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GOE 265 AIRFOIL (goe265-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 265 AIRFOIL (goe265-il)
Reynolds number: 1,000,000
Max Cl/Cd: 136.53 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe265-il-1000000.txt
Download as CSV file: xf-goe265-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 265 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2847   0.11214   0.11061  -0.0109   1.0000   0.0137
  -9.250  -0.2781   0.10834   0.10682  -0.0132   1.0000   0.0147
  -9.000  -0.2723   0.10482   0.10331  -0.0156   1.0000   0.0148
  -8.750  -0.2593   0.10097   0.09945  -0.0194   0.9606   0.0148
  -8.500  -0.2533   0.09742   0.09574  -0.0202   0.9032   0.0150
  -8.250  -0.2446   0.09543   0.09363  -0.0200   0.8711   0.0152
  -8.000  -0.2352   0.09337   0.09145  -0.0206   0.8413   0.0154
  -7.750  -0.2254   0.09112   0.08908  -0.0216   0.8107   0.0157
  -7.500  -0.2155   0.08868   0.08653  -0.0230   0.7823   0.0161
  -7.250  -0.2054   0.08609   0.08385  -0.0249   0.7597   0.0167
  -7.000  -0.1882   0.08076   0.07845  -0.0334   0.7435   0.0181
  -6.750  -0.1705   0.07692   0.07453  -0.0380   0.7282   0.0181
  -6.500  -0.1551   0.07264   0.07018  -0.0419   0.7147   0.0184
  -6.250  -0.1371   0.07070   0.06818  -0.0433   0.7007   0.0186
  -6.000  -0.1166   0.06851   0.06595  -0.0458   0.6893   0.0190
  -5.750  -0.0942   0.06606   0.06344  -0.0491   0.6794   0.0198
  -5.500  -0.0543   0.05947   0.05675  -0.0614   0.6710   0.0218
  -5.250   0.0356   0.01451   0.01003  -0.1116   0.6742   0.0267
  -5.000   0.0636   0.01408   0.00952  -0.1116   0.6644   0.0276
  -4.750   0.0919   0.01381   0.00918  -0.1116   0.6543   0.0283
  -4.500   0.1203   0.01308   0.00827  -0.1117   0.6447   0.0291
  -4.000   0.1773   0.01212   0.00698  -0.1118   0.6246   0.0308
  -3.750   0.2058   0.01135   0.00596  -0.1119   0.6154   0.0315
  -3.500   0.2342   0.01049   0.00490  -0.1120   0.6053   0.0326
  -3.250   0.2626   0.01029   0.00465  -0.1119   0.5957   0.0336
  -3.000   0.2910   0.01008   0.00433  -0.1117   0.5864   0.0345
  -2.750   0.3196   0.00980   0.00395  -0.1116   0.5778   0.0354
  -2.500   0.3481   0.00958   0.00362  -0.1115   0.5691   0.0362
  -2.250   0.3766   0.00940   0.00336  -0.1114   0.5604   0.0369
  -2.000   0.4050   0.00901   0.00285  -0.1113   0.5525   0.0382
  -1.750   0.4336   0.00881   0.00261  -0.1112   0.5449   0.0396
  -1.500   0.4619   0.00871   0.00246  -0.1111   0.5373   0.0410
  -1.250   0.4904   0.00861   0.00231  -0.1109   0.5297   0.0425
  -1.000   0.5187   0.00856   0.00219  -0.1108   0.5220   0.0438
  -0.750   0.5473   0.00837   0.00198  -0.1107   0.5149   0.0466
  -0.500   0.5755   0.00836   0.00193  -0.1105   0.5065   0.0498
  -0.250   0.6039   0.00833   0.00187  -0.1104   0.4977   0.0525
   0.000   0.6322   0.00829   0.00182  -0.1102   0.4888   0.0587
   0.250   0.6605   0.00829   0.00179  -0.1101   0.4804   0.0634
   0.500   0.6887   0.00832   0.00182  -0.1100   0.4723   0.0693
   0.750   0.7169   0.00839   0.00187  -0.1098   0.4630   0.0729
   1.000   0.7450   0.00839   0.00185  -0.1097   0.4529   0.0788
   1.250   0.7729   0.00847   0.00190  -0.1096   0.4423   0.0828
   1.500   0.8010   0.00855   0.00194  -0.1095   0.4316   0.0855
   1.750   0.8289   0.00856   0.00193  -0.1093   0.4203   0.0907
   2.000   0.8567   0.00867   0.00200  -0.1092   0.4080   0.0953
   2.250   0.8843   0.00880   0.00207  -0.1090   0.3954   0.0990
   2.500   0.9119   0.00887   0.00210  -0.1089   0.3834   0.1030
   2.750   0.9396   0.00895   0.00217  -0.1088   0.3728   0.1082
   3.000   0.9671   0.00908   0.00226  -0.1086   0.3626   0.1125
