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GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il)
Reynolds number: 500,000
Max Cl/Cd: 95.86 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe278-il-500000.txt
Download as CSV file: xf-goe278-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 278 (DAIMLER IX) AIRFOIL                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3635   0.09112   0.08892  -0.0261   1.0000   0.0186
  -7.750  -0.3736   0.08927   0.08713  -0.0256   1.0000   0.0186
  -7.500  -0.3853   0.08763   0.08554  -0.0243   1.0000   0.0186
  -7.250  -0.3733   0.08344   0.08134  -0.0301   0.9982   0.0187
  -7.000  -0.3504   0.07738   0.07525  -0.0370   0.9955   0.0188
  -6.750  -0.3335   0.07370   0.07158  -0.0376   0.9939   0.0191
  -6.500  -0.3096   0.06985   0.06770  -0.0421   0.9903   0.0195
  -6.250  -0.2794   0.06555   0.06336  -0.0488   0.9870   0.0201
  -6.000  -0.2442   0.06080   0.05854  -0.0567   0.9845   0.0212
  -5.750  -0.1901   0.05450   0.05195  -0.0698   0.9788   0.0230
  -5.500  -0.1581   0.04834   0.04563  -0.0756   0.9755   0.0232
  -5.250  -0.1322   0.04486   0.04214  -0.0787   0.9734   0.0237
  -5.000  -0.1011   0.04194   0.03915  -0.0821   0.9711   0.0243
  -4.750  -0.0747   0.03922   0.03633  -0.0840   0.9643   0.0253
  -4.500  -0.0300   0.03645   0.03314  -0.0870   0.9598   0.0284
  -4.250  -0.0031   0.03165   0.02805  -0.0887   0.9533   0.0289
  -4.000   0.0199   0.02912   0.02549  -0.0895   0.9458   0.0295
  -3.750   0.0442   0.02736   0.02365  -0.0897   0.9379   0.0303
  -3.500   0.0698   0.02569   0.02184  -0.0898   0.9306   0.0316
  -3.250   0.1019   0.02545   0.02126  -0.0890   0.9237   0.0355
  -3.000   0.1261   0.02169   0.01718  -0.0890   0.9164   0.0366
  -2.750   0.1507   0.02019   0.01563  -0.0891   0.9091   0.0376
  -2.500   0.1761   0.01908   0.01442  -0.0888   0.9009   0.0391
  -2.250   0.2027   0.01811   0.01330  -0.0884   0.8924   0.0417
  -2.000   0.2306   0.01693   0.01174  -0.0877   0.8837   0.0465
  -1.750   0.2560   0.01580   0.01060  -0.0875   0.8732   0.0483
  -1.500   0.2825   0.01507   0.00977  -0.0871   0.8632   0.0513
  -1.250   0.3101   0.01449   0.00889  -0.0865   0.8526   0.0586
  -1.000   0.3361   0.01351   0.00793  -0.0863   0.8399   0.0615
  -0.750   0.3632   0.01328   0.00758  -0.0859   0.8258   0.0677
  -0.500   0.3895   0.01236   0.00657  -0.0856   0.8099   0.0755
   0.000   0.4454   0.01049   0.00421  -0.0835   0.7676   0.0458
   0.250   0.4713   0.01011   0.00371  -0.0828   0.7359   0.0445
   0.500   0.4964   0.00971   0.00314  -0.0820   0.6986   0.0441
   0.750   0.5215   0.00954   0.00280  -0.0813   0.6635   0.0441
   1.000   0.5469   0.00957   0.00268  -0.0807   0.6330   0.0449
   1.250   0.5725   0.00949   0.00247  -0.0802   0.6050   0.0450
   1.500   0.5982   0.00940   0.00226  -0.0797   0.5762   0.0454
   1.750   0.6240   0.00935   0.00208  -0.0793   0.5454   0.0468
   2.000   0.6498   0.00943   0.00203  -0.0788   0.5106   0.0492
   2.250   0.6749   0.00964   0.00204  -0.0783   0.4688   0.0524
   2.750   0.7249   0.00816   0.00234  -0.0777   0.4093   1.0000
   3.000   0.7509   0.00840   0.00244  -0.0774   0.3930   1.0000
   3.250   0.7768   0.00864   0.00257  -0.0770   0.3772   1.0000
   3.500   0.8029   0.00886   0.00270  -0.0767   0.3634   1.0000
   3.750   0.8290   0.00908   0.00285  -0.0764   0.3525   1.0000
   4.000   0.8551   0.00929   0.00302  -0.0761   0.3429   1.0000
   4.250   0.8816   0.00946   0.00317  -0.0759   0.3341   1.0000
   4.500   0.9076   0.00969   0.00335  -0.0756   0.3247   1.0000
