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GOE 388 AIRFOIL (goe388-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 388 AIRFOIL (goe388-il)
Reynolds number: 1,000,000
Max Cl/Cd: 53.51 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe388-il-1000000.txt
Download as CSV file: xf-goe388-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 388 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3241   0.09459   0.09008  -0.0483   0.1005   0.0218
  -9.000  -0.3310   0.08816   0.08367  -0.0514   0.0954   0.0222
  -8.750  -0.3205   0.08621   0.08172  -0.0518   0.0997   0.0225
  -8.500  -0.3095   0.08426   0.07976  -0.0525   0.0974   0.0228
  -8.250  -0.2994   0.08211   0.07760  -0.0538   0.0934   0.0233
  -8.000  -0.2910   0.07979   0.07526  -0.0554   0.0791   0.0239
  -7.750  -0.2816   0.07708   0.07253  -0.0582   0.0625   0.0249
  -7.500  -0.2618   0.07163   0.06706  -0.0690   0.0624   0.0274
  -7.250  -0.2446   0.06674   0.06215  -0.0756   0.0612   0.0275
  -7.000  -0.2252   0.06122   0.05657  -0.0827   0.0602   0.0276
  -6.750  -0.2114   0.04972   0.04494  -0.0951   0.0613   0.0285
  -6.500  -0.1903   0.04815   0.04335  -0.0965   0.0575   0.0289
  -6.250  -0.1677   0.04625   0.04142  -0.0984   0.0429   0.0294
  -6.000  -0.1437   0.04361   0.03871  -0.1010   0.0375   0.0301
  -5.750  -0.1183   0.04045   0.03545  -0.1041   0.0347   0.0312
  -5.500  -0.0845   0.03669   0.03145  -0.1073   0.0329   0.0348
  -4.500   0.0141   0.01899   0.01216  -0.1145   0.0298   0.0325
  -4.250   0.0407   0.01715   0.01001  -0.1148   0.0289   0.0321
  -4.000   0.0672   0.01639   0.00909  -0.1148   0.0282   0.0326
  -3.750   0.0930   0.01587   0.00842  -0.1147   0.0279   0.0330
  -3.500   0.1199   0.01528   0.00770  -0.1147   0.0278   0.0334
  -3.250   0.1472   0.01485   0.00717  -0.1148   0.0277   0.0340
  -3.000   0.1749   0.01443   0.00666  -0.1149   0.0273   0.0344
  -2.750   0.2020   0.01417   0.00633  -0.1150   0.0267   0.0346
  -2.500   0.2287   0.01401   0.00611  -0.1149   0.0261   0.0349
  -2.250   0.2553   0.01394   0.00598  -0.1149   0.0256   0.0351
  -2.000   0.2813   0.01357   0.00555  -0.1148   0.0249   0.0353
  -1.750   0.3066   0.01328   0.00520  -0.1145   0.0245   0.0359
  -1.500   0.3301   0.01343   0.00530  -0.1140   0.0242   0.0369
  -1.250   0.3523   0.01398   0.00580  -0.1133   0.0241   0.0382
  -1.000   0.3785   0.01403   0.00583  -0.1132   0.0240   0.0395
  -0.750   0.4060   0.01388   0.00567  -0.1133   0.0239   0.0407
  -0.500   0.4354   0.01348   0.00527  -0.1137   0.0233   0.0419
  -0.250   0.4615   0.01358   0.00534  -0.1136   0.0225   0.0430
   0.000   0.4866   0.01382   0.00555  -0.1133   0.0220   0.0439
   0.250   0.5114   0.01413   0.00583  -0.1130   0.0217   0.0446
   0.500   0.5361   0.01442   0.00606  -0.1126   0.0214   0.0476
   0.750   0.5606   0.01480   0.00642  -0.1122   0.0212   0.0535
   1.000   0.5850   0.01524   0.00686  -0.1119   0.0210   0.0688
   1.250   0.6098   0.01558   0.00744  -0.1118   0.0209   0.1832
   1.500   0.6349   0.01600   0.00815  -0.1118   0.0208   0.3263
   1.750   0.6607   0.01636   0.00903  -0.1122   0.0207   0.5770
   6.500   1.1023   0.02060   0.01402  -0.1041   0.0205   1.0000
   6.750   1.1247   0.02148   0.01496  -0.1037   0.0205   1.0000
   7.000   1.1468   0.02244   0.01598  -0.1034   0.0205   1.0000
   7.250   1.1688   0.02338   0.01701  -0.1030   0.0205   1.0000
   7.500   1.1908   0.02427   0.01798  -0.1025   0.0204   1.0000
   7.750   1.2132   0.02494   0.01877  -0.1021   0.0204   1.0000
   8.000   1.2370   0.02450   0.01855  -0.1013   0.0202   1.0000
   8.250   1.2618   0.02368   0.01779  -0.1010   0.0178   1.0000
   8.500   1.2807   0.02570   0.01980  -0.1009   0.0170   1.0000
   8.750   1.3557   0.03613   0.02995  -0.1089   0.0144   1.0000
   9.000   1.3783   0.03707   0.03098  -0.1084   0.0103   1.0000
   9.250   1.4011   0.03751   0.03140  -0.1084   0.0096   1.0000
   9.500   1.4228   0.03827   0.03219  -0.1081   0.0090   1.0000
   9.750   1.4437   0.03923   0.03319  -0.1077   0.0084   1.0000
  10.000   1.4649   0.03995   0.03392  -0.1074   0.0079   1.0000
  10.250   1.4874   0.04021   0.03414  -0.1074   0.0075   1.0000
  10.500   1.5060   0.04156   0.03559  -0.1066   0.0072   1.0000
  10.750   1.5237   0.04300   0.03715  -0.1057   0.0069   1.0000
  11.000   1.5421   0.04411   0.03833  -0.1049   0.0065   1.0000
  11.250   1.5610   0.04497   0.03923  -0.1043   0.0063   1.0000
  11.500   1.5794   0.04581   0.04011  -0.1037   0.0061   1.0000
  11.750   1.5962   0.04680   0.04117  -0.1028   0.0058   1.0000
  12.000   1.6080   0.04848   0.04301  -0.1011   0.0056   1.0000
  12.250   1.6169   0.05070   0.04545  -0.0990   0.0055   1.0000
  12.500   1.6239   0.05303   0.04798  -0.0967   0.0055   1.0000
  12.750   1.6277   0.05557   0.05073  -0.0941   0.0054   1.0000
  13.000   1.6276   0.05829   0.05369  -0.0910   0.0053   1.0000
  13.250   1.6230   0.06122   0.05686  -0.0875   0.0053   1.0000
  13.500   1.6139   0.06428   0.06016  -0.0835   0.0052   1.0000
  13.750   1.6001   0.06745   0.06356  -0.0792   0.0052   1.0000
  14.000   1.5779   0.07053   0.06686  -0.0738   0.0051   1.0000
  14.250   1.5478   0.07366   0.07020  -0.0680   0.0051   1.0000
  14.500   1.5176   0.07713   0.07386  -0.0635   0.0051   1.0000
  14.750   1.4884   0.08091   0.07782  -0.0602   0.0051   1.0000
  15.000   1.4574   0.08526   0.08235  -0.0578   0.0051   1.0000
  15.250   1.4261   0.09010   0.08737  -0.0565   0.0052   1.0000
  15.500   1.3938   0.09555   0.09299  -0.0562   0.0052   1.0000
  15.750   1.3628   0.10141   0.09901  -0.0569   0.0052   1.0000
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