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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 200,000
Max Cl/Cd: 63.73 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du8608418-il-200000.txt
Download as CSV file: xf-du8608418-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: DU86-084/18 8.44%                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5341   0.08920   0.08606  -0.0188   1.0000   0.0397
  -8.750  -0.5349   0.08480   0.08170  -0.0218   1.0000   0.0407
  -8.500  -0.5385   0.07996   0.07691  -0.0260   1.0000   0.0417
  -8.250  -0.5471   0.07477   0.07175  -0.0309   1.0000   0.0419
  -8.000  -0.5554   0.07033   0.06729  -0.0336   1.0000   0.0424
  -7.750  -0.5627   0.06568   0.06255  -0.0355   1.0000   0.0439
  -7.500  -0.5750   0.06236   0.05910  -0.0344   1.0000   0.0452
  -7.250  -0.5952   0.06135   0.05774  -0.0302   1.0000   0.0467
  -5.500  -0.5225   0.03115   0.02509  -0.0233   0.9861   0.0355
  -5.250  -0.4971   0.02791   0.02159  -0.0232   0.9845   0.0333
  -5.000  -0.4720   0.02401   0.01721  -0.0227   0.9831   0.0304
  -4.750  -0.4471   0.02152   0.01429  -0.0217   0.9815   0.0288
  -4.500  -0.4216   0.01961   0.01208  -0.0208   0.9798   0.0285
  -4.250  -0.3955   0.01819   0.01049  -0.0202   0.9780   0.0295
  -4.000  -0.3685   0.01701   0.00921  -0.0199   0.9761   0.0322
  -3.750  -0.3419   0.01583   0.00796  -0.0198   0.9743   0.0383
  -3.500  -0.3135   0.01481   0.00692  -0.0200   0.9723   0.0504
  -3.250  -0.2866   0.01318   0.00598  -0.0204   0.9706   0.1726
  -3.000  -0.2662   0.01192   0.00578  -0.0200   0.9682   0.4054
  -2.750  -0.2523   0.01086   0.00571  -0.0175   0.9649   0.6236
  -2.500  -0.2396   0.01114   0.00676  -0.0119   0.9618   0.8566
  -2.250  -0.2204   0.01168   0.00716  -0.0089   0.9583   0.9157
  -2.000  -0.1621   0.01223   0.00754  -0.0132   0.9592   0.9523
  -1.750  -0.0603   0.01236   0.00739  -0.0275   0.9647   0.9717
  -1.500   0.0193   0.01217   0.00703  -0.0380   0.9675   0.9845
  -1.250   0.0900   0.01185   0.00660  -0.0469   0.9691   0.9947
  -1.000   0.1424   0.01158   0.00623  -0.0524   0.9674   1.0000
  -0.750   0.1809   0.01146   0.00606  -0.0550   0.9626   1.0000
  -0.500   0.2259   0.01127   0.00583  -0.0588   0.9584   1.0000
  -0.250   0.2655   0.01114   0.00568  -0.0614   0.9527   1.0000
   0.000   0.3009   0.01103   0.00555  -0.0631   0.9450   1.0000
   0.250   0.3296   0.01100   0.00552  -0.0632   0.9352   1.0000
   0.500   0.3537   0.01103   0.00555  -0.0622   0.9244   1.0000
   0.750   0.3742   0.01110   0.00563  -0.0604   0.9133   1.0000
   1.000   0.3924   0.01120   0.00572  -0.0582   0.9024   1.0000
   1.250   0.4101   0.01130   0.00584  -0.0559   0.8913   1.0000
   1.500   0.4280   0.01139   0.00596  -0.0536   0.8804   1.0000
   1.750   0.4458   0.01145   0.00604  -0.0511   0.8694   1.0000
   2.000   0.4636   0.01149   0.00613  -0.0485   0.8580   1.0000
   2.250   0.4814   0.01150   0.00615  -0.0458   0.8459   1.0000
   2.500   0.4996   0.01148   0.00617  -0.0433   0.8328   1.0000
   2.750   0.5181   0.01141   0.00616  -0.0409   0.8179   1.0000
   3.000   0.5371   0.01124   0.00606  -0.0386   0.8011   1.0000
   3.250   0.5568   0.01092   0.00585  -0.0363   0.7823   1.0000
   3.500   0.5775   0.01055   0.00565  -0.0347   0.7494   1.0000
   3.750   0.5972   0.00994   0.00504  -0.0320   0.7029   1.0000
   4.000   0.6131   0.00962   0.00425  -0.0281   0.6082   1.0000
   4.250   0.6272   0.01033   0.00434  -0.0252   0.4911   1.0000
   4.500   0.6419   0.01118   0.00471  -0.0230   0.3882   1.0000
   4.750   0.6573   0.01202   0.00517  -0.0211   0.3025   1.0000
   5.000   0.6736   0.01280   0.00564  -0.0194   0.2355   1.0000
   5.250   0.6903   0.01355   0.00616  -0.0177   0.1849   1.0000
   5.500   0.7066   0.01434   0.00676  -0.0159   0.1439   1.0000
   5.750   0.7227   0.01513   0.00740  -0.0141   0.1141   1.0000
   6.000   0.7377   0.01603   0.00818  -0.0120   0.0947   1.0000
   6.250   0.7533   0.01687   0.00902  -0.0099   0.0809   1.0000
   6.500   0.7694   0.01758   0.00979  -0.0080   0.0675   1.0000
   6.750   0.7846   0.01846   0.01067  -0.0060   0.0557   1.0000
   7.000   0.7995   0.01948   0.01171  -0.0039   0.0439   1.0000
   7.250   0.8149   0.02082   0.01309  -0.0019   0.0342   1.0000
   7.500   0.8339   0.02232   0.01478  -0.0002   0.0294   1.0000
   7.750   0.8523   0.02345   0.01594   0.0009   0.0245   1.0000
   8.000   0.8708   0.02636   0.01912   0.0023   0.0223   1.0000
   8.250   0.8904   0.02863   0.02173   0.0037   0.0212   1.0000
   8.500   0.9070   0.03150   0.02502   0.0052   0.0206   1.0000
   8.750   0.9192   0.03496   0.02901   0.0070   0.0204   1.0000
   9.000   0.9257   0.03898   0.03352   0.0091   0.0206   1.0000
   9.250   0.9268   0.04330   0.03829   0.0112   0.0210   1.0000
   9.500   0.9218   0.04781   0.04319   0.0134   0.0215   1.0000
   9.750   0.9105   0.05244   0.04814   0.0155   0.0220   1.0000
  10.000   0.8937   0.05664   0.05256   0.0177   0.0224   1.0000
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