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GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il)
Reynolds number: 500,000
Max Cl/Cd: 97.57 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe276-il-500000.txt
Download as CSV file: xf-goe276-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 276 (DAIMLER VII) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3913   0.09996   0.09769  -0.0204   1.0000   0.0176
  -8.250  -0.3940   0.09715   0.09492  -0.0214   1.0000   0.0176
  -8.000  -0.3953   0.09416   0.09197  -0.0225   1.0000   0.0176
  -7.750  -0.3908   0.09061   0.08844  -0.0251   1.0000   0.0177
  -7.500  -0.3897   0.08628   0.08414  -0.0242   1.0000   0.0179
  -7.250  -0.3846   0.08345   0.08133  -0.0229   1.0000   0.0181
  -7.000  -0.3795   0.08071   0.07862  -0.0231   1.0000   0.0183
  -6.750  -0.3746   0.07798   0.07591  -0.0239   1.0000   0.0186
  -6.500  -0.3718   0.07547   0.07343  -0.0242   1.0000   0.0190
  -6.250  -0.3562   0.07203   0.06998  -0.0280   0.9987   0.0199
  -6.000  -0.3096   0.06589   0.06372  -0.0413   0.9957   0.0220
  -5.750  -0.2600   0.05919   0.05683  -0.0537   0.9929   0.0224
  -5.500  -0.2227   0.05364   0.05111  -0.0604   0.9896   0.0225
  -5.250  -0.2011   0.04776   0.04520  -0.0646   0.9869   0.0232
  -5.000  -0.1710   0.04509   0.04249  -0.0679   0.9847   0.0240
  -4.750  -0.1368   0.04181   0.03910  -0.0720   0.9801   0.0256
  -4.500  -0.0850   0.03839   0.03526  -0.0771   0.9760   0.0288
  -4.250  -0.0460   0.03491   0.03148  -0.0806   0.9731   0.0289
  -4.000  -0.0180   0.02904   0.02549  -0.0845   0.9682   0.0304
  -3.750   0.0135   0.02711   0.02348  -0.0865   0.9620   0.0315
  -3.500   0.0481   0.02509   0.02128  -0.0886   0.9559   0.0336
  -3.250   0.0873   0.02507   0.02091  -0.0893   0.9477   0.0375
  -3.000   0.1215   0.02047   0.01593  -0.0920   0.9393   0.0392
  -2.750   0.1534   0.01893   0.01433  -0.0935   0.9299   0.0407
  -2.500   0.1840   0.01781   0.01306  -0.0942   0.9188   0.0430
  -2.250   0.2142   0.01728   0.01230  -0.0942   0.9068   0.0471
  -2.000   0.2440   0.01597   0.01062  -0.0943   0.8953   0.0508
  -1.750   0.2711   0.01486   0.00948  -0.0945   0.8831   0.0532
  -1.500   0.2984   0.01431   0.00881  -0.0942   0.8682   0.0574
  -1.250   0.3261   0.01552   0.00980  -0.0932   0.8503   0.0623
  -1.000   0.3532   0.01293   0.00713  -0.0937   0.8337   0.0689
  -0.500   0.4107   0.01156   0.00527  -0.0922   0.7964   0.0501
  -0.250   0.4377   0.01083   0.00446  -0.0917   0.7665   0.0471
   0.000   0.4633   0.01046   0.00385  -0.0909   0.7050   0.0463
   0.250   0.4864   0.01052   0.00339  -0.0898   0.6006   0.0450
   0.500   0.5114   0.01060   0.00312  -0.0892   0.5271   0.0447
   0.750   0.5380   0.01062   0.00293  -0.0890   0.4889   0.0452
   1.000   0.5654   0.01060   0.00279  -0.0889   0.4683   0.0463
   1.250   0.5930   0.01060   0.00270  -0.0888   0.4538   0.0473
   1.500   0.6207   0.01062   0.00266  -0.0888   0.4427   0.0485
   1.750   0.6485   0.01061   0.00259  -0.0888   0.4331   0.0514
   2.000   0.6764   0.01063   0.00258  -0.0888   0.4243   0.0556
   2.250   0.7040   0.01071   0.00261  -0.0887   0.4163   0.0670
   2.500   0.7256   0.00879   0.00276  -0.0878   0.4099   1.0000
   2.750   0.7531   0.00897   0.00285  -0.0877   0.4026   1.0000
   3.000   0.7809   0.00910   0.00296  -0.0877   0.3952   1.0000
   3.250   0.8082   0.00929   0.00307  -0.0876   0.3865   1.0000
   3.500   0.8360   0.00939   0.00318  -0.0876   0.3785   1.0000
   3.750   0.8632   0.00957   0.00331  -0.0875   0.3704   1.0000
