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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 200,000
Max Cl/Cd: 53.84 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-du8608418-il-200000-n5.txt
Download as CSV file: xf-du8608418-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5469   0.09444   0.09118  -0.0135   0.9783   0.0096
  -9.500  -0.5454   0.08866   0.08540  -0.0181   0.9481   0.0095
  -9.250  -0.5428   0.08302   0.07976  -0.0231   0.9396   0.0093
  -9.000  -0.5432   0.07691   0.07365  -0.0287   0.9327   0.0091
  -8.750  -0.5487   0.06985   0.06657  -0.0363   0.9261   0.0090
  -8.500  -0.5584   0.06384   0.06047  -0.0403   0.9207   0.0089
  -8.250  -0.5660   0.05863   0.05513  -0.0421   0.9171   0.0088
  -8.000  -0.5704   0.05337   0.04966  -0.0429   0.9141   0.0086
  -7.750  -0.5712   0.04847   0.04452  -0.0429   0.9113   0.0084
  -7.500  -0.5695   0.04341   0.03913  -0.0422   0.9091   0.0083
  -7.250  -0.5638   0.03876   0.03408  -0.0411   0.9073   0.0081
  -7.000  -0.5547   0.03440   0.02924  -0.0397   0.9057   0.0081
  -6.750  -0.5418   0.03046   0.02476  -0.0382   0.9040   0.0082
  -6.500  -0.5246   0.02732   0.02110  -0.0368   0.9024   0.0083
  -6.250  -0.5042   0.02467   0.01791  -0.0357   0.9014   0.0087
  -6.000  -0.4814   0.02252   0.01535  -0.0349   0.9005   0.0091
  -5.750  -0.4569   0.02105   0.01358  -0.0343   0.8995   0.0102
  -5.500  -0.4335   0.01987   0.01230  -0.0341   0.8982   0.0122
  -5.250  -0.4085   0.01859   0.01085  -0.0336   0.8970   0.0133
  -5.000  -0.3837   0.01738   0.00949  -0.0330   0.8960   0.0145
  -4.750  -0.3591   0.01642   0.00840  -0.0324   0.8947   0.0159
  -4.500  -0.3352   0.01550   0.00739  -0.0319   0.8933   0.0191
  -4.250  -0.3101   0.01486   0.00664  -0.0315   0.8921   0.0231
  -4.000  -0.2848   0.01426   0.00590  -0.0310   0.8907   0.0282
  -3.750  -0.2597   0.01367   0.00532  -0.0305   0.8894   0.0439
  -3.500  -0.2360   0.01295   0.00494  -0.0302   0.8880   0.1092
  -3.250  -0.2121   0.01233   0.00467  -0.0299   0.8865   0.1971
  -3.000  -0.1888   0.01169   0.00447  -0.0295   0.8847   0.3050
  -2.750  -0.1667   0.01105   0.00428  -0.0289   0.8826   0.4258
  -2.500  -0.1459   0.01040   0.00415  -0.0277   0.8805   0.5562
  -2.250  -0.1277   0.00984   0.00433  -0.0250   0.8784   0.7268
  -2.000  -0.1018   0.01027   0.00499  -0.0227   0.8768   0.8418
  -1.750  -0.0821   0.01046   0.00505  -0.0209   0.8744   0.8759
  -1.500  -0.0580   0.01065   0.00514  -0.0196   0.8717   0.8942
  -1.250  -0.0331   0.01079   0.00522  -0.0186   0.8684   0.9083
  -1.000  -0.0066   0.01090   0.00525  -0.0179   0.8651   0.9199
  -0.750   0.0202   0.01098   0.00526  -0.0173   0.8618   0.9302
  -0.500   0.0523   0.01104   0.00524  -0.0178   0.8582   0.9383
  -0.250   0.0846   0.01107   0.00523  -0.0186   0.8533   0.9456
   0.000   0.1187   0.01109   0.00520  -0.0196   0.8489   0.9523
   0.250   0.1565   0.01111   0.00518  -0.0214   0.8444   0.9583
   0.500   0.1977   0.01108   0.00513  -0.0241   0.8380   0.9638
   0.750   0.2382   0.01105   0.00507  -0.0264   0.8316   0.9708
