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GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 532 AIRFOIL (goe532-il)
Reynolds number: 500,000
Max Cl/Cd: 89.74 at α=3°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe532-il-500000-n5.txt
Download as CSV file: xf-goe532-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 532 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3213   0.09567   0.09320  -0.0389   1.0000   0.0206
 -10.250  -0.3168   0.09335   0.09091  -0.0392   1.0000   0.0209
  -9.750  -0.4560   0.03335   0.03000  -0.1041   0.9384   0.0239
  -9.500  -0.4247   0.03154   0.02804  -0.1077   0.9219   0.0241
  -9.250  -0.3990   0.02980   0.02609  -0.1099   0.9019   0.0243
  -9.000  -0.3788   0.02806   0.02411  -0.1107   0.8822   0.0246
  -8.750  -0.3602   0.02635   0.02215  -0.1108   0.8650   0.0248
  -8.500  -0.3416   0.02464   0.02017  -0.1106   0.8491   0.0251
  -8.250  -0.3223   0.02301   0.01824  -0.1102   0.8339   0.0254
  -8.000  -0.3021   0.02147   0.01640  -0.1097   0.8186   0.0258
  -7.750  -0.2805   0.02013   0.01477  -0.1092   0.8034   0.0263
  -7.500  -0.2578   0.01900   0.01335  -0.1086   0.7879   0.0268
  -7.250  -0.2344   0.01802   0.01210  -0.1080   0.7720   0.0271
  -7.000  -0.2102   0.01724   0.01107  -0.1074   0.7545   0.0274
  -6.750  -0.1862   0.01643   0.01007  -0.1067   0.7344   0.0276
  -6.500  -0.1620   0.01579   0.00927  -0.1061   0.7114   0.0278
  -6.250  -0.1374   0.01533   0.00866  -0.1054   0.6860   0.0281
  -6.000  -0.1126   0.01494   0.00812  -0.1047   0.6621   0.0284
  -5.750  -0.0873   0.01458   0.00762  -0.1041   0.6423   0.0287
  -5.500  -0.0616   0.01423   0.00714  -0.1036   0.6257   0.0290
  -5.250  -0.0355   0.01389   0.00670  -0.1031   0.6121   0.0294
  -5.000  -0.0093   0.01360   0.00629  -0.1026   0.6000   0.0299
  -4.750   0.0172   0.01329   0.00589  -0.1022   0.5883   0.0304
  -4.500   0.0437   0.01299   0.00549  -0.1018   0.5760   0.0308
  -4.250   0.0700   0.01273   0.00512  -0.1013   0.5630   0.0311
  -4.000   0.0965   0.01250   0.00479  -0.1008   0.5492   0.0314
  -3.750   0.1233   0.01226   0.00448  -0.1004   0.5377   0.0317
  -3.500   0.1496   0.01196   0.00412  -0.1000   0.5272   0.0322
  -3.250   0.1766   0.01174   0.00388  -0.0996   0.5180   0.0327
  -3.000   0.2036   0.01158   0.00367  -0.0993   0.5104   0.0333
  -2.750   0.2310   0.01141   0.00347  -0.0990   0.5031   0.0338
  -2.500   0.2582   0.01129   0.00330  -0.0986   0.4958   0.0346
  -2.250   0.2857   0.01118   0.00315  -0.0983   0.4894   0.0355
  -2.000   0.3131   0.01109   0.00301  -0.0980   0.4815   0.0363
  -1.750   0.3402   0.01096   0.00285  -0.0977   0.4746   0.0373
  -1.500   0.3678   0.01086   0.00273  -0.0974   0.4685   0.0383
  -1.250   0.3953   0.01080   0.00264  -0.0971   0.4621   0.0396
  -1.000   0.4227   0.01076   0.00256  -0.0968   0.4561   0.0411
  -0.750   0.4503   0.01070   0.00249  -0.0966   0.4499   0.0432
  -0.500   0.4777   0.01067   0.00244  -0.0963   0.4440   0.0468
  -0.250   0.5051   0.01064   0.00241  -0.0960   0.4392   0.0536
   0.000   0.5327   0.01055   0.00238  -0.0957   0.4336   0.0724
   0.250   0.5589   0.01016   0.00236  -0.0955   0.4278   0.2070
   0.500   0.5854   0.00997   0.00241  -0.0952   0.4232   0.3004
   0.750   0.6125   0.00982   0.00247  -0.0950   0.4187   0.3754
   1.000   0.6393   0.00972   0.00254  -0.0947   0.4135   0.4429
   1.250   0.6653   0.00962   0.00264  -0.0942   0.4079   0.5262
   1.500   0.6907   0.00947   0.00277  -0.0936   0.4013   0.6236
   1.750   0.7158   0.00938   0.00287  -0.0929   0.3939   0.7009
   2.000   0.7403   0.00931   0.00295  -0.0919   0.3869   0.7656
   2.250   0.7766   0.00902   0.00301  -0.0934   0.3765   0.9375
   2.500   0.8079   0.00917   0.00308  -0.0940   0.3647   1.0000
   2.750   0.8341   0.00935   0.00317  -0.0936   0.3507   1.0000
