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AG25 Bubble Dancer DLG by Mark Drela (ag25-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: AG25 Bubble Dancer DLG by Mark Drela (ag25-il)
Reynolds number: 50,000
Max Cl/Cd: 38.95 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag25-il-50000-n5.txt
Download as CSV file: xf-ag25-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG25 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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3923   0.09154   0.08510  -0.0181   1.0000   0.0525
  -8.250  -0.4920   0.09819   0.09155  -0.0158   1.0000   0.0539
  -8.000  -0.4786   0.09452   0.08782  -0.0130   1.0000   0.0516
  -7.750  -0.4737   0.09062   0.08397  -0.0143   1.0000   0.0497
  -7.500  -0.4696   0.08634   0.07976  -0.0171   1.0000   0.0478
  -7.250  -0.4640   0.08134   0.07483  -0.0217   1.0000   0.0459
  -6.750  -0.4447   0.06627   0.05958  -0.0399   1.0000   0.0407
  -6.500  -0.4334   0.06150   0.05473  -0.0427   1.0000   0.0402
  -6.250  -0.4203   0.05651   0.04959  -0.0459   1.0000   0.0398
  -6.000  -0.4048   0.05148   0.04431  -0.0490   1.0000   0.0395
  -5.750  -0.3868   0.04660   0.03907  -0.0516   1.0000   0.0393
  -5.500  -0.3662   0.04200   0.03394  -0.0537   1.0000   0.0394
  -5.250  -0.3433   0.03785   0.02920  -0.0551   1.0000   0.0399
  -5.000  -0.3198   0.03436   0.02520  -0.0559   1.0000   0.0422
  -4.750  -0.2972   0.03215   0.02280  -0.0561   1.0000   0.0462
  -4.500  -0.2718   0.02953   0.01970  -0.0560   1.0000   0.0489
  -4.250  -0.2458   0.02716   0.01684  -0.0555   1.0000   0.0515
  -4.000  -0.2210   0.02524   0.01468  -0.0550   1.0000   0.0565
  -3.750  -0.1961   0.02388   0.01305  -0.0543   1.0000   0.0662
  -3.500  -0.1718   0.02236   0.01145  -0.0536   1.0000   0.0752
  -3.250  -0.1468   0.02116   0.01019  -0.0532   1.0000   0.0964
  -3.000  -0.1200   0.01984   0.00897  -0.0532   1.0000   0.1364
  -2.750  -0.0927   0.01844   0.00814  -0.0538   1.0000   0.2434
  -2.500  -0.0678   0.01750   0.00781  -0.0537   1.0000   0.3922
  -2.250  -0.0455   0.01685   0.00760  -0.0526   1.0000   0.5211
  -2.000  -0.0264   0.01629   0.00737  -0.0503   1.0000   0.6377
  -1.750  -0.0123   0.01573   0.00717  -0.0466   1.0000   0.7665
  -1.500   0.0070   0.01525   0.00676  -0.0445   1.0000   1.0000
  -1.250   0.0336   0.01540   0.00653  -0.0451   1.0000   1.0000
  -1.000   0.0593   0.01558   0.00641  -0.0454   1.0000   1.0000
  -0.750   0.0845   0.01581   0.00634  -0.0457   1.0000   1.0000
  -0.500   0.1139   0.01608   0.00638  -0.0468   0.9969   1.0000
  -0.250   0.1598   0.01638   0.00645  -0.0510   0.9833   1.0000
   0.000   0.2051   0.01665   0.00652  -0.0549   0.9690   1.0000
   0.250   0.2488   0.01688   0.00661  -0.0584   0.9538   1.0000
   0.500   0.2914   0.01708   0.00671  -0.0614   0.9377   1.0000
   0.750   0.3324   0.01724   0.00680  -0.0640   0.9207   1.0000
