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GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.02 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe279-il-1000000-n5.txt
Download as CSV file: xf-goe279-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 279 (DAIMLER X) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3345   0.10906   0.10739  -0.0267   1.0000   0.0054
  -9.500  -0.3301   0.10619   0.10453  -0.0274   1.0000   0.0052
  -9.250  -0.3274   0.10335   0.10171  -0.0278   1.0000   0.0051
  -9.000  -0.3163   0.09949   0.09785  -0.0310   0.9972   0.0050
  -8.750  -0.3044   0.09556   0.09393  -0.0344   0.9935   0.0049
  -8.500  -0.2926   0.09161   0.08998  -0.0379   0.9878   0.0049
  -8.250  -0.2811   0.08769   0.08606  -0.0415   0.9800   0.0050
  -8.000  -0.2707   0.08380   0.08216  -0.0450   0.9696   0.0051
  -7.750  -0.2622   0.08001   0.07837  -0.0482   0.9566   0.0052
  -7.500  -0.2503   0.07581   0.07414  -0.0528   0.9443   0.0053
  -7.250  -0.2362   0.07138   0.06967  -0.0580   0.9329   0.0054
  -7.000  -0.2195   0.06615   0.06438  -0.0644   0.9221   0.0056
  -6.750  -0.1998   0.06126   0.05943  -0.0705   0.9116   0.0058
  -6.500  -0.1777   0.05675   0.05484  -0.0761   0.9021   0.0058
  -6.250  -0.1538   0.05270   0.05069  -0.0809   0.8933   0.0059
  -6.000  -0.1283   0.04887   0.04677  -0.0852   0.8845   0.0061
  -5.000  -0.0090   0.01111   0.00634  -0.1043   0.8548   0.0116
  -4.750   0.0183   0.01042   0.00551  -0.1043   0.8466   0.0126
  -4.500   0.0458   0.00960   0.00452  -0.1043   0.8380   0.0137
  -4.250   0.0738   0.00950   0.00438  -0.1042   0.8302   0.0148
  -4.000   0.1021   0.00972   0.00461  -0.1041   0.8215   0.0157
  -3.750   0.1302   0.00960   0.00443  -0.1041   0.8124   0.0168
  -3.500   0.1580   0.00916   0.00385  -0.1040   0.8031   0.0180
  -3.250   0.1861   0.00912   0.00377  -0.1040   0.7909   0.0187
  -3.000   0.2141   0.00933   0.00395  -0.1039   0.7753   0.0194
  -2.750   0.2418   0.00945   0.00399  -0.1037   0.7556   0.0202
  -2.500   0.2694   0.00932   0.00375  -0.1036   0.7317   0.0212
  -2.250   0.2959   0.00932   0.00353  -0.1032   0.6867   0.0224
  -2.000   0.3221   0.00941   0.00338  -0.1029   0.6410   0.0231
  -1.750   0.3492   0.00942   0.00324  -0.1027   0.6138   0.0234
  -1.500   0.3764   0.00906   0.00275  -0.1026   0.5925   0.0246
  -1.250   0.4037   0.00901   0.00260  -0.1026   0.5681   0.0252
  -1.000   0.4311   0.00899   0.00247  -0.1025   0.5449   0.0259
  -0.750   0.4587   0.00894   0.00234  -0.1024   0.5259   0.0266
  -0.500   0.4864   0.00891   0.00224  -0.1024   0.5089   0.0276
  -0.250   0.5140   0.00887   0.00211  -0.1023   0.4890   0.0283
   0.000   0.5413   0.00888   0.00201  -0.1023   0.4636   0.0290
   0.250   0.5681   0.00898   0.00195  -0.1021   0.4278   0.0295
   0.500   0.5947   0.00911   0.00191  -0.1020   0.3926   0.0299
   0.750   0.6217   0.00921   0.00189  -0.1019   0.3670   0.0302
   1.000   0.6488   0.00930   0.00189  -0.1018   0.3458   0.0305
   1.250   0.6756   0.00947   0.00194  -0.1016   0.3215   0.0309
   1.500   0.7027   0.00954   0.00190  -0.1015   0.3033   0.0320
   1.750   0.7301   0.00960   0.00191  -0.1015   0.2911   0.0337
   2.000   0.7577   0.00966   0.00195  -0.1015   0.2820   0.0357
   2.250   0.7850   0.00976   0.00201  -0.1014   0.2730   0.0376
   2.500   0.8124   0.00984   0.00207  -0.1013   0.2648   0.0398
   2.750   0.8396   0.00995   0.00215  -0.1013   0.2544   0.0438
   3.000   0.8666   0.01008   0.00225  -0.1012   0.2434   0.0567
   3.500   0.9147   0.00871   0.00269  -0.1003   0.2191   1.0000
   3.750   0.9410   0.00896   0.00284  -0.1001   0.2022   1.0000
   4.000   0.9670   0.00925   0.00301  -0.0998   0.1825   1.0000
