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GOE 450 AIRFOIL (goe450-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 450 AIRFOIL (goe450-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.42 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe450-il-1000000.txt
Download as CSV file: xf-goe450-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.2332   0.08290   0.08123  -0.0668   0.9820   0.0169
  -8.250  -0.2295   0.07781   0.07614  -0.0703   0.9730   0.0171
  -8.000  -0.2183   0.07579   0.07412  -0.0707   0.9660   0.0173
  -7.750  -0.2078   0.07347   0.07178  -0.0721   0.9582   0.0176
  -7.500  -0.1954   0.07082   0.06912  -0.0747   0.9504   0.0179
  -7.250  -0.1818   0.06782   0.06609  -0.0780   0.9428   0.0184
  -7.000  -0.1654   0.06428   0.06252  -0.0826   0.9349   0.0193
  -6.750  -0.1358   0.05631   0.05443  -0.0960   0.9261   0.0208
  -6.500  -0.1110   0.05011   0.04813  -0.1035   0.9185   0.0209
  -6.250  -0.0945   0.04422   0.04212  -0.1087   0.9119   0.0214
  -6.000  -0.0722   0.04212   0.03996  -0.1106   0.9056   0.0218
  -5.750  -0.0485   0.03973   0.03748  -0.1127   0.8994   0.0223
  -5.500  -0.0227   0.03672   0.03435  -0.1154   0.8931   0.0232
  -5.250   0.0090   0.02396   0.02076  -0.1222   0.8860   0.0263
  -5.000   0.0334   0.02255   0.01926  -0.1226   0.8800   0.0267
  -4.750   0.0588   0.02151   0.01815  -0.1230   0.8729   0.0271
  -4.500   0.0846   0.02039   0.01688  -0.1232   0.8663   0.0278
  -4.250   0.1111   0.01901   0.01535  -0.1235   0.8583   0.0291
  -4.000   0.1406   0.01922   0.01528  -0.1230   0.8504   0.0317
  -3.750   0.1674   0.01783   0.01361  -0.1231   0.8411   0.0318
  -3.500  -0.0614   0.02285   0.02064  -0.1245   0.8602   0.0276
  -2.750   0.2742   0.01111   0.00597  -0.1231   0.7998   0.0310
  -2.500   0.3015   0.01026   0.00495  -0.1230   0.7876   0.0308
  -2.250   0.3289   0.00974   0.00430  -0.1228   0.7750   0.0309
  -2.000   0.3563   0.00934   0.00379  -0.1226   0.7624   0.0310
  -1.750   0.3838   0.00898   0.00335  -0.1225   0.7498   0.0311
  -1.500   0.4112   0.00867   0.00298  -0.1224   0.7372   0.0313
  -1.250   0.4386   0.00843   0.00267  -0.1222   0.7249   0.0314
  -1.000   0.4661   0.00832   0.00249  -0.1221   0.7132   0.0317
  -0.500   0.5209   0.00773   0.00179  -0.1219   0.6905   0.0329
  -0.250   0.5485   0.00759   0.00159  -0.1219   0.6797   0.0340
   0.000   0.5761   0.00753   0.00148  -0.1218   0.6689   0.0349
   0.250   0.6035   0.00751   0.00141  -0.1217   0.6572   0.0359
   0.500   0.6312   0.00748   0.00135  -0.1216   0.6463   0.0369
   0.750   0.6588   0.00748   0.00132  -0.1216   0.6366   0.0382
   1.250   0.7138   0.00750   0.00129  -0.1214   0.6146   0.0479
   1.500   0.7412   0.00719   0.00138  -0.1215   0.6053   0.2337
   1.750   0.7679   0.00675   0.00154  -0.1217   0.5964   0.5085
   2.000   0.7925   0.00577   0.00166  -0.1211   0.5880   1.0000
   2.250   0.8197   0.00589   0.00172  -0.1209   0.5767   1.0000
   2.500   0.8464   0.00603   0.00178  -0.1207   0.5590   1.0000
   2.750   0.8730   0.00619   0.00185  -0.1205   0.5403   1.0000
   3.000   0.8994   0.00636   0.00194  -0.1203   0.5220   1.0000
   3.250   0.9257   0.00655   0.00204  -0.1200   0.5036   1.0000
   3.500   0.9519   0.00675   0.00215  -0.1198   0.4825   1.0000
   3.750   0.9776   0.00699   0.00229  -0.1194   0.4609   1.0000
   4.000   1.0032   0.00723   0.00244  -0.1191   0.4393   1.0000
   4.250   1.0277   0.00757   0.00263  -0.1186   0.4097   1.0000
   4.500   1.0522   0.00791   0.00284  -0.1181   0.3823   1.0000
   4.750   1.0773   0.00819   0.00304  -0.1177   0.3601   1.0000
   5.000   1.1018   0.00852   0.00325  -0.1172   0.3371   1.0000
   5.250   1.1255   0.00892   0.00351  -0.1166   0.3069   1.0000