   1.000   0.2809   0.01096   0.00497  -0.0293   0.8228   0.9777
   1.250   0.3151   0.01088   0.00492  -0.0306   0.8137   0.9830
   1.500   0.3464   0.01077   0.00483  -0.0312   0.8055   0.9853
   1.750   0.3754   0.01065   0.00474  -0.0314   0.7960   0.9875
   2.000   0.4035   0.01050   0.00468  -0.0316   0.7842   0.9896
   2.250   0.4314   0.01036   0.00467  -0.0317   0.7674   0.9916
   2.500   0.4590   0.01018   0.00460  -0.0318   0.7422   0.9934
   2.750   0.4854   0.00978   0.00418  -0.0309   0.7039   0.9950
   3.000   0.5083   0.00946   0.00350  -0.0290   0.6316   0.9967
   3.250   0.5298   0.00984   0.00339  -0.0276   0.5358   0.9983
   3.500   0.5512   0.01046   0.00362  -0.0266   0.4431   0.9996
   3.750   0.5712   0.01102   0.00388  -0.0254   0.3713   1.0000
   4.000   0.5903   0.01156   0.00417  -0.0241   0.3086   1.0000
   4.250   0.6095   0.01211   0.00450  -0.0229   0.2540   1.0000
   4.500   0.6289   0.01262   0.00483  -0.0216   0.2103   1.0000
   4.750   0.6484   0.01310   0.00519  -0.0204   0.1735   1.0000
   5.000   0.6681   0.01355   0.00561  -0.0191   0.1457   1.0000
   5.250   0.6873   0.01402   0.00601  -0.0178   0.1200   1.0000
   5.500   0.7060   0.01453   0.00645  -0.0164   0.0973   1.0000
   5.750   0.7246   0.01503   0.00693  -0.0149   0.0805   1.0000
   6.000   0.7427   0.01554   0.00747  -0.0134   0.0688   1.0000
   6.250   0.7602   0.01611   0.00806  -0.0117   0.0592   1.0000
   6.500   0.7771   0.01668   0.00862  -0.0099   0.0483   1.0000
   6.750   0.7943   0.01723   0.00923  -0.0083   0.0388   1.0000
   7.000   0.8116   0.01776   0.00984  -0.0066   0.0308   1.0000
   7.250   0.8277   0.01851   0.01063  -0.0048   0.0244   1.0000
   7.500   0.8448   0.01934   0.01156  -0.0031   0.0193   1.0000
   7.750   0.8603   0.02060   0.01293  -0.0013   0.0160   1.0000
   8.000   0.8801   0.02136   0.01381  -0.0003   0.0130   1.0000
   8.250   0.8986   0.02240   0.01495   0.0007   0.0112   1.0000
   8.500   0.9128   0.02426   0.01699   0.0023   0.0099   1.0000
   8.750   0.9300   0.02586   0.01882   0.0036   0.0093   1.0000
   9.000   0.9461   0.02777   0.02106   0.0049   0.0087   1.0000
   9.250   0.9614   0.02970   0.02327   0.0062   0.0080   1.0000
   9.500   0.9776   0.03081   0.02455   0.0071   0.0070   1.0000
   9.750   0.9904   0.03208   0.02593   0.0081   0.0061   1.0000
  10.250   0.9977   0.03753   0.03205   0.0120   0.0056   1.0000
  10.500   0.9947   0.04022   0.03507   0.0145   0.0055   1.0000
  10.750   0.9874   0.04323   0.03840   0.0166   0.0053   1.0000
  11.000   0.9776   0.04649   0.04193   0.0181   0.0053   1.0000
  11.250   0.9641   0.05029   0.04598   0.0189   0.0054   1.0000
  11.500   0.9469   0.05486   0.05083   0.0187   0.0052   1.0000
  11.750   0.9296   0.05997   0.05615   0.0170   0.0053   1.0000
  12.000   0.9112   0.06625   0.06263   0.0133   0.0053   1.0000
  12.250   0.8921   0.07423   0.07077   0.0074   0.0054   1.0000
  12.500   0.8703   0.08524   0.08193  -0.0008   0.0055   1.0000
  12.750   0.8521   0.09537   0.09211  -0.0073   0.0057   1.0000
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