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GOE 423 AIRFOIL (goe423-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 423 AIRFOIL (goe423-il)
Reynolds number: 200,000
Max Cl/Cd: 69.32 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe423-il-200000.txt
Download as CSV file: xf-goe423-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 423 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1564   0.09110   0.08729  -0.0966   0.9627   0.0998
  -9.750  -0.1305   0.08856   0.08473  -0.0980   0.9573   0.1016
  -9.500  -0.1947   0.07773   0.07385  -0.1191   0.9362   0.1098
  -9.250  -0.1677   0.07484   0.07103  -0.1157   0.9292   0.1107
  -9.000  -0.1379   0.07393   0.07010  -0.1119   0.9225   0.1116
  -8.750  -0.1235   0.07232   0.06847  -0.1098   0.9088   0.1127
  -8.500  -0.1146   0.07013   0.06627  -0.1091   0.8935   0.1145
  -8.250  -0.2055   0.06000   0.05556  -0.1207   0.8654   0.1234
  -8.000  -0.1773   0.05678   0.05246  -0.1199   0.8533   0.1246
  -7.750  -0.1565   0.05521   0.05089  -0.1184   0.8362   0.1258
  -7.500  -0.2356   0.03480   0.02844  -0.1172   0.8198   0.0873
  -7.250  -0.2200   0.03228   0.02563  -0.1160   0.8029   0.0871
  -7.000  -0.2037   0.03030   0.02326  -0.1147   0.7864   0.0872
  -6.750  -0.1853   0.02850   0.02111  -0.1135   0.7709   0.0873
  -6.500  -0.1652   0.02689   0.01917  -0.1125   0.7571   0.0873
  -6.250  -0.1437   0.02539   0.01732  -0.1116   0.7454   0.0876
  -6.000  -0.1218   0.02381   0.01554  -0.1109   0.7333   0.0883
  -5.750  -0.0975   0.02281   0.01442  -0.1105   0.7237   0.0895
  -5.500  -0.0727   0.02211   0.01359  -0.1102   0.7148   0.0909
  -5.250  -0.0471   0.02143   0.01276  -0.1098   0.7074   0.0922
  -5.000  -0.0217   0.02073   0.01191  -0.1094   0.7000   0.0933
  -4.750   0.0051   0.02011   0.01108  -0.1092   0.6942   0.0946
  -4.500   0.0311   0.01957   0.01041  -0.1089   0.6882   0.0961
  -4.250   0.0575   0.01919   0.00988  -0.1086   0.6826   0.0978
  -4.000   0.0845   0.01849   0.00913  -0.1086   0.6780   0.1001
  -3.750   0.1112   0.01814   0.00878  -0.1085   0.6734   0.1025
  -3.500   0.1372   0.01782   0.00845  -0.1082   0.6684   0.1050
  -3.250   0.1639   0.01753   0.00809  -0.1080   0.6640   0.1079
  -3.000   0.1908   0.01719   0.00770  -0.1078   0.6603   0.1113
  -2.750   0.2176   0.01699   0.00752  -0.1078   0.6570   0.1160
  -2.500   0.2431   0.01684   0.00738  -0.1074   0.6534   0.1217
  -2.250   0.2681   0.01656   0.00719  -0.1070   0.6500   0.1285
  -2.000   0.2940   0.01639   0.00702  -0.1067   0.6468   0.1390
  -1.750   0.3193   0.01610   0.00683  -0.1063   0.6439   0.1582
  -1.500   0.3439   0.01575   0.00666  -0.1059   0.6413   0.1986
  -1.250   0.3677   0.01546   0.00669  -0.1055   0.6387   0.2709
  -1.000   0.3863   0.01491   0.00674  -0.1041   0.6358   0.4026
  -0.750   0.4015   0.01430   0.00694  -0.1017   0.6328   0.6209
  -0.500   0.4253   0.01397   0.00727  -0.1001   0.6302   0.7965
  -0.250   0.4789   0.01422   0.00763  -0.1045   0.6276   0.9059
   0.000   0.5314   0.01458   0.00789  -0.1090   0.6253   0.9470
   0.250   0.6035   0.01498   0.00814  -0.1177   0.6230   0.9770
   0.500   0.6762   0.01526   0.00828  -0.1271   0.6208   0.9947
   0.750   0.7157   0.01538   0.00839  -0.1301   0.6185   1.0000
   1.000   0.7362   0.01557   0.00858  -0.1292   0.6159   1.0000
   1.250   0.7572   0.01578   0.00878  -0.1283   0.6135   1.0000
   1.500   0.7787   0.01602   0.00900  -0.1274   0.6113   1.0000
   1.750   0.8007   0.01627   0.00922  -0.1266   0.6093   1.0000
   2.000   0.8232   0.01653   0.00945  -0.1259   0.6074   1.0000
   2.250   0.8466   0.01681   0.00969  -0.1254   0.6054   1.0000
   2.500   0.8709   0.01716   0.00998  -0.1249   0.6034   1.0000
