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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 500,000
Max Cl/Cd: 75.64 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du8608418-il-500000.txt
Download as CSV file: xf-du8608418-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4510   0.08978   0.08762  -0.0196   0.9121   0.0152
  -9.750  -0.4575   0.08355   0.08141  -0.0221   0.9116   0.0155
  -9.500  -0.4601   0.07823   0.07609  -0.0246   0.9110   0.0155
  -9.250  -0.4653   0.07274   0.07062  -0.0270   0.9106   0.0159
  -9.000  -0.5041   0.07735   0.07505  -0.0355   0.9138   0.0148
  -8.750  -0.5105   0.07041   0.06809  -0.0422   0.9116   0.0148
  -8.500  -0.5222   0.06557   0.06316  -0.0442   0.9091   0.0148
  -8.250  -0.5344   0.06190   0.05940  -0.0438   0.9074   0.0148
  -8.000  -0.5396   0.05801   0.05537  -0.0437   0.9060   0.0148
  -7.750  -0.5711   0.04869   0.04578  -0.0432   0.9041   0.0155
  -7.500  -0.5698   0.04476   0.04166  -0.0424   0.9027   0.0159
  -7.250  -0.5608   0.04193   0.03870  -0.0418   0.9018   0.0164
  -7.000  -0.5493   0.03923   0.03583  -0.0410   0.9010   0.0169
  -6.750  -0.5359   0.03645   0.03285  -0.0402   0.9003   0.0175
  -6.500  -0.5210   0.03366   0.02982  -0.0393   0.8994   0.0184
  -6.250  -0.5041   0.03090   0.02674  -0.0382   0.8985   0.0196
  -6.000  -0.4907   0.02350   0.01850  -0.0346   0.8974   0.0124
  -5.750  -0.4708   0.01908   0.01341  -0.0326   0.8964   0.0109
  -5.500  -0.4462   0.01747   0.01158  -0.0319   0.8954   0.0115
  -5.250  -0.4207   0.01615   0.01010  -0.0314   0.8947   0.0121
  -5.000  -0.3947   0.01536   0.00921  -0.0311   0.8938   0.0132
  -4.750  -0.3684   0.01473   0.00848  -0.0308   0.8928   0.0142
  -4.500  -0.3431   0.01375   0.00739  -0.0302   0.8918   0.0145
  -4.250  -0.3192   0.01265   0.00617  -0.0295   0.8906   0.0152
  -4.000  -0.2957   0.01162   0.00502  -0.0286   0.8894   0.0186
  -3.750  -0.2696   0.01125   0.00458  -0.0283   0.8882   0.0232
  -3.500  -0.2451   0.01051   0.00399  -0.0277   0.8869   0.0630
  -3.250  -0.2203   0.00985   0.00373  -0.0276   0.8856   0.1532
  -3.000  -0.1959   0.00923   0.00356  -0.0274   0.8840   0.2664
  -2.750  -0.1721   0.00861   0.00341  -0.0271   0.8820   0.3928
  -2.500  -0.1490   0.00805   0.00330  -0.0265   0.8797   0.5166
  -2.250  -0.1277   0.00743   0.00319  -0.0253   0.8771   0.6548
  -2.000  -0.1134   0.00728   0.00374  -0.0213   0.8744   0.8445
  -1.750  -0.0897   0.00757   0.00398  -0.0200   0.8716   0.8806
  -1.500  -0.0670   0.00778   0.00415  -0.0184   0.8678   0.8977
  -1.250  -0.0447   0.00794   0.00427  -0.0166   0.8640   0.9092
  -1.000  -0.0228   0.00809   0.00437  -0.0148   0.8605   0.9192
  -0.750  -0.0005   0.00821   0.00446  -0.0132   0.8565   0.9293
  -0.500   0.0236   0.00825   0.00447  -0.0118   0.8521   0.9367
  -0.250   0.0472   0.00829   0.00446  -0.0104   0.8478   0.9442
   0.000   0.0757   0.00834   0.00449  -0.0101   0.8431   0.9503
   0.250   0.1015   0.00833   0.00444  -0.0094   0.8373   0.9564
   0.500   0.1378   0.00836   0.00443  -0.0108   0.8322   0.9601
