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GOE 63 AIRFOIL (goe63-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 63 AIRFOIL (goe63-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe63-il-1000000-n5.txt
Download as CSV file: xf-goe63-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 63 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  -0.2035   0.09570   0.09298  -0.0313   0.7062   0.0145
  -8.000  -0.1942   0.09296   0.09021  -0.0329   0.6994   0.0147
  -7.750  -0.1869   0.08934   0.08657  -0.0355   0.6926   0.0157
  -7.250  -0.1662   0.08388   0.08107  -0.0397   0.6800   0.0160
  -7.000  -0.1512   0.08150   0.07867  -0.0421   0.6735   0.0162
  -6.750  -0.1349   0.07906   0.07620  -0.0448   0.6677   0.0164
  -6.500  -0.1172   0.07646   0.07359  -0.0479   0.6624   0.0167
  -6.250  -0.0968   0.07361   0.07070  -0.0519   0.6562   0.0182
  -6.000  -0.0755   0.07032   0.06737  -0.0564   0.6501   0.0183
  -5.750  -0.0512   0.06678   0.06378  -0.0617   0.6442   0.0184
  -5.500  -0.0257   0.06331   0.06026  -0.0668   0.6380   0.0184
  -5.250   0.0019   0.05983   0.05671  -0.0721   0.6330   0.0184
  -5.000   0.0321   0.05627   0.05309  -0.0777   0.6284   0.0185
  -4.750   0.0630   0.05284   0.04959  -0.0828   0.6234   0.0185
  -4.500   0.0907   0.04974   0.04642  -0.0865   0.6184   0.0186
  -4.250   0.1144   0.04795   0.04461  -0.0880   0.6138   0.0188
  -4.000   0.1414   0.04613   0.04275  -0.0903   0.6088   0.0190
  -3.750   0.1704   0.04420   0.04077  -0.0930   0.6038   0.0196
  -3.250   0.2445   0.03835   0.03469  -0.1017   0.5942   0.0213
  -3.000   0.2775   0.03578   0.03203  -0.1047   0.5882   0.0213
  -2.500   0.3398   0.03161   0.02768  -0.1092   0.5780   0.0204
  -2.250   0.3744   0.02930   0.02526  -0.1117   0.5737   0.0202
  -2.000   0.4090   0.02715   0.02297  -0.1139   0.5685   0.0204
  -1.750   0.4436   0.02499   0.02066  -0.1159   0.5635   0.0203
  -1.500   0.4788   0.02278   0.01828  -0.1178   0.5584   0.0203
  -1.250   0.5143   0.02056   0.01586  -0.1194   0.5529   0.0207
  -1.000   0.5494   0.01836   0.01341  -0.1208   0.5476   0.0209
  -0.750   0.5841   0.01621   0.01102  -0.1220   0.5419   0.0211
  -0.500   0.6238   0.01144   0.00549  -0.1241   0.5349   0.0218
  -0.250   0.6531   0.01111   0.00506  -0.1243   0.5263   0.0221
   0.000   0.6824   0.01082   0.00467  -0.1245   0.5163   0.0223
   0.250   0.7116   0.01052   0.00427  -0.1247   0.5056   0.0227
   0.500   0.7406   0.01027   0.00390  -0.1248   0.4907   0.0230
   0.750   0.7692   0.01010   0.00359  -0.1249   0.4704   0.0233
   1.000   0.7974   0.01005   0.00336  -0.1250   0.4426   0.0237
   1.250   0.8250   0.01014   0.00324  -0.1250   0.4045   0.0240
   1.500   0.8526   0.01028   0.00320  -0.1249   0.3737   0.0245
   1.750   0.8804   0.01040   0.00320  -0.1249   0.3531   0.0249
   2.000   0.9087   0.01038   0.00311  -0.1250   0.3381   0.0253
   2.250   0.9369   0.01041   0.00309  -0.1251   0.3268   0.0258
   2.500   0.9649   0.01050   0.00313  -0.1251   0.3159   0.0264
   2.750   0.9931   0.01056   0.00316  -0.1252   0.3070   0.0270
   3.000   1.0211   0.01065   0.00322  -0.1252   0.2986   0.0277
   3.250   1.0492   0.01071   0.00327  -0.1252   0.2917   0.0284
   3.500   1.0769   0.01084   0.00335  -0.1252   0.2837   0.0289
   3.750   1.1051   0.01089   0.00341  -0.1253   0.2784   0.0304
   4.000   1.1328   0.01101   0.00352  -0.1253   0.2717   0.0319
   4.250   1.1603   0.01115   0.00363  -0.1252   0.2647   0.0333
   4.500   1.1880   0.01126   0.00374  -0.1252   0.2580   0.0361
   4.750   1.2152   0.01142   0.00389  -0.1251   0.2512   0.0438
   5.000   1.2428   0.01151   0.00406  -0.1251   0.2452   0.0942
