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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 100,000
Max Cl/Cd: 63.4 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe450-il-100000.txt
Download as CSV file: xf-goe450-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 450 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3483   0.10818   0.10349  -0.0317   1.0000   0.0726
  -8.000  -0.3696   0.10830   0.10374  -0.0292   1.0000   0.0729
  -7.750  -0.3861   0.10796   0.10351  -0.0294   1.0000   0.0732
  -7.500  -0.3967   0.10705   0.10267  -0.0319   1.0000   0.0734
  -7.250  -0.3936   0.10142   0.09708  -0.0269   1.0000   0.0744
  -7.000  -0.3868   0.09762   0.09330  -0.0219   1.0000   0.0762
  -6.750  -0.3889   0.09541   0.09114  -0.0200   1.0000   0.0778
  -6.500  -0.3927   0.09339   0.08917  -0.0189   1.0000   0.0795
  -6.250  -0.3961   0.09133   0.08715  -0.0187   1.0000   0.0816
  -6.000  -0.3977   0.08921   0.08507  -0.0203   1.0000   0.0844
  -5.750  -0.3822   0.08767   0.08336  -0.0371   1.0000   0.0878
  -5.500  -0.3809   0.08251   0.07836  -0.0298   0.9980   0.0895
  -5.250  -0.3575   0.07885   0.07468  -0.0308   0.9933   0.0939
  -5.000  -0.2990   0.07309   0.06861  -0.0505   0.9849   0.1034
  -4.750  -0.2828   0.06946   0.06506  -0.0489   0.9794   0.1062
  -4.500  -0.2285   0.06480   0.06006  -0.0630   0.9723   0.1186
  -4.250  -0.1885   0.06249   0.05747  -0.0699   0.9644   0.1328
  -4.000  -0.1696   0.05778   0.05295  -0.0694   0.9595   0.1360
  -3.750  -0.1295   0.05447   0.04943  -0.0759   0.9528   0.1502
  -3.500  -0.0929   0.05156   0.04636  -0.0806   0.9459   0.1652
  -3.250  -0.0526   0.04852   0.04324  -0.0850   0.9419   0.1819
  -3.000  -0.0288   0.04646   0.04115  -0.0860   0.9327   0.1994
  -2.000   0.1819   0.03323   0.02528  -0.1084   0.9128   0.1176
  -1.750   0.2129   0.03080   0.02279  -0.1096   0.9048   0.1115
  -1.500   0.2599   0.02913   0.02046  -0.1123   0.8998   0.1012
  -1.250   0.3017   0.02768   0.01877  -0.1148   0.8945   0.0992
  -1.000   0.3360   0.02673   0.01763  -0.1157   0.8862   0.0987
  -0.750   0.3841   0.02578   0.01646  -0.1189   0.8825   0.1023
  -0.500   0.4110   0.02504   0.01579  -0.1188   0.8724   0.1060
  -0.250   0.4574   0.02400   0.01481  -0.1217   0.8684   0.1117
   0.000   0.4853   0.02360   0.01441  -0.1215   0.8587   0.1189
   0.250   0.5275   0.02265   0.01357  -0.1235   0.8539   0.1452
   0.500   0.5572   0.02027   0.01323  -0.1231   0.8465   1.0000
   0.750   0.5933   0.02007   0.01277  -0.1239   0.8395   1.0000
   1.000   0.6211   0.02014   0.01270  -0.1236   0.8298   1.0000
   1.250   0.6579   0.01983   0.01225  -0.1246   0.8237   1.0000
   1.500   0.6837   0.01995   0.01229  -0.1239   0.8132   1.0000
   1.750   0.7211   0.01955   0.01180  -0.1249   0.8077   1.0000
   2.000   0.7455   0.01971   0.01192  -0.1240   0.7963   1.0000
   2.250   0.7763   0.01958   0.01174  -0.1240   0.7880   1.0000
   2.500   0.8072   0.01942   0.01155  -0.1239   0.7793   1.0000
   2.750   0.8332   0.01952   0.01164  -0.1233   0.7683   1.0000
   3.000   0.8692   0.01911   0.01119  -0.1239   0.7618   1.0000
   3.250   0.8935   0.01929   0.01139  -0.1230   0.7494   1.0000
