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DU86-084/18 8.44% (du8608418-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: DU86-084/18 8.44% (du8608418-il)
Reynolds number: 50,000
Max Cl/Cd: 32.27 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-du8608418-il-50000.txt
Download as CSV file: xf-du8608418-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5052   0.09635   0.09009   0.0000   1.0000   0.3023
  -8.000  -0.5031   0.09310   0.08690   0.0000   1.0000   0.3173
  -7.750  -0.5124   0.09067   0.08458  -0.0003   1.0000   0.3340
  -7.500  -0.5063   0.08689   0.08087   0.0003   1.0000   0.3497
  -7.250  -0.4002   0.07231   0.06665  -0.0048   1.0000   0.3664
  -7.000  -0.3953   0.06846   0.06285  -0.0039   1.0000   0.3833
  -6.750  -0.3964   0.06466   0.05912  -0.0031   1.0000   0.3964
  -6.250  -0.5671   0.05890   0.05250  -0.0245   1.0000   0.1637
  -6.000  -0.5747   0.05297   0.04555  -0.0242   1.0000   0.1271
  -5.750  -0.5625   0.04861   0.04119  -0.0225   1.0000   0.1191
  -5.500  -0.5535   0.04455   0.03651  -0.0205   1.0000   0.1096
  -5.250  -0.5413   0.04081   0.03223  -0.0185   1.0000   0.1040
  -5.000  -0.5250   0.03774   0.02821  -0.0162   1.0000   0.0994
  -4.750  -0.5059   0.03475   0.02482  -0.0145   1.0000   0.0990
  -4.500  -0.4859   0.03197   0.02181  -0.0131   1.0000   0.1032
  -4.250  -0.4643   0.02999   0.01944  -0.0116   1.0000   0.1116
  -4.000  -0.4402   0.02766   0.01694  -0.0102   1.0000   0.1192
  -3.750  -0.4151   0.02571   0.01487  -0.0089   1.0000   0.1359
  -3.500  -0.1542   0.01957   0.01137  -0.0370   1.0000   1.0000
  -3.250  -0.1550   0.01926   0.01080  -0.0338   1.0000   1.0000
  -3.000  -0.1523   0.01907   0.01030  -0.0307   1.0000   1.0000
  -2.750  -0.1473   0.01895   0.00992  -0.0277   1.0000   1.0000
  -2.500  -0.1405   0.01886   0.00958  -0.0248   1.0000   1.0000
  -2.250  -0.1325   0.01880   0.00929  -0.0220   1.0000   1.0000
  -2.000  -0.1235   0.01876   0.00903  -0.0193   1.0000   1.0000
  -1.750  -0.1137   0.01874   0.00882  -0.0166   1.0000   1.0000
  -1.500  -0.1034   0.01874   0.00863  -0.0141   1.0000   1.0000
  -1.250  -0.0927   0.01875   0.00844  -0.0116   1.0000   1.0000
  -1.000  -0.0816   0.01877   0.00831  -0.0092   1.0000   1.0000
  -0.750  -0.0701   0.01881   0.00822  -0.0068   1.0000   1.0000
  -0.500  -0.0582   0.01887   0.00815  -0.0045   1.0000   1.0000
  -0.250  -0.0460   0.01894   0.00812  -0.0023   1.0000   1.0000
   0.000  -0.0335   0.01904   0.00812  -0.0002   1.0000   1.0000
   0.250  -0.0207   0.01915   0.00812   0.0019   1.0000   1.0000
   0.500  -0.0073   0.01929   0.00819   0.0038   1.0000   1.0000
   0.750   0.0068   0.01947   0.00830   0.0055   1.0000   1.0000
   1.000   0.0216   0.01967   0.00846   0.0070   1.0000   1.0000
   1.250   0.0369   0.01992   0.00868   0.0084   1.0000   1.0000
   1.500   0.0527   0.02020   0.00894   0.0096   1.0000   1.0000
   1.750   0.0688   0.02053   0.00926   0.0107   1.0000   1.0000
   2.000   0.0851   0.02091   0.00965   0.0116   1.0000   1.0000
   2.250   0.1014   0.02133   0.01010   0.0124   1.0000   1.0000
   2.500   0.1177   0.02182   0.01062   0.0131   1.0000   1.0000
   2.750   0.1338   0.02237   0.01123   0.0137   1.0000   1.0000
   3.000   0.1496   0.02300   0.01195   0.0141   1.0000   1.0000
   3.250   0.1650   0.02371   0.01274   0.0145   1.0000   1.0000
   3.500   0.2264   0.02543   0.01471   0.0058   0.9777   1.0000
   3.750   0.3125   0.02730   0.01701  -0.0062   0.9410   1.0000
   4.000   0.3944   0.02845   0.01863  -0.0160   0.8998   1.0000
   4.250   0.4789   0.02872   0.01957  -0.0242   0.8530   1.0000
   4.500   0.5726   0.02735   0.01898  -0.0305   0.7979   1.0000
   4.750   0.6078   0.02538   0.01744  -0.0269   0.7406   1.0000
   5.000   0.6455   0.02191   0.01439  -0.0209   0.6618   1.0000
   5.250   0.6716   0.02081   0.01238  -0.0139   0.5062   1.0000
   5.500   0.6816   0.02254   0.01318  -0.0094   0.3928   1.0000
   5.750   0.6973   0.02445   0.01444  -0.0067   0.3144   1.0000
   6.000   0.7176   0.02637   0.01604  -0.0048   0.2568   1.0000
   6.250   0.7399   0.02837   0.01782  -0.0034   0.2164   1.0000
   6.500   0.7628   0.03058   0.02007  -0.0021   0.1878   1.0000
   6.750   0.7849   0.03291   0.02261  -0.0007   0.1656   1.0000
   7.000   0.8048   0.03551   0.02539   0.0007   0.1472   1.0000
   7.250   0.8243   0.03865   0.02883   0.0023   0.1343   1.0000
   7.500   0.8393   0.04147   0.03196   0.0040   0.1205   1.0000
   7.750   0.8505   0.04543   0.03662   0.0061   0.1155   1.0000
   8.000   0.8631   0.04894   0.04029   0.0076   0.1072   1.0000
   8.250   0.8650   0.05294   0.04494   0.0097   0.1034   1.0000
   8.500   0.8650   0.05756   0.05003   0.0114   0.1032   1.0000
   8.750   0.8608   0.06250   0.05535   0.0127   0.1046   1.0000
   9.000   0.8555   0.06749   0.06060   0.0136   0.1064   1.0000
   9.250   0.8561   0.07269   0.06591   0.0141   0.1083   1.0000
   9.500   0.8111   0.07794   0.07151   0.0133   0.1147   1.0000
   9.750   0.7884   0.08360   0.07720   0.0117   0.1186   1.0000
  10.000   0.7550   0.09225   0.08583   0.0050   0.1309   1.0000
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