   5.500   1.2920   0.01063   0.00462  -0.1243   0.2294   1.0000
   5.750   1.3185   0.01089   0.00481  -0.1242   0.2208   1.0000
   6.000   1.3451   0.01111   0.00499  -0.1240   0.2135   1.0000
   6.500   1.3972   0.01165   0.00544  -0.1236   0.1964   1.0000
   6.750   1.4227   0.01196   0.00569  -0.1233   0.1876   1.0000
   7.000   1.4481   0.01227   0.00596  -0.1230   0.1786   1.0000
   7.250   1.4730   0.01261   0.00625  -0.1226   0.1693   1.0000
   7.500   1.4970   0.01302   0.00658  -0.1221   0.1585   1.0000
   7.750   1.5213   0.01338   0.00690  -0.1217   0.1502   1.0000
   8.000   1.5456   0.01373   0.00722  -0.1212   0.1438   1.0000
   8.250   1.5695   0.01409   0.00755  -0.1207   0.1370   1.0000
   8.500   1.5930   0.01447   0.00791  -0.1202   0.1312   1.0000
   8.750   1.6164   0.01484   0.00826  -0.1196   0.1254   1.0000
   9.000   1.6385   0.01530   0.00867  -0.1189   0.1182   1.0000
   9.250   1.6612   0.01568   0.00905  -0.1182   0.1131   1.0000
   9.500   1.6825   0.01615   0.00949  -0.1173   0.1073   1.0000
   9.750   1.7044   0.01654   0.00989  -0.1165   0.1036   1.0000
  10.000   1.7251   0.01701   0.01034  -0.1156   0.0986   1.0000
  10.250   1.7444   0.01753   0.01085  -0.1144   0.0932   1.0000
  10.500   1.7639   0.01801   0.01134  -0.1133   0.0888   1.0000
  10.750   1.7802   0.01864   0.01193  -0.1117   0.0829   1.0000
  11.000   1.7962   0.01924   0.01253  -0.1100   0.0768   1.0000
  11.250   1.8080   0.01999   0.01325  -0.1077   0.0696   1.0000
  11.500   1.8131   0.02100   0.01422  -0.1043   0.0594   1.0000
  11.750   1.8018   0.02321   0.01625  -0.0992   0.0355   1.0000
  12.000   1.7924   0.02564   0.01861  -0.0951   0.0185   1.0000
  12.250   1.7987   0.02709   0.02011  -0.0932   0.0159   1.0000
  12.500   1.8058   0.02858   0.02165  -0.0915   0.0145   1.0000
  12.750   1.8146   0.03001   0.02314  -0.0902   0.0138   1.0000
  13.000   1.8223   0.03161   0.02480  -0.0890   0.0131   1.0000
  13.250   1.8287   0.03336   0.02662  -0.0878   0.0125   1.0000
  13.500   1.8338   0.03531   0.02863  -0.0867   0.0120   1.0000
  13.750   1.8389   0.03729   0.03068  -0.0857   0.0115   1.0000
  14.000   1.8445   0.03927   0.03274  -0.0848   0.0113   1.0000
  14.250   1.8485   0.04141   0.03496  -0.0840   0.0110   1.0000
  14.500   1.8514   0.04374   0.03737  -0.0832   0.0107   1.0000
  14.750   1.8531   0.04623   0.03993  -0.0825   0.0103   1.0000
  15.000   1.8532   0.04892   0.04270  -0.0818   0.0100   1.0000
  15.250   1.8518   0.05183   0.04569  -0.0812   0.0097   1.0000
  15.500   1.8492   0.05497   0.04891  -0.0807   0.0095   1.0000
  15.750   1.8448   0.05839   0.05243  -0.0804   0.0092   1.0000
  16.000   1.8415   0.06177   0.05590  -0.0802   0.0090   1.0000
  16.250   1.8382   0.06522   0.05945  -0.0801   0.0089   1.0000
  16.500   1.8339   0.06890   0.06322  -0.0802   0.0088   1.0000
  16.750   1.8284   0.07280   0.06722  -0.0804   0.0087   1.0000
  17.000   1.8216   0.07695   0.07147  -0.0807   0.0085   1.0000
  17.250   1.8135   0.08138   0.07601  -0.0813   0.0084   1.0000
  17.500   1.8045   0.08604   0.08079  -0.0820   0.0083   1.0000
  17.750   1.7940   0.09099   0.08584  -0.0829   0.0082   1.0000
  18.000   1.7821   0.09623   0.09119  -0.0840   0.0081   1.0000
  18.250   1.7687   0.10184   0.09692  -0.0854   0.0080   1.0000
  18.500   1.7545   0.10768   0.10288  -0.0871   0.0079   1.0000
  18.750   1.7397   0.11366   0.10898  -0.0889   0.0078   1.0000
  19.000   1.7241   0.11988   0.11532  -0.0910   0.0078   1.0000
  19.250   1.7079   0.12633   0.12189  -0.0934   0.0077   1.0000
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