   3.000   0.8597   0.00958   0.00328  -0.0931   0.3304   1.0000
   3.250   0.8832   0.00998   0.00345  -0.0923   0.2926   1.0000
   3.500   0.9038   0.01066   0.00380  -0.0911   0.2383   1.0000
   3.750   0.9264   0.01116   0.00413  -0.0902   0.2108   1.0000
   4.000   0.9505   0.01151   0.00438  -0.0895   0.1976   1.0000
   4.250   0.9751   0.01182   0.00461  -0.0889   0.1895   1.0000
   4.500   1.0001   0.01208   0.00484  -0.0883   0.1842   1.0000
   4.750   1.0253   0.01231   0.00504  -0.0878   0.1807   1.0000
   5.000   1.0501   0.01256   0.00527  -0.0872   0.1774   1.0000
   5.250   1.0746   0.01283   0.00551  -0.0866   0.1743   1.0000
   5.500   1.0989   0.01311   0.00577  -0.0859   0.1711   1.0000
   5.750   1.1235   0.01334   0.00600  -0.0853   0.1687   1.0000
   6.000   1.1481   0.01358   0.00625  -0.0847   0.1666   1.0000
   6.250   1.1722   0.01383   0.00650  -0.0841   0.1644   1.0000
   6.500   1.1960   0.01409   0.00676  -0.0834   0.1622   1.0000
   6.750   1.2193   0.01438   0.00706  -0.0826   0.1596   1.0000
   7.000   1.2418   0.01471   0.00737  -0.0817   0.1568   1.0000
   7.250   1.2641   0.01503   0.00770  -0.0808   0.1539   1.0000
   7.500   1.2875   0.01526   0.00797  -0.0801   0.1520   1.0000
   7.750   1.3103   0.01553   0.00825  -0.0793   0.1486   1.0000
   8.000   1.3321   0.01584   0.00857  -0.0783   0.1450   1.0000
   8.250   1.3523   0.01622   0.00893  -0.0771   0.1407   1.0000
   8.500   1.3735   0.01652   0.00926  -0.0761   0.1363   1.0000
   8.750   1.3925   0.01691   0.00962  -0.0748   0.1257   1.0000
   9.250   1.4096   0.01850   0.01093  -0.0689   0.0860   1.0000
   9.500   1.4220   0.01912   0.01156  -0.0667   0.0832   1.0000
   9.750   1.4340   0.01977   0.01224  -0.0645   0.0811   1.0000
  10.000   1.4453   0.02049   0.01298  -0.0623   0.0792   1.0000
  10.250   1.4571   0.02120   0.01374  -0.0603   0.0778   1.0000
  10.500   1.4698   0.02189   0.01449  -0.0585   0.0768   1.0000
  10.750   1.4814   0.02268   0.01534  -0.0568   0.0757   1.0000
  11.000   1.4916   0.02360   0.01631  -0.0550   0.0745   1.0000
  11.250   1.5003   0.02465   0.01743  -0.0532   0.0733   1.0000
  11.500   1.5082   0.02583   0.01866  -0.0516   0.0723   1.0000
  11.750   1.5145   0.02719   0.02008  -0.0499   0.0713   1.0000
  12.000   1.5199   0.02871   0.02166  -0.0485   0.0704   1.0000
  12.250   1.5231   0.03049   0.02351  -0.0471   0.0695   1.0000
  12.500   1.5296   0.03210   0.02520  -0.0461   0.0689   1.0000
  12.750   1.5368   0.03372   0.02689  -0.0452   0.0684   1.0000
  13.000   1.5431   0.03548   0.02875  -0.0445   0.0678   1.0000
  13.250   1.5482   0.03745   0.03079  -0.0439   0.0671   1.0000
  13.500   1.5523   0.03957   0.03300  -0.0434   0.0665   1.0000
  13.750   1.5560   0.04181   0.03534  -0.0431   0.0659   1.0000
  14.000   1.5591   0.04418   0.03778  -0.0428   0.0652   1.0000
  14.250   1.5606   0.04678   0.04046  -0.0427   0.0645   1.0000
  14.500   1.5617   0.04947   0.04324  -0.0427   0.0639   1.0000
  14.750   1.5618   0.05235   0.04619  -0.0427   0.0632   1.0000
  15.000   1.5609   0.05539   0.04932  -0.0429   0.0626   1.0000
  15.250   1.5585   0.05868   0.05267  -0.0432   0.0619   1.0000
  15.500   1.5543   0.06223   0.05630  -0.0437   0.0612   1.0000
  15.750   1.5565   0.06509   0.05924  -0.0441   0.0604   1.0000
  16.000   1.5593   0.06789   0.06214  -0.0446   0.0596   1.0000
  16.250   1.5617   0.07077   0.06511  -0.0451   0.0587   1.0000
  16.500   1.5626   0.07390   0.06833  -0.0457   0.0579   1.0000
  16.750   1.5629   0.07716   0.07168  -0.0465   0.0572   1.0000
  17.000   1.5629   0.08048   0.07507  -0.0473   0.0564   1.0000
  17.250   1.5616   0.08407   0.07873  -0.0483   0.0555   1.0000
  17.500   1.5591   0.08787   0.08260  -0.0494   0.0546   1.0000
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