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AG27 Bubble Dancer DLG by Mark Drela (ag27-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: AG27 Bubble Dancer DLG by Mark Drela (ag27-il)
Reynolds number: 200,000
Max Cl/Cd: 71.72 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-ag27-il-200000.txt
Download as CSV file: xf-ag27-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG27 Bubble Dancer DLG by Mark Drela            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.4837   0.09872   0.09530   0.0041   1.0000   0.0336
  -7.750  -0.4788   0.09535   0.09198   0.0010   1.0000   0.0349
  -7.500  -0.4738   0.09220   0.08888  -0.0046   1.0000   0.0359
  -7.250  -0.4597   0.08813   0.08483  -0.0133   1.0000   0.0365
  -7.000  -0.4427   0.08358   0.08028  -0.0205   1.0000   0.0367
  -6.750  -0.4303   0.07713   0.07385  -0.0267   1.0000   0.0371
  -6.500  -0.4283   0.07303   0.06977  -0.0234   1.0000   0.0383
  -6.250  -0.4161   0.06990   0.06664  -0.0236   1.0000   0.0396
  -6.000  -0.3999   0.06619   0.06293  -0.0266   1.0000   0.0412
  -5.750  -0.3799   0.06185   0.05856  -0.0315   1.0000   0.0434
  -5.500  -0.3497   0.05605   0.05262  -0.0405   1.0000   0.0474
  -5.250  -0.3171   0.04792   0.04410  -0.0507   1.0000   0.0502
  -5.000  -0.3024   0.04515   0.04143  -0.0500   1.0000   0.0519
  -4.750  -0.2822   0.04231   0.03854  -0.0509   1.0000   0.0546
  -4.500  -0.2486   0.03695   0.03251  -0.0561   1.0000   0.0634
  -4.250  -0.2298   0.03405   0.02972  -0.0559   1.0000   0.0658
  -4.000  -0.2059   0.03145   0.02694  -0.0564   1.0000   0.0708
  -3.750  -0.1636   0.02149   0.01562  -0.0583   1.0000   0.0321
  -3.500  -0.1365   0.01930   0.01296  -0.0580   1.0000   0.0338
  -3.250  -0.1094   0.01735   0.01060  -0.0575   1.0000   0.0347
  -3.000  -0.0820   0.01557   0.00849  -0.0571   1.0000   0.0350
  -2.750  -0.0552   0.01441   0.00713  -0.0565   1.0000   0.0366
  -2.500  -0.0274   0.01287   0.00558  -0.0566   1.0000   0.0434
  -2.250   0.0005   0.01193   0.00463  -0.0565   1.0000   0.0547
  -2.000   0.0289   0.01116   0.00393  -0.0568   1.0000   0.0849
  -1.750   0.0592   0.01015   0.00350  -0.0578   1.0000   0.2109
  -1.500   0.0877   0.00955   0.00349  -0.0586   1.0000   0.3757
  -1.250   0.1159   0.00904   0.00353  -0.0591   1.0000   0.5358
  -1.000   0.1473   0.00788   0.00342  -0.0590   0.9941   1.0000
  -0.750   0.1938   0.00792   0.00326  -0.0629   0.9839   1.0000
  -0.500   0.2388   0.00792   0.00311  -0.0664   0.9731   1.0000
  -0.250   0.2815   0.00790   0.00297  -0.0693   0.9610   1.0000
   0.000   0.3204   0.00786   0.00284  -0.0712   0.9465   1.0000
   0.250   0.3552   0.00782   0.00273  -0.0722   0.9298   1.0000
   0.500   0.3852   0.00781   0.00263  -0.0720   0.9099   1.0000
   0.750   0.4120   0.00782   0.00256  -0.0711   0.8879   1.0000
   1.000   0.4373   0.00786   0.00252  -0.0699   0.8639   1.0000
   1.250   0.4622   0.00793   0.00248  -0.0686   0.8388   1.0000
   1.500   0.4871   0.00802   0.00248  -0.0674   0.8125   1.0000
   1.750   0.5122   0.00814   0.00249  -0.0663   0.7849   1.0000
   2.000   0.5376   0.00829   0.00251  -0.0653   0.7560   1.0000
   2.250   0.5632   0.00845   0.00256  -0.0644   0.7258   1.0000
   2.500   0.5888   0.00865   0.00263  -0.0635   0.6946   1.0000
   2.750   0.6145   0.00887   0.00274  -0.0627   0.6623   1.0000
   3.000   0.6403   0.00910   0.00286  -0.0621   0.6278   1.0000
   3.250   0.6660   0.00938   0.00299  -0.0614   0.5919   1.0000
   3.500   0.6916   0.00967   0.00316  -0.0607   0.5533   1.0000
   3.750   0.7172   0.01000   0.00338  -0.0601   0.5122   1.0000
   4.000   0.7425   0.01038   0.00360  -0.0596   0.4689   1.0000
   4.250   0.7678   0.01080   0.00386  -0.0590   0.4233   1.0000
   4.500   0.7928   0.01129   0.00417  -0.0585   0.3749   1.0000
   4.750   0.8176   0.01184   0.00456  -0.0581   0.3272   1.0000
   5.000   0.8423   0.01245   0.00498  -0.0576   0.2795   1.0000
   5.250   0.8668   0.01311   0.00547  -0.0572   0.2378   1.0000
   5.500   0.8911   0.01384   0.00603  -0.0568   0.2042   1.0000
   5.750   0.9155   0.01455   0.00664  -0.0563   0.1758   1.0000
   6.000   0.9399   0.01528   0.00733  -0.0559   0.1531   1.0000
   6.250   0.9641   0.01605   0.00807  -0.0554   0.1338   1.0000
   6.500   0.9883   0.01679   0.00882  -0.0549   0.1169   1.0000
   6.750   1.0122   0.01759   0.00963  -0.0543   0.1021   1.0000
   7.000   1.0358   0.01843   0.01050  -0.0537   0.0885   1.0000
   7.250   1.0590   0.01934   0.01146  -0.0531   0.0759   1.0000
   7.500   1.0818   0.02031   0.01252  -0.0524   0.0638   1.0000
   7.750   1.1040   0.02138   0.01366  -0.0517   0.0525   1.0000
   8.000   1.1248   0.02286   0.01525  -0.0507   0.0433   1.0000
   8.250   1.1443   0.02454   0.01697  -0.0497   0.0354   1.0000
   8.500   1.1652   0.02599   0.01861  -0.0486   0.0301   1.0000
   8.750   1.1816   0.02861   0.02139  -0.0472   0.0258   1.0000
   9.000   1.2009   0.03038   0.02346  -0.0460   0.0229   1.0000
   9.250   1.2177   0.03267   0.02606  -0.0447   0.0210   1.0000
   9.500   1.2317   0.03537   0.02899  -0.0433   0.0197   1.0000
   9.750   1.2398   0.03945   0.03345  -0.0415   0.0189   1.0000
  10.000   1.2392   0.04469   0.03919  -0.0395   0.0185   1.0000
  10.500   1.2267   0.05303   0.04841  -0.0355   0.0178   1.0000
  10.750   1.2154   0.05626   0.05194  -0.0334   0.0175   1.0000
  11.000   1.1983   0.06031   0.05625  -0.0325   0.0175   1.0000
  11.250   1.1787   0.06542   0.06159  -0.0336   0.0176   1.0000
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