   4.000   0.8909   0.00968   0.00344  -0.0874   0.3615   1.0000
   4.250   0.9183   0.00984   0.00358  -0.0874   0.3528   1.0000
   4.500   0.9455   0.01000   0.00372  -0.0873   0.3429   1.0000
   4.750   0.9729   0.01014   0.00388  -0.0872   0.3320   1.0000
   5.000   0.9999   0.01031   0.00403  -0.0871   0.3173   1.0000
   5.500   1.0528   0.01079   0.00439  -0.0867   0.2806   1.0000
   5.750   1.0786   0.01111   0.00464  -0.0865   0.2589   1.0000
   6.000   1.1039   0.01150   0.00492  -0.0862   0.2351   1.0000
   6.250   1.1291   0.01190   0.00523  -0.0858   0.2148   1.0000
   6.500   1.1543   0.01229   0.00556  -0.0855   0.1939   1.0000
   6.750   1.1787   0.01279   0.00595  -0.0851   0.1648   1.0000
   7.000   1.2015   0.01352   0.00645  -0.0845   0.1299   1.0000
   7.250   1.2242   0.01426   0.00704  -0.0838   0.1016   1.0000
   7.500   1.2399   0.01601   0.00827  -0.0822   0.0266   1.0000
   7.750   1.2620   0.01683   0.00913  -0.0813   0.0209   1.0000
   8.000   1.2849   0.01746   0.00985  -0.0805   0.0191   1.0000
   8.250   1.3065   0.01822   0.01070  -0.0795   0.0175   1.0000
   8.500   1.3259   0.01924   0.01182  -0.0782   0.0162   1.0000
   8.750   1.3420   0.02057   0.01331  -0.0764   0.0153   1.0000
   9.000   1.3611   0.02145   0.01430  -0.0751   0.0148   1.0000
   9.250   1.3783   0.02247   0.01543  -0.0735   0.0143   1.0000
   9.500   1.3943   0.02353   0.01660  -0.0717   0.0137   1.0000
   9.750   1.4093   0.02463   0.01778  -0.0699   0.0130   1.0000
  10.000   1.4221   0.02583   0.01906  -0.0678   0.0124   1.0000
  10.250   1.4309   0.02731   0.02063  -0.0651   0.0120   1.0000
  10.500   1.4349   0.02908   0.02250  -0.0618   0.0117   1.0000
  10.750   1.4328   0.03128   0.02480  -0.0576   0.0114   1.0000
  11.000   1.4310   0.03395   0.02760  -0.0537   0.0112   1.0000
  11.250   1.4369   0.03534   0.02912  -0.0510   0.0110   1.0000
  11.500   1.4419   0.03691   0.03084  -0.0485   0.0109   1.0000
  11.750   1.4456   0.03877   0.03285  -0.0460   0.0108   1.0000
  12.000   1.4479   0.04089   0.03513  -0.0438   0.0106   1.0000
  12.250   1.4487   0.04327   0.03767  -0.0417   0.0105   1.0000
  12.500   1.4479   0.04594   0.04053  -0.0399   0.0104   1.0000
  12.750   1.4454   0.04886   0.04362  -0.0383   0.0103   1.0000
  13.000   1.4412   0.05202   0.04698  -0.0371   0.0102   1.0000
  13.250   1.4355   0.05549   0.05063  -0.0364   0.0101   1.0000
  13.500   1.4282   0.05925   0.05457  -0.0361   0.0099   1.0000
  13.750   1.4190   0.06356   0.05907  -0.0364   0.0098   1.0000
  14.000   1.4090   0.06817   0.06386  -0.0374   0.0097   1.0000
  14.250   1.3983   0.07318   0.06904  -0.0390   0.0096   1.0000
  14.500   1.3842   0.07908   0.07514  -0.0412   0.0096   1.0000
  14.750   1.3695   0.08531   0.08155  -0.0440   0.0096   1.0000
  15.000   1.3539   0.09204   0.08846  -0.0473   0.0096   1.0000
  15.250   1.3369   0.09936   0.09597  -0.0512   0.0097   1.0000
  15.500   1.3188   0.10706   0.10384  -0.0553   0.0097   1.0000
  15.750   1.3004   0.11509   0.11203  -0.0598   0.0098   1.0000
  16.000   1.2820   0.12346   0.12057  -0.0647   0.0099   1.0000
  16.250   1.2632   0.13228   0.12953  -0.0701   0.0100   1.0000
  16.500   1.2448   0.14146   0.13885  -0.0758   0.0101   1.0000
  16.750   1.2261   0.15135   0.14888  -0.0821   0.0103   1.0000
  17.000   1.2074   0.16183   0.15949  -0.0888   0.0105   1.0000
  17.250   1.1868   0.17340   0.17116  -0.0962   0.0107   1.0000
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