105
  -7.000  -0.5147   0.07915   0.07620   0.0179   0.4871   0.0106
  -6.750  -0.4961   0.07545   0.07242   0.0134   0.4709   0.0108
  -6.000  -0.4270   0.06009   0.05675  -0.0039   0.4392   0.0126
  -5.750  -0.4033   0.05751   0.05409  -0.0064   0.4289   0.0128
  -5.500  -0.3782   0.05462   0.05111  -0.0090   0.4211   0.0130
  -5.250  -0.3520   0.05150   0.04789  -0.0117   0.4139   0.0133
  -5.000  -0.3246   0.04816   0.04440  -0.0144   0.4071   0.0137
  -4.750  -0.2903   0.04179   0.03776  -0.0187   0.4030   0.0151
  -4.500  -0.2645   0.03996   0.03585  -0.0197   0.3967   0.0153
  -4.250  -0.2377   0.03808   0.03385  -0.0207   0.3906   0.0155
  -4.000  -0.2099   0.03600   0.03166  -0.0217   0.3853   0.0157
  -3.750  -0.1814   0.03378   0.02929  -0.0227   0.3790   0.0160
  -3.500  -0.1521   0.03145   0.02679  -0.0235   0.3732   0.0164
  -3.250  -0.1169   0.02715   0.02208  -0.0243   0.3681   0.0179
  -3.000  -0.0898   0.02586   0.02069  -0.0247   0.3603   0.0181
  -2.750  -0.0621   0.02470   0.01943  -0.0250   0.3529   0.0183
  -2.500  -0.0338   0.02354   0.01812  -0.0253   0.3434   0.0185
  -2.250  -0.0049   0.02224   0.01667  -0.0255   0.3335   0.0187
  -2.000   0.0243   0.02096   0.01521  -0.0256   0.3214   0.0190
  -1.750   0.0534   0.01989   0.01394  -0.0257   0.3023   0.0196
  -1.500   0.0832   0.01863   0.01241  -0.0258   0.2790   0.0199
  -1.250   0.1130   0.01745   0.01098  -0.0257   0.2614   0.0203
  -1.000   0.1428   0.01632   0.00961  -0.0256   0.2498   0.0206
  -0.750   0.1723   0.01536   0.00848  -0.0255   0.2429   0.0208
  -0.500   0.2015   0.01445   0.00739  -0.0254   0.2368   0.0213
  -0.250   0.2304   0.01374   0.00655  -0.0254   0.2312   0.0213
   0.000   0.2591   0.01321   0.00595  -0.0253   0.2278   0.0215
   0.250   0.2876   0.01283   0.00551  -0.0253   0.2236   0.0217
   0.500   0.3161   0.01250   0.00511  -0.0252   0.2183   0.0220
   0.750   0.3447   0.01216   0.00472  -0.0251   0.2141   0.0223
   1.000   0.3733   0.01181   0.00433  -0.0250   0.2120   0.0227
   1.250   0.4019   0.01147   0.00395  -0.0248   0.2092   0.0231
   1.500   0.4304   0.01115   0.00360  -0.0247   0.2060   0.0233
   1.750   0.4589   0.01089   0.00331  -0.0246   0.2029   0.0238
   2.000   0.4874   0.01065   0.00304  -0.0245   0.2000   0.0242
   2.250   0.5159   0.01040   0.00279  -0.0244   0.1980   0.0245
   2.500   0.5444   0.01025   0.00264  -0.0244   0.1965   0.0248
   2.750   0.5731   0.01004   0.00243  -0.0244   0.1945   0.0254
   3.000   0.6016   0.01000   0.00240  -0.0243   0.1920   0.0259
   3.250   0.6301   0.00998   0.00238  -0.0243   0.1891   0.0264
   3.500   0.6585   0.00998   0.00238  -0.0242   0.1860   0.0269
   3.750   0.6869   0.01000   0.00240  -0.0242   0.1830   0.0276
   4.000   0.7153   0.01000   0.00242  -0.0241   0.1809   0.0286
   4.250   0.7437   0.01002   0.00245  -0.0240   0.1777   0.0292
   4.500   0.7720   0.01006   0.00249  -0.0240   0.1735   0.0297
   4.750   0.8002   0.01012   0.00254  -0.0239   0.1689   0.0310