   3.250   0.9945   0.00921   0.00235  -0.1085   0.3525   0.1162
   3.500   1.0221   0.00929   0.00243  -0.1083   0.3440   0.1234
   3.750   1.0492   0.00945   0.00256  -0.1082   0.3353   0.1291
   4.000   1.0768   0.00953   0.00265  -0.1081   0.3284   0.1383
   4.250   1.1039   0.00968   0.00279  -0.1079   0.3210   0.1486
   4.500   1.1314   0.00975   0.00292  -0.1078   0.3155   0.1664
   4.750   1.1587   0.00982   0.00309  -0.1077   0.3094   0.2334
   5.000   1.1827   0.00884   0.00340  -0.1073   0.3040   1.0000
   5.250   1.2101   0.00897   0.00352  -0.1071   0.2996   1.0000
   5.500   1.2371   0.00914   0.00367  -0.1069   0.2944   1.0000
   5.750   1.2637   0.00936   0.00385  -0.1067   0.2889   1.0000
   6.000   1.2909   0.00949   0.00399  -0.1066   0.2847   1.0000
   6.250   1.3176   0.00967   0.00416  -0.1064   0.2789   1.0000
   6.500   1.3440   0.00989   0.00435  -0.1062   0.2734   1.0000
   6.750   1.3708   0.01004   0.00452  -0.1060   0.2683   1.0000
   7.000   1.3969   0.01027   0.00473  -0.1058   0.2615   1.0000
   7.250   1.4232   0.01048   0.00493  -0.1056   0.2534   1.0000
   7.500   1.4487   0.01077   0.00517  -0.1053   0.2432   1.0000
   7.750   1.4740   0.01107   0.00542  -0.1050   0.2309   1.0000
   8.000   1.4985   0.01144   0.00573  -0.1046   0.2150   1.0000
   8.250   1.5214   0.01200   0.00614  -0.1040   0.1888   1.0000
   8.500   1.5401   0.01302   0.00687  -0.1029   0.1462   1.0000
   8.750   1.5614   0.01371   0.00746  -0.1021   0.1296   1.0000
   9.000   1.5833   0.01428   0.00798  -0.1014   0.1204   1.0000
   9.250   1.6071   0.01463   0.00836  -0.1009   0.1172   1.0000
   9.500   1.6299   0.01506   0.00880  -0.1003   0.1133   1.0000
   9.750   1.6516   0.01558   0.00931  -0.0995   0.1081   1.0000
  10.000   1.6748   0.01593   0.00969  -0.0990   0.1049   1.0000
  10.250   1.6972   0.01632   0.01011  -0.0984   0.1006   1.0000
  10.500   1.7171   0.01693   0.01069  -0.0974   0.0934   1.0000
  10.750   1.7380   0.01740   0.01114  -0.0966   0.0839   1.0000
  11.000   1.7436   0.01913   0.01253  -0.0939   0.0467   1.0000
  11.250   1.7393   0.02137   0.01457  -0.0900   0.0188   1.0000
  11.500   1.7454   0.02245   0.01570  -0.0871   0.0160   1.0000
  11.750   1.7529   0.02349   0.01680  -0.0846   0.0146   1.0000
  12.000   1.7603   0.02463   0.01802  -0.0824   0.0137   1.0000
  12.250   1.7651   0.02609   0.01954  -0.0804   0.0129   1.0000
  12.500   1.7671   0.02795   0.02150  -0.0786   0.0121   1.0000
  12.750   1.7714   0.02978   0.02342  -0.0772   0.0117   1.0000
  13.000   1.7765   0.03167   0.02540  -0.0763   0.0113   1.0000
  13.250   1.7797   0.03388   0.02770  -0.0755   0.0110   1.0000
  13.500   1.7817   0.03636   0.03028  -0.0749   0.0106   1.0000
  13.750   1.7815   0.03917   0.03318  -0.0745   0.0103   1.0000
  14.000   1.7787   0.04235   0.03646  -0.0743   0.0099   1.0000
  14.250   1.7719   0.04610   0.04032  -0.0741   0.0096   1.0000
  14.500   1.7597   0.05059   0.04494  -0.0742   0.0094   1.0000
  14.750   1.7460   0.05539   0.04987  -0.0744   0.0092   1.0000
  15.000   1.7404   0.05917   0.05375  -0.0746   0.0091   1.0000
  15.250   1.7331   0.06325   0.05794  -0.0750   0.0089   1.0000
  15.500   1.7238   0.06773   0.06253  -0.0755   0.0088   1.0000
  15.750   1.7130   0.07252   0.06743  -0.0762   0.0087   1.0000
  16.000   1.7021   0.07744   0.07246  -0.0771   0.0086   1.0000
  16.250   1.6901   0.08260   0.07773  -0.0781   0.0085   1.0000
  16.500   1.6771   0.08799   0.08323  -0.0793   0.0084   1.0000
  16.750   1.6641   0.09349   0.08884  -0.0806   0.0083   1.0000
  17.000   1.6512   0.09904   0.09450  -0.0820   0.0082   1.0000
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