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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 100,000
Max Cl/Cd: 46.95 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du8608418-il-100000.txt
Download as CSV file: xf-du8608418-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4387   0.09374   0.08951  -0.0161   1.0000   0.1085
  -9.000  -0.4557   0.08962   0.08547  -0.0208   1.0000   0.1123
  -8.750  -0.4835   0.08505   0.08098  -0.0278   1.0000   0.1131
  -8.500  -0.4441   0.08069   0.07658  -0.0209   1.0000   0.1198
  -8.250  -0.4569   0.07630   0.07225  -0.0245   1.0000   0.1248
  -8.000  -0.4902   0.07175   0.06777  -0.0308   1.0000   0.1262
  -7.750  -0.4695   0.06712   0.06318  -0.0279   1.0000   0.1314
  -7.500  -0.4791   0.06348   0.05957  -0.0285   1.0000   0.1355
  -7.250  -0.5129   0.06033   0.05638  -0.0296   1.0000   0.1395
  -6.500  -0.5763   0.06134   0.05700  -0.0233   1.0000   0.1478
  -5.750  -0.5545   0.04170   0.03743  -0.0163   1.0000   0.1832
  -5.500  -0.5686   0.04049   0.03399  -0.0165   1.0000   0.0715
  -5.250  -0.5535   0.03559   0.02847  -0.0139   1.0000   0.0578
  -5.000  -0.5374   0.03196   0.02445  -0.0121   1.0000   0.0540
  -4.750  -0.5177   0.02870   0.02047  -0.0099   1.0000   0.0502
  -4.500  -0.4956   0.02630   0.01757  -0.0082   1.0000   0.0493
  -4.250  -0.4745   0.02470   0.01583  -0.0071   1.0000   0.0536
  -4.000  -0.4512   0.02320   0.01402  -0.0058   1.0000   0.0577
  -3.750  -0.4267   0.02157   0.01215  -0.0044   1.0000   0.0603
  -3.500  -0.4043   0.01982   0.01050  -0.0032   1.0000   0.0686
  -3.250  -0.3828   0.01869   0.00932  -0.0019   1.0000   0.0858
  -3.000  -0.3629   0.01700   0.00804  -0.0005   1.0000   0.1371
  -2.750  -0.3546   0.01370   0.00746   0.0032   1.0000   0.6006
  -2.500  -0.1479   0.01510   0.00871  -0.0239   1.0000   1.0000
  -2.250  -0.1403   0.01504   0.00847  -0.0211   1.0000   1.0000
  -2.000  -0.1316   0.01501   0.00827  -0.0183   1.0000   1.0000
  -1.750  -0.1221   0.01499   0.00811  -0.0156   1.0000   1.0000
  -1.500  -0.1121   0.01499   0.00797  -0.0130   1.0000   1.0000
  -1.250  -0.1016   0.01500   0.00784  -0.0105   1.0000   1.0000
  -1.000  -0.0909   0.01503   0.00776  -0.0080   1.0000   1.0000
  -0.750  -0.0799   0.01508   0.00770  -0.0055   1.0000   1.0000
  -0.500  -0.0687   0.01513   0.00767  -0.0031   1.0000   1.0000
  -0.250  -0.0574   0.01520   0.00767  -0.0008   1.0000   1.0000
   0.000  -0.0458   0.01529   0.00769   0.0015   1.0000   1.0000
   0.250  -0.0338   0.01540   0.00772   0.0037   1.0000   1.0000
   0.500  -0.0216   0.01554   0.00781   0.0057   1.0000   1.0000
   0.750   0.0194   0.01603   0.00825   0.0022   0.9937   1.0000
   1.000   0.0676   0.01655   0.00875  -0.0027   0.9846   1.0000
   1.250   0.1146   0.01702   0.00922  -0.0073   0.9743   1.0000
   1.500   0.1649   0.01749   0.00972  -0.0123   0.9630   1.0000
   1.750   0.2195   0.01790   0.01019  -0.0179   0.9506   1.0000
   2.000   0.2793   0.01818   0.01059  -0.0242   0.9367   1.0000
   2.250   0.3462   0.01828   0.01083  -0.0315   0.9220   1.0000
   2.500   0.4236   0.01808   0.01088  -0.0404   0.9078   1.0000
   2.750   0.4869   0.01769   0.01072  -0.0461   0.8914   1.0000
   3.000   0.5358   0.01725   0.01047  -0.0483   0.8735   1.0000
   3.250   0.5584   0.01710   0.01050  -0.0457   0.8510   1.0000
   3.500   0.5800   0.01683   0.01036  -0.0426   0.8288   1.0000
   3.750   0.5960   0.01650   0.01017  -0.0385   0.8033   1.0000
   4.000   0.6087   0.01599   0.00982  -0.0342   0.7706   1.0000
   4.250   0.6222   0.01523   0.00925  -0.0301   0.7259   1.0000
   4.500   0.6413   0.01410   0.00809  -0.0256   0.6570   1.0000
   4.750   0.6563   0.01398   0.00729  -0.0206   0.5250   1.0000
   5.000   0.6658   0.01508   0.00762  -0.0168   0.3964   1.0000
   5.250   0.6763   0.01635   0.00826  -0.0139   0.3014   1.0000
   5.500   0.6885   0.01762   0.00909  -0.0113   0.2348   1.0000
   5.750   0.7019   0.01885   0.00999  -0.0090   0.1876   1.0000
   6.000   0.7176   0.02011   0.01108  -0.0069   0.1550   1.0000
   6.250   0.7351   0.02144   0.01229  -0.0051   0.1319   1.0000
   6.500   0.7536   0.02268   0.01353  -0.0035   0.1123   1.0000
   6.750   0.7742   0.02436   0.01513  -0.0022   0.0968   1.0000
   7.000   0.7940   0.02608   0.01693  -0.0009   0.0813   1.0000
   7.250   0.8132   0.02784   0.01885   0.0005   0.0673   1.0000
   7.500   0.8342   0.03018   0.02129   0.0017   0.0583   1.0000
   7.750   0.8521   0.03247   0.02407   0.0034   0.0508   1.0000
   8.000   0.8703   0.03523   0.02708   0.0047   0.0472   1.0000
   8.250   0.8846   0.03954   0.03172   0.0061   0.0455   1.0000
   8.500   0.8937   0.04424   0.03692   0.0079   0.0452   1.0000
   8.750   0.8979   0.04831   0.04150   0.0100   0.0447   1.0000
   9.000   0.8983   0.05170   0.04544   0.0123   0.0439   1.0000
   9.250   0.8958   0.05585   0.04998   0.0141   0.0439   1.0000
   9.500   0.8876   0.05993   0.05442   0.0159   0.0436   1.0000
   9.750   0.8770   0.06434   0.05907   0.0172   0.0439   1.0000
  10.000   0.8644   0.06863   0.06349   0.0184   0.0444   1.0000
  10.250   0.8097   0.07676   0.07209   0.0168   0.0541   1.0000
  10.500   0.7966   0.08214   0.07751   0.0149   0.0554   1.0000
  10.750   0.7883   0.08782   0.08320   0.0128   0.0563   1.0000
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