   4.750   0.9336   0.00990   0.00353  -0.0753   0.3124   1.0000
   5.000   0.9599   0.01007   0.00370  -0.0751   0.3009   1.0000
   5.250   0.9859   0.01029   0.00389  -0.0748   0.2864   1.0000
   5.500   1.0113   0.01055   0.00407  -0.0745   0.2630   1.0000
   5.750   1.0340   0.01115   0.00436  -0.0738   0.2003   1.0000
   6.000   1.0476   0.01293   0.00535  -0.0720   0.0713   1.0000
   6.250   1.0699   0.01364   0.00596  -0.0711   0.0516   1.0000
   6.500   1.0935   0.01415   0.00648  -0.0705   0.0472   1.0000
   6.750   1.1163   0.01475   0.00714  -0.0697   0.0436   1.0000
   7.000   1.1396   0.01526   0.00771  -0.0690   0.0423   1.0000
   7.250   1.1628   0.01575   0.00827  -0.0683   0.0407   1.0000
   7.500   1.1850   0.01633   0.00891  -0.0675   0.0390   1.0000
   7.750   1.2063   0.01698   0.00963  -0.0666   0.0373   1.0000
   8.000   1.2252   0.01786   0.01056  -0.0653   0.0353   1.0000
   8.250   1.2385   0.01929   0.01210  -0.0632   0.0333   1.0000
   8.500   1.2601   0.01980   0.01268  -0.0623   0.0325   1.0000
   8.750   1.2801   0.02043   0.01339  -0.0612   0.0312   1.0000
   9.000   1.2991   0.02114   0.01417  -0.0600   0.0296   1.0000
   9.250   1.3163   0.02197   0.01504  -0.0586   0.0282   1.0000
   9.500   1.3295   0.02315   0.01625  -0.0567   0.0269   1.0000
   9.750   1.3352   0.02525   0.01844  -0.0537   0.0254   1.0000
  10.000   1.3541   0.02563   0.01893  -0.0525   0.0245   1.0000
  10.250   1.3684   0.02634   0.01973  -0.0507   0.0233   1.0000
  10.500   1.3806   0.02721   0.02067  -0.0486   0.0223   1.0000
  10.750   1.3919   0.02814   0.02166  -0.0466   0.0214   1.0000
  11.000   1.4010   0.02928   0.02283  -0.0445   0.0206   1.0000
  11.250   1.4024   0.03197   0.02559  -0.0416   0.0196   1.0000
  11.500   1.4129   0.03275   0.02652  -0.0398   0.0191   1.0000
  11.750   1.4221   0.03386   0.02776  -0.0381   0.0183   1.0000
  12.000   1.4301   0.03516   0.02917  -0.0364   0.0175   1.0000
  12.250   1.4369   0.03662   0.03073  -0.0349   0.0169   1.0000
  12.500   1.4430   0.03815   0.03235  -0.0335   0.0164   1.0000
  12.750   1.4481   0.03984   0.03413  -0.0323   0.0160   1.0000
  13.000   1.4509   0.04192   0.03627  -0.0311   0.0156   1.0000
  13.250   1.4455   0.04547   0.03995  -0.0291   0.0150   1.0000
  13.500   1.4466   0.04785   0.04251  -0.0283   0.0148   1.0000
  13.750   1.4458   0.05062   0.04546  -0.0277   0.0145   1.0000
  14.000   1.4434   0.05370   0.04873  -0.0273   0.0141   1.0000
  14.250   1.4397   0.05707   0.05226  -0.0272   0.0138   1.0000
  14.500   1.4350   0.06069   0.05605  -0.0275   0.0135   1.0000
  14.750   1.4306   0.06439   0.05989  -0.0283   0.0132   1.0000
  15.000   1.4242   0.06849   0.06414  -0.0294   0.0130   1.0000
  15.250   1.4173   0.07284   0.06862  -0.0309   0.0127   1.0000
  15.500   1.4110   0.07728   0.07320  -0.0327   0.0125   1.0000
  15.750   1.4038   0.08202   0.07805  -0.0346   0.0124   1.0000
  16.000   1.3947   0.08717   0.08333  -0.0368   0.0122   1.0000
  16.250   1.3857   0.09247   0.08874  -0.0392   0.0121   1.0000
  16.500   1.3741   0.09837   0.09478  -0.0419   0.0120   1.0000
  16.750   1.3612   0.10462   0.10117  -0.0449   0.0119   1.0000
  17.000   1.3462   0.11144   0.10813  -0.0482   0.0118   1.0000
  17.250   1.3296   0.11883   0.11568  -0.0521   0.0118   1.0000
  17.500   1.3111   0.12692   0.12393  -0.0565   0.0118   1.0000
  17.750   1.2909   0.13568   0.13286  -0.0616   0.0118   1.0000
  18.000   1.2649   0.14641   0.14381  -0.0681   0.0119   1.0000
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