   4.250   0.9920   0.00965   0.00325  -0.0995   0.1539   1.0000
   4.500   1.0165   0.01010   0.00355  -0.0990   0.1263   1.0000
   4.750   1.0424   0.01039   0.00377  -0.0988   0.1164   1.0000
   5.000   1.0687   0.01059   0.00395  -0.0986   0.1117   1.0000
   5.250   1.0947   0.01084   0.00418  -0.0984   0.1063   1.0000
   5.500   1.1207   0.01107   0.00439  -0.0981   0.1013   1.0000
   5.750   1.1467   0.01129   0.00460  -0.0979   0.0962   1.0000
   6.000   1.1719   0.01161   0.00487  -0.0976   0.0873   1.0000
   6.250   1.1924   0.01247   0.00545  -0.0966   0.0423   1.0000
   6.500   1.2171   0.01282   0.00578  -0.0961   0.0371   1.0000
   6.750   1.2422   0.01310   0.00607  -0.0958   0.0348   1.0000
   7.000   1.2673   0.01337   0.00638  -0.0954   0.0342   1.0000
   7.250   1.2921   0.01365   0.00668  -0.0951   0.0337   1.0000
   7.500   1.3167   0.01395   0.00702  -0.0946   0.0332   1.0000
   7.750   1.3410   0.01427   0.00737  -0.0942   0.0328   1.0000
   8.000   1.3650   0.01460   0.00774  -0.0937   0.0323   1.0000
   8.250   1.3885   0.01497   0.00813  -0.0931   0.0311   1.0000
   8.500   1.4112   0.01540   0.00858  -0.0924   0.0293   1.0000
   8.750   1.4337   0.01584   0.00905  -0.0917   0.0277   1.0000
   9.000   1.4557   0.01630   0.00957  -0.0909   0.0264   1.0000
   9.250   1.4780   0.01670   0.01001  -0.0902   0.0257   1.0000
   9.500   1.5009   0.01701   0.01036  -0.0896   0.0253   1.0000
   9.750   1.5234   0.01734   0.01074  -0.0889   0.0246   1.0000
  10.000   1.5453   0.01770   0.01115  -0.0882   0.0232   1.0000
  10.250   1.5661   0.01814   0.01160  -0.0873   0.0205   1.0000
  10.500   1.5853   0.01869   0.01214  -0.0862   0.0173   1.0000
  10.750   1.6026   0.01936   0.01276  -0.0848   0.0126   1.0000
  11.000   1.6185   0.02008   0.01349  -0.0831   0.0098   1.0000
  11.250   1.6335   0.02079   0.01424  -0.0813   0.0083   1.0000
  11.500   1.6456   0.02152   0.01503  -0.0789   0.0071   1.0000
  11.750   1.6576   0.02226   0.01583  -0.0766   0.0064   1.0000
  12.000   1.6680   0.02312   0.01675  -0.0742   0.0057   1.0000
  12.250   1.6783   0.02401   0.01771  -0.0719   0.0052   1.0000
  12.500   1.6889   0.02490   0.01869  -0.0698   0.0049   1.0000
  12.750   1.6983   0.02591   0.01977  -0.0676   0.0045   1.0000
  13.000   1.7063   0.02704   0.02098  -0.0654   0.0042   1.0000
  13.250   1.7128   0.02832   0.02234  -0.0632   0.0040   1.0000
  13.500   1.7175   0.02981   0.02393  -0.0610   0.0037   1.0000
  13.750   1.7236   0.03122   0.02544  -0.0591   0.0036   1.0000
  14.000   1.7287   0.03280   0.02712  -0.0573   0.0035   1.0000
  14.250   1.7324   0.03456   0.02898  -0.0557   0.0033   1.0000
  14.500   1.7346   0.03652   0.03104  -0.0541   0.0032   1.0000
  14.750   1.7358   0.03869   0.03332  -0.0527   0.0031   1.0000
  15.000   1.7354   0.04111   0.03585  -0.0515   0.0030   1.0000
  15.250   1.7330   0.04386   0.03871  -0.0505   0.0029   1.0000
  15.500   1.7291   0.04697   0.04194  -0.0499   0.0028   1.0000
  15.750   1.7231   0.05053   0.04562  -0.0496   0.0027   1.0000
  16.000   1.7146   0.05464   0.04986  -0.0499   0.0026   1.0000
  16.250   1.7036   0.05943   0.05478  -0.0507   0.0025   1.0000
  16.500   1.6907   0.06474   0.06024  -0.0519   0.0024   1.0000
  16.750   1.6781   0.07014   0.06578  -0.0534   0.0024   1.0000
  17.000   1.6632   0.07607   0.07186  -0.0553   0.0024   1.0000
  17.250   1.6471   0.08236   0.07828  -0.0574   0.0024   1.0000
  17.500   1.6273   0.08937   0.08544  -0.0599   0.0024   1.0000
  17.750   1.6064   0.09673   0.09295  -0.0627   0.0024   1.0000
  18.000   1.5844   0.10446   0.10082  -0.0658   0.0024   1.0000
  18.250   1.5617   0.11237   0.10886  -0.0691   0.0024   1.0000
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