Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

E169 (14.4%) (e169-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E169 (14.4%) (e169-il)
Reynolds number: 100,000
Max Cl/Cd: 39.29 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e169-il-100000.txt
Download as CSV file: xf-e169-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E169  (14.4%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -0.9141   0.09832   0.09294  -0.0135   1.0000   0.0614
 -14.750  -0.9480   0.08904   0.08349  -0.0193   1.0000   0.0607
 -14.500  -0.9777   0.08110   0.07535  -0.0241   1.0000   0.0602
 -14.250  -1.0036   0.07428   0.06831  -0.0279   1.0000   0.0599
 -14.000  -1.0258   0.06847   0.06226  -0.0308   1.0000   0.0599
 -13.750  -1.0460   0.06342   0.05695  -0.0329   1.0000   0.0602
 -13.500  -1.0637   0.05906   0.05233  -0.0342   1.0000   0.0608
 -13.250  -1.0791   0.05540   0.04837  -0.0347   1.0000   0.0615
 -13.000  -1.0767   0.05185   0.04476  -0.0344   1.0000   0.0639
 -12.750  -1.0694   0.04953   0.04245  -0.0339   1.0000   0.0666
 -12.500  -1.0700   0.04690   0.03964  -0.0332   1.0000   0.0688
 -12.250  -1.0727   0.04443   0.03693  -0.0320   1.0000   0.0714
 -12.000  -1.0696   0.04188   0.03419  -0.0307   1.0000   0.0748
 -11.750  -1.0574   0.04003   0.03247  -0.0298   1.0000   0.0798
 -11.500  -1.0559   0.03810   0.03030  -0.0277   1.0000   0.0842
 -11.250  -1.0432   0.03605   0.02835  -0.0266   1.0000   0.0905
 -11.000  -1.0408   0.03443   0.02655  -0.0242   1.0000   0.0974
 -10.750  -1.0313   0.03268   0.02496  -0.0226   1.0000   0.1065
 -10.500  -1.0240   0.03099   0.02331  -0.0206   1.0000   0.1173
 -10.250  -1.0166   0.02947   0.02183  -0.0186   1.0000   0.1303
 -10.000  -1.0082   0.02811   0.02052  -0.0166   1.0000   0.1460
  -9.750  -0.9987   0.02689   0.01930  -0.0146   1.0000   0.1644
  -9.500  -0.9872   0.02586   0.01833  -0.0128   1.0000   0.1839
  -9.250  -0.9736   0.02509   0.01762  -0.0110   1.0000   0.2045
  -9.000  -0.9592   0.02441   0.01689  -0.0093   1.0000   0.2257
  -8.750  -0.9413   0.02400   0.01658  -0.0079   1.0000   0.2450
  -8.500  -0.9228   0.02366   0.01622  -0.0064   1.0000   0.2640
  -8.250  -0.9036   0.02333   0.01581  -0.0050   1.0000   0.2819
  -8.000  -0.8835   0.02303   0.01544  -0.0037   1.0000   0.2984
  -7.750  -0.8623   0.02279   0.01516  -0.0025   1.0000   0.3139
  -7.500  -0.8399   0.02260   0.01499  -0.0015   1.0000   0.3283
  -7.250  -0.8166   0.02243   0.01485  -0.0004   1.0000   0.3419
  -7.000  -0.7933   0.02224   0.01469   0.0006   1.0000   0.3548
  -6.750  -0.7703   0.02201   0.01445   0.0016   1.0000   0.3673
  -6.500  -0.7480   0.02171   0.01412   0.0027   1.0000   0.3798
  -6.250  -0.7264   0.02136   0.01370   0.0039   1.0000   0.3925
  -6.000  -0.7046   0.02107   0.01336   0.0050   1.0000   0.4048