   3.500   0.9197   0.01940   0.01152  -0.1223   0.7378   1.0000
   3.750   0.9490   0.01937   0.01150  -0.1220   0.7276   1.0000
   4.000   0.9801   0.01922   0.01133  -0.1219   0.7174   1.0000
   4.250   1.0057   0.01936   0.01152  -0.1211   0.7041   1.0000
   4.500   1.0317   0.01948   0.01166  -0.1204   0.6907   1.0000
   4.750   1.0582   0.01958   0.01179  -0.1196   0.6770   1.0000
   5.000   1.0846   0.01970   0.01196  -0.1189   0.6631   1.0000
   5.250   1.1109   0.01983   0.01212  -0.1182   0.6489   1.0000
   5.500   1.1366   0.01987   0.01218  -0.1172   0.6326   1.0000
   5.750   1.1621   0.01982   0.01214  -0.1160   0.6144   1.0000
   6.000   1.1881   0.01968   0.01193  -0.1148   0.5949   1.0000
   6.250   1.2080   0.01979   0.01213  -0.1129   0.5731   1.0000
   6.500   1.2304   0.01986   0.01222  -0.1114   0.5529   1.0000
   6.750   1.2527   0.01998   0.01240  -0.1100   0.5334   1.0000
   7.000   1.2710   0.02015   0.01266  -0.1079   0.5093   1.0000
   7.250   1.2889   0.02033   0.01287  -0.1058   0.4830   1.0000
   7.500   1.3041   0.02060   0.01313  -0.1032   0.4508   1.0000
   7.750   1.3177   0.02106   0.01357  -0.1004   0.4161   1.0000
   8.000   1.3250   0.02178   0.01417  -0.0967   0.3657   1.0000
   8.250   1.3181   0.02333   0.01519  -0.0910   0.2625   1.0000
   8.500   1.2972   0.02625   0.01711  -0.0842   0.1570   1.0000
   8.750   1.2886   0.02874   0.01922  -0.0792   0.1149   1.0000
   9.000   1.2870   0.03074   0.02108  -0.0754   0.1004   1.0000
   9.250   1.2871   0.03268   0.02300  -0.0721   0.0918   1.0000
   9.500   1.2853   0.03485   0.02509  -0.0688   0.0856   1.0000
   9.750   1.2916   0.03663   0.02696  -0.0662   0.0805   1.0000
  10.000   1.3002   0.03845   0.02879  -0.0640   0.0760   1.0000
  10.250   1.3174   0.04043   0.03066  -0.0624   0.0711   1.0000
  10.500   1.3357   0.04202   0.03241  -0.0610   0.0670   1.0000
  10.750   1.3632   0.04389   0.03429  -0.0605   0.0635   1.0000
  11.000   1.4059   0.04687   0.03728  -0.0621   0.0594   1.0000
  11.250   1.4226   0.04908   0.03982  -0.0606   0.0573   1.0000
  11.500   1.4442   0.05205   0.04311  -0.0598   0.0560   1.0000
  11.750   1.4571   0.05513   0.04653  -0.0582   0.0551   1.0000
  12.000   1.4633   0.05803   0.04971  -0.0561   0.0539   1.0000
  12.250   1.4732   0.06096   0.05280  -0.0546   0.0523   1.0000
  12.500   1.4761   0.06436   0.05644  -0.0527   0.0514   1.0000
  12.750   1.4694   0.06791   0.06032  -0.0498   0.0515   1.0000
  13.000   1.4551   0.07153   0.06431  -0.0467   0.0518   1.0000
  13.250   1.4280   0.07553   0.06873  -0.0436   0.0524   1.0000
  13.500   1.3997   0.08022   0.07380  -0.0415   0.0531   1.0000
  13.750   1.3715   0.08554   0.07946  -0.0406   0.0538   1.0000
  14.000   1.3427   0.09141   0.08564  -0.0408   0.0545   1.0000
  14.250   1.3132   0.09790   0.09238  -0.0422   0.0552   1.0000
  14.500   1.2832   0.10506   0.09978  -0.0447   0.0559   1.0000
  14.750   1.2527   0.11304   0.10796  -0.0485   0.0566   1.0000
  15.000   1.2226   0.12199   0.11708  -0.0535   0.0575   1.0000
  15.250   1.1949   0.13171   0.12693  -0.0593   0.0585   1.0000
  15.500   1.1754   0.14093   0.13621  -0.0645   0.0595   1.0000
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