   2.750   0.8913   0.01756   0.01039  -0.1239   0.6014   1.0000
   3.000   0.9091   0.01793   0.01083  -0.1223   0.5994   1.0000
   3.250   0.9273   0.01832   0.01126  -0.1208   0.5970   1.0000
   3.500   0.9467   0.01869   0.01166  -0.1195   0.5944   1.0000
   3.750   0.9669   0.01905   0.01205  -0.1183   0.5920   1.0000
   4.000   0.9889   0.01937   0.01237  -0.1174   0.5896   1.0000
   4.250   1.0140   0.01960   0.01256  -0.1170   0.5867   1.0000
   4.500   1.0415   0.02000   0.01289  -0.1170   0.5838   1.0000
   4.750   1.0518   0.02040   0.01342  -0.1141   0.5800   1.0000
   5.000   1.0687   0.02073   0.01381  -0.1122   0.5759   1.0000
   5.250   1.0926   0.02080   0.01387  -0.1115   0.5715   1.0000
   5.500   1.1251   0.02066   0.01362  -0.1121   0.5669   1.0000
   5.750   1.1401   0.02094   0.01396  -0.1098   0.5615   1.0000
   6.000   1.1578   0.02102   0.01409  -0.1079   0.5557   1.0000
   6.250   1.1864   0.02083   0.01386  -0.1079   0.5508   1.0000
   6.500   1.2163   0.02082   0.01377  -0.1082   0.5463   1.0000
   6.750   1.2257   0.02113   0.01423  -0.1050   0.5409   1.0000
   7.000   1.2471   0.02112   0.01426  -0.1038   0.5357   1.0000
   7.250   1.2804   0.02078   0.01382  -0.1045   0.5307   1.0000
   7.500   1.2939   0.02099   0.01414  -0.1020   0.5251   1.0000
   7.750   1.3102   0.02100   0.01423  -0.0999   0.5189   1.0000
   8.000   1.3429   0.02051   0.01363  -0.1004   0.5126   1.0000
   8.250   1.3504   0.02071   0.01398  -0.0968   0.5058   1.0000
   8.500   1.3691   0.02051   0.01382  -0.0950   0.4987   1.0000
   8.750   1.3862   0.02039   0.01373  -0.0930   0.4914   1.0000
   9.000   1.3940   0.02032   0.01373  -0.0893   0.4820   1.0000
   9.250   1.4009   0.02030   0.01377  -0.0854   0.4729   1.0000
   9.500   1.4065   0.02029   0.01377  -0.0814   0.4623   1.0000
   9.750   1.4056   0.02067   0.01427  -0.0767   0.4492   1.0000
  10.000   1.4059   0.02112   0.01474  -0.0724   0.4319   1.0000
  10.250   1.4056   0.02184   0.01547  -0.0684   0.4093   1.0000
  10.500   1.3974   0.02304   0.01650  -0.0637   0.3717   1.0000
  10.750   1.3802   0.02514   0.01833  -0.0585   0.3343   1.0000
  11.000   1.3607   0.02789   0.02087  -0.0539   0.3020   1.0000
  11.250   1.3402   0.03110   0.02393  -0.0499   0.2716   1.0000
  11.500   1.3187   0.03479   0.02747  -0.0466   0.2401   1.0000
  11.750   1.2956   0.03903   0.03154  -0.0438   0.2050   1.0000
  12.000   1.2679   0.04403   0.03630  -0.0415   0.1598   1.0000
  12.250   1.2391   0.04937   0.04134  -0.0395   0.1193   1.0000
  12.500   1.2219   0.05368   0.04551  -0.0380   0.0958   1.0000
  12.750   1.2130   0.05727   0.04903  -0.0369   0.0825   1.0000
  13.000   1.2092   0.06041   0.05216  -0.0361   0.0759   1.0000
  13.250   1.2056   0.06357   0.05531  -0.0354   0.0719   1.0000
  13.500   1.2050   0.06647   0.05828  -0.0349   0.0692   1.0000
  13.750   1.2037   0.06949   0.06133  -0.0344   0.0670   1.0000
  14.000   1.2008   0.07272   0.06460  -0.0339   0.0653   1.0000
  14.250   1.1974   0.07599   0.06790  -0.0335   0.0639   1.0000
  14.500   1.1994   0.07868   0.07066  -0.0332   0.0628   1.0000
  14.750   1.2019   0.08129   0.07333  -0.0328   0.0617   1.0000
  15.000   1.2049   0.08383   0.07591  -0.0325   0.0606   1.0000
  15.250   1.2087   0.08622   0.07833  -0.0321   0.0595   1.0000
  15.500   1.2135   0.08841   0.08051  -0.0317   0.0584   1.0000
  15.750   1.2202   0.09015   0.08221  -0.0310   0.0573   1.0000
  16.000   1.2308   0.09133   0.08336  -0.0302   0.0562   1.0000
  16.250   1.2415   0.09276   0.08484  -0.0297   0.0555   1.0000
  16.500   1.2535   0.09395   0.08608  -0.0291   0.0547   1.0000
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