   0.750   0.1754   0.00832   0.00438  -0.0127   0.8260   0.9643
   1.000   0.2031   0.00833   0.00435  -0.0123   0.8210   0.9690
   1.250   0.2524   0.00825   0.00428  -0.0168   0.8151   0.9712
   1.500   0.2985   0.00816   0.00418  -0.0205   0.8092   0.9747
   1.750   0.3391   0.00805   0.00410  -0.0231   0.8017   0.9807
   2.000   0.3864   0.00784   0.00388  -0.0270   0.7946   0.9854
   2.250   0.4262   0.00756   0.00367  -0.0295   0.7834   0.9893
   2.500   0.4564   0.00727   0.00345  -0.0300   0.7689   0.9913
   2.750   0.4850   0.00698   0.00322  -0.0300   0.7389   0.9929
   3.000   0.5083   0.00672   0.00262  -0.0286   0.6631   0.9943
   3.250   0.5315   0.00717   0.00261  -0.0278   0.5621   0.9955
   3.500   0.5545   0.00777   0.00279  -0.0273   0.4577   0.9967
   3.750   0.5786   0.00833   0.00298  -0.0270   0.3700   0.9979
   4.000   0.6033   0.00884   0.00318  -0.0269   0.2960   0.9989
   4.250   0.6288   0.00927   0.00340  -0.0269   0.2420   0.9997
   4.500   0.6517   0.00967   0.00365  -0.0263   0.1983   1.0000
   4.750   0.6728   0.01008   0.00391  -0.0253   0.1595   1.0000
   5.000   0.6940   0.01048   0.00418  -0.0243   0.1274   1.0000
   5.250   0.7147   0.01090   0.00450  -0.0232   0.1001   1.0000
   5.500   0.7351   0.01134   0.00485  -0.0221   0.0775   1.0000
   5.750   0.7553   0.01179   0.00521  -0.0209   0.0606   1.0000
   6.000   0.7755   0.01218   0.00562  -0.0197   0.0498   1.0000
   6.250   0.7954   0.01258   0.00605  -0.0184   0.0418   1.0000
   6.500   0.8145   0.01304   0.00648  -0.0169   0.0325   1.0000
   6.750   0.8327   0.01358   0.00701  -0.0153   0.0217   1.0000
   7.000   0.8471   0.01454   0.00800  -0.0130   0.0144   1.0000
   7.250   0.8639   0.01511   0.00867  -0.0111   0.0125   1.0000
   7.500   0.8792   0.01577   0.00940  -0.0089   0.0109   1.0000
   7.750   0.8906   0.01677   0.01049  -0.0061   0.0099   1.0000
   8.000   0.8974   0.01839   0.01230  -0.0026   0.0092   1.0000
   8.250   0.9072   0.02062   0.01478   0.0002   0.0089   1.0000
   8.500   0.9280   0.02127   0.01557   0.0011   0.0085   1.0000
   8.750   0.9479   0.02237   0.01682   0.0020   0.0081   1.0000
   9.000   0.9671   0.02370   0.01833   0.0029   0.0076   1.0000
   9.250   0.9843   0.02548   0.02035   0.0040   0.0073   1.0000
   9.500   0.9988   0.02776   0.02291   0.0053   0.0071   1.0000
   9.750   1.0114   0.02999   0.02541   0.0066   0.0068   1.0000
  10.000   1.0218   0.03211   0.02778   0.0080   0.0064   1.0000
  10.250   1.0263   0.03481   0.03077   0.0099   0.0063   1.0000
  10.500   1.0185   0.03853   0.03486   0.0129   0.0064   1.0000
  10.750   1.0047   0.04181   0.03841   0.0159   0.0064   1.0000
  11.000   0.9855   0.04578   0.04266   0.0180   0.0064   1.0000
  11.250   0.9554   0.05146   0.04867   0.0191   0.0066   1.0000
  11.500   0.9310   0.05697   0.05440   0.0182   0.0067   1.0000
  11.750   0.9094   0.06308   0.06069   0.0152   0.0067   1.0000
  12.000   0.8829   0.07212   0.06992   0.0085   0.0070   1.0000
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