   5.000   0.8284   0.01018   0.00262  -0.0239   0.1649   0.0323
   5.250   0.8565   0.01030   0.00272  -0.0238   0.1574   0.0336
   5.500   0.8843   0.01048   0.00285  -0.0237   0.1452   0.0356
   5.750   0.9120   0.01070   0.00301  -0.0237   0.1336   0.0388
   6.000   0.9397   0.01089   0.00320  -0.0236   0.1266   0.0447
   6.500   0.9919   0.00967   0.00372  -0.0233   0.1200   1.0000
   6.750   1.0195   0.00989   0.00394  -0.0232   0.1165   1.0000
   7.000   1.0472   0.01009   0.00415  -0.0231   0.1143   1.0000
   7.250   1.0748   0.01027   0.00435  -0.0230   0.1126   1.0000
   7.500   1.1023   0.01049   0.00458  -0.0229   0.1102   1.0000
   7.750   1.1295   0.01075   0.00484  -0.0228   0.1065   1.0000
   8.000   1.1566   0.01104   0.00512  -0.0227   0.1022   1.0000
   8.250   1.1840   0.01125   0.00537  -0.0226   0.1004   1.0000
   8.500   1.2112   0.01146   0.00562  -0.0225   0.0979   1.0000
   8.750   1.2381   0.01174   0.00591  -0.0225   0.0929   1.0000
   9.000   1.2647   0.01208   0.00623  -0.0224   0.0863   1.0000
   9.250   1.2890   0.01306   0.00699  -0.0223   0.0566   1.0000
   9.500   1.3143   0.01370   0.00760  -0.0222   0.0480   1.0000
   9.750   1.3402   0.01414   0.00807  -0.0220   0.0444   1.0000
  10.000   1.3656   0.01468   0.00863  -0.0219   0.0408   1.0000
  10.250   1.3913   0.01510   0.00909  -0.0217   0.0387   1.0000
  10.500   1.4167   0.01555   0.00958  -0.0216   0.0367   1.0000
  10.750   1.4415   0.01611   0.01017  -0.0214   0.0342   1.0000
  11.000   1.4663   0.01664   0.01074  -0.0212   0.0322   1.0000
  11.250   1.4912   0.01711   0.01126  -0.0210   0.0308   1.0000
  11.500   1.5154   0.01768   0.01186  -0.0208   0.0287   1.0000
  11.750   1.5389   0.01836   0.01257  -0.0206   0.0264   1.0000
  12.000   1.5628   0.01892   0.01318  -0.0203   0.0244   1.0000
  12.250   1.5854   0.01967   0.01396  -0.0201   0.0217   1.0000
  12.500   1.6078   0.02040   0.01474  -0.0198   0.0191   1.0000
  12.750   1.6290   0.02129   0.01565  -0.0195   0.0165   1.0000
  13.000   1.6494   0.02226   0.01667  -0.0191   0.0144   1.0000
  13.250   1.6694   0.02323   0.01770  -0.0187   0.0129   1.0000
  13.500   1.6880   0.02432   0.01886  -0.0183   0.0116   1.0000
  13.750   1.7056   0.02549   0.02011  -0.0178   0.0106   1.0000
  14.000   1.7228   0.02662   0.02133  -0.0173   0.0100   1.0000
  14.250   1.7379   0.02793   0.02274  -0.0168   0.0094   1.0000
  14.500   1.7501   0.02950   0.02441  -0.0162   0.0088   1.0000
  14.750   1.7584   0.03141   0.02643  -0.0157   0.0083   1.0000
  15.000   1.7634   0.03350   0.02866  -0.0152   0.0080   1.0000
  15.250   1.7530   0.03706   0.03239  -0.0156   0.0079   1.0000
  15.500   1.7154   0.05075   0.04643  -0.0292   0.0081   1.0000
  15.750   1.6590   0.06353   0.05943  -0.0364   0.0084   1.0000
  16.000   1.6081   0.07480   0.07089  -0.0418   0.0088   1.0000
  16.250   1.5624   0.08543   0.08168  -0.0467   0.0091   1.0000
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