   5.500   1.1474   0.00948   0.00384  -0.1157   0.2629   1.0000
   5.750   1.1633   0.01057   0.00446  -0.1139   0.1777   1.0000
   6.000   1.1831   0.01129   0.00496  -0.1127   0.1382   1.0000
   6.250   1.1989   0.01236   0.00565  -0.1108   0.0717   1.0000
   6.500   1.2178   0.01311   0.00620  -0.1095   0.0391   1.0000
   6.750   1.2399   0.01357   0.00664  -0.1086   0.0340   1.0000
   7.000   1.2626   0.01395   0.00704  -0.1078   0.0318   1.0000
   7.250   1.2852   0.01432   0.00745  -0.1070   0.0304   1.0000
   7.500   1.3068   0.01475   0.00791  -0.1060   0.0287   1.0000
   7.750   1.3266   0.01531   0.00850  -0.1048   0.0266   1.0000
   8.000   1.3455   0.01591   0.00915  -0.1034   0.0251   1.0000
   8.250   1.3668   0.01628   0.00955  -0.1024   0.0243   1.0000
   8.500   1.3870   0.01671   0.01001  -0.1012   0.0231   1.0000
   8.750   1.4058   0.01718   0.01050  -0.0999   0.0219   1.0000
   9.000   1.4200   0.01782   0.01118  -0.0977   0.0205   1.0000
   9.250   1.4308   0.01868   0.01210  -0.0950   0.0195   1.0000
   9.500   1.4489   0.01910   0.01256  -0.0936   0.0188   1.0000
   9.750   1.4653   0.01963   0.01313  -0.0919   0.0180   1.0000
  10.000   1.4813   0.02018   0.01372  -0.0903   0.0172   1.0000
  10.250   1.4966   0.02080   0.01435  -0.0886   0.0164   1.0000
  10.500   1.5022   0.02205   0.01566  -0.0856   0.0154   1.0000
  10.750   1.5160   0.02279   0.01646  -0.0839   0.0149   1.0000
  11.000   1.5302   0.02353   0.01726  -0.0823   0.0144   1.0000
  11.250   1.5431   0.02437   0.01815  -0.0806   0.0139   1.0000
  11.500   1.5555   0.02527   0.01909  -0.0789   0.0133   1.0000
  11.750   1.5674   0.02622   0.02009  -0.0773   0.0129   1.0000
  12.000   1.5758   0.02746   0.02138  -0.0754   0.0124   1.0000
  12.250   1.5734   0.02961   0.02362  -0.0725   0.0118   1.0000
  12.500   1.5804   0.03108   0.02518  -0.0708   0.0116   1.0000
  12.750   1.5907   0.03231   0.02649  -0.0694   0.0113   1.0000
  13.000   1.5995   0.03371   0.02796  -0.0681   0.0109   1.0000
  13.250   1.6073   0.03523   0.02955  -0.0667   0.0106   1.0000
  13.500   1.6135   0.03694   0.03133  -0.0654   0.0103   1.0000
  13.750   1.6192   0.03874   0.03320  -0.0642   0.0100   1.0000
  14.000   1.6236   0.04074   0.03527  -0.0631   0.0097   1.0000
  14.250   1.6251   0.04308   0.03769  -0.0620   0.0095   1.0000
  14.500   1.6215   0.04603   0.04073  -0.0608   0.0092   1.0000
  14.750   1.6114   0.04985   0.04468  -0.0597   0.0090   1.0000
  15.000   1.6052   0.05337   0.04833  -0.0589   0.0088   1.0000
  15.250   1.6071   0.05605   0.05110  -0.0585   0.0087   1.0000
  15.500   1.6073   0.05902   0.05418  -0.0582   0.0086   1.0000
  15.750   1.6057   0.06226   0.05753  -0.0581   0.0085   1.0000
  16.000   1.6036   0.06564   0.06101  -0.0580   0.0084   1.0000
  16.250   1.6006   0.06919   0.06467  -0.0582   0.0082   1.0000
  16.500   1.5965   0.07297   0.06856  -0.0584   0.0081   1.0000
  16.750   1.5917   0.07693   0.07263  -0.0589   0.0080   1.0000
  17.000   1.5864   0.08106   0.07687  -0.0595   0.0078   1.0000
  17.250   1.5806   0.08529   0.08121  -0.0602   0.0077   1.0000
  17.500   1.5744   0.08968   0.08570  -0.0612   0.0076   1.0000
  17.750   1.5680   0.09419   0.09031  -0.0623   0.0075   1.0000
  18.000   1.5616   0.09881   0.09503  -0.0635   0.0074   1.0000
  18.250   1.5544   0.10359   0.09991  -0.0650   0.0073   1.0000
  18.500   1.5459   0.10862   0.10503  -0.0666   0.0072   1.0000
  18.750   1.5374   0.11375   0.11026  -0.0684   0.0071   1.0000
  19.000   1.5276   0.11915   0.11576  -0.0705   0.0070   1.0000
  19.250   1.5167   0.12483   0.12154  -0.0728   0.0069   1.0000
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