   1.000   0.3716   0.01735   0.00688  -0.0660   0.9031   1.0000
   1.250   0.4092   0.01744   0.00694  -0.0676   0.8850   1.0000
   1.500   0.4420   0.01753   0.00706  -0.0681   0.8639   1.0000
   1.750   0.4756   0.01759   0.00711  -0.0686   0.8438   1.0000
   2.000   0.5053   0.01768   0.00721  -0.0683   0.8205   1.0000
   2.250   0.5343   0.01777   0.00731  -0.0678   0.7969   1.0000
   2.500   0.5626   0.01787   0.00741  -0.0671   0.7726   1.0000
   2.750   0.5899   0.01798   0.00757  -0.0661   0.7472   1.0000
   3.000   0.6162   0.01813   0.00773  -0.0650   0.7201   1.0000
   3.250   0.6419   0.01832   0.00790  -0.0639   0.6919   1.0000
   3.500   0.6671   0.01856   0.00814  -0.0627   0.6620   1.0000
   3.750   0.6921   0.01883   0.00847  -0.0615   0.6312   1.0000
   4.000   0.7168   0.01914   0.00877  -0.0603   0.5999   1.0000
   4.250   0.7414   0.01949   0.00910  -0.0591   0.5682   1.0000
   4.500   0.7659   0.01992   0.00952  -0.0581   0.5348   1.0000
   4.750   0.7902   0.02039   0.00998  -0.0570   0.5016   1.0000
   5.000   0.8142   0.02092   0.01056  -0.0560   0.4681   1.0000
   5.250   0.8378   0.02151   0.01117  -0.0551   0.4339   1.0000
   5.500   0.8611   0.02216   0.01180  -0.0541   0.4004   1.0000
   5.750   0.8841   0.02287   0.01255  -0.0532   0.3659   1.0000
   6.000   0.9064   0.02366   0.01332  -0.0522   0.3328   1.0000
   6.250   0.9285   0.02452   0.01430  -0.0513   0.2987   1.0000
   6.500   0.9498   0.02547   0.01526  -0.0504   0.2659   1.0000
   6.750   0.9705   0.02653   0.01633  -0.0495   0.2333   1.0000
   7.000   0.9905   0.02770   0.01754  -0.0486   0.2012   1.0000
   7.250   1.0095   0.02903   0.01886  -0.0476   0.1712   1.0000
   7.500   1.0277   0.03055   0.02039  -0.0466   0.1439   1.0000
   7.750   1.0449   0.03222   0.02209  -0.0455   0.1185   1.0000
   8.000   1.0613   0.03415   0.02414  -0.0443   0.0987   1.0000
   8.250   1.0769   0.03620   0.02632  -0.0431   0.0818   1.0000
   8.500   1.0919   0.03845   0.02871  -0.0417   0.0692   1.0000
   8.750   1.1058   0.04085   0.03127  -0.0404   0.0594   1.0000
   9.000   1.1194   0.04343   0.03396  -0.0391   0.0532   1.0000
   9.250   1.1316   0.04642   0.03736  -0.0376   0.0471   1.0000
   9.500   1.1408   0.04904   0.04018  -0.0364   0.0425   1.0000
   9.750   1.1490   0.05261   0.04389  -0.0350   0.0402   1.0000
  10.000   1.1513   0.05672   0.04858  -0.0335   0.0388   1.0000
  10.250   1.1469   0.06090   0.05325  -0.0321   0.0375   1.0000
  10.500   1.1360   0.06497   0.05768  -0.0308   0.0366   1.0000
  10.750   1.1215   0.06943   0.06243  -0.0304   0.0361   1.0000
  11.000   1.1040   0.07461   0.06788  -0.0315   0.0359   1.0000
  11.250   1.0842   0.08078   0.07428  -0.0343   0.0363   1.0000
  11.500   1.0630   0.08807   0.08176  -0.0386   0.0370   1.0000
  11.750   1.0420   0.09630   0.09012  -0.0441   0.0379   1.0000
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