  -5.750  -0.6809   0.02086   0.01325   0.0060   1.0000   0.4151
  -5.500  -0.6594   0.02052   0.01289   0.0072   1.0000   0.4263
  -5.250  -0.6393   0.02012   0.01240   0.0084   1.0000   0.4381
  -5.000  -0.6180   0.01989   0.01225   0.0096   1.0000   0.4480
  -4.750  -0.5992   0.01957   0.01196   0.0110   1.0000   0.4578
  -4.500  -0.5850   0.01925   0.01158   0.0128   1.0000   0.4688
  -4.250  -0.5724   0.01914   0.01158   0.0149   1.0000   0.4768
  -4.000  -0.5455   0.01901   0.01142   0.0139   0.9938   0.4879
  -3.750  -0.4896   0.01886   0.01125   0.0081   0.9752   0.5025
  -3.500  -0.4349   0.01864   0.01099   0.0027   0.9573   0.5170
  -3.250  -0.3808   0.01837   0.01070  -0.0023   0.9401   0.5313
  -3.000  -0.3339   0.01814   0.01048  -0.0056   0.9189   0.5438
  -2.750  -0.2914   0.01793   0.01027  -0.0078   0.8966   0.5554
  -2.500  -0.2569   0.01775   0.01004  -0.0086   0.8725   0.5671
  -2.250  -0.2277   0.01762   0.00980  -0.0083   0.8485   0.5792
  -2.000  -0.2008   0.01757   0.00971  -0.0075   0.8256   0.5899
  -1.750  -0.1752   0.01751   0.00962  -0.0066   0.8041   0.6005
  -1.500  -0.1502   0.01745   0.00946  -0.0056   0.7848   0.6122
  -1.250  -0.1254   0.01742   0.00934  -0.0046   0.7666   0.6247
  -1.000  -0.1003   0.01740   0.00933  -0.0036   0.7486   0.6354
  -0.750  -0.0753   0.01738   0.00928  -0.0026   0.7319   0.6475
  -0.500  -0.0503   0.01736   0.00922  -0.0018   0.7164   0.6604
  -0.250  -0.0252   0.01735   0.00917  -0.0009   0.7017   0.6741
   0.000   0.0000   0.01735   0.00913   0.0000   0.6881   0.6882
   0.250   0.0252   0.01735   0.00917   0.0009   0.6741   0.7017
   0.500   0.0503   0.01736   0.00922   0.0018   0.6604   0.7165
   0.750   0.0753   0.01738   0.00928   0.0026   0.6475   0.7319
   1.000   0.1003   0.01740   0.00933   0.0036   0.6354   0.7486
   1.250   0.1254   0.01742   0.00934   0.0046   0.6247   0.7666
   1.500   0.1502   0.01745   0.00946   0.0056   0.6123   0.7847
   1.750   0.1752   0.01751   0.00961   0.0066   0.6005   0.8041
   2.000   0.2008   0.01757   0.00971   0.0075   0.5899   0.8256
   2.250   0.2277   0.01762   0.00979   0.0084   0.5792   0.8485
   2.500   0.2569   0.01775   0.01004   0.0086   0.5671   0.8725
   2.750   0.2914   0.01793   0.01027   0.0078   0.5554   0.8966
   3.000   0.3339   0.01814   0.01049   0.0056   0.5438   0.9189
   3.250   0.3808   0.01837   0.01070   0.0023   0.5313   0.9401
   3.500   0.4348   0.01864   0.01099  -0.0027   0.5170   0.9572
   3.750   0.4897   0.01886   0.01125  -0.0081   0.5025   0.9752
   4.000   0.5456   0.01901   0.01142  -0.0139   0.4879   0.9938
   4.250   0.5725   0.01914   0.01158  -0.0149   0.4768   1.0000
   4.500   0.5851   0.01924   0.01157  -0.0128   0.4688   1.0000
   4.750   0.5993   0.01957   0.01196  -0.0110   0.4578   1.0000
   5.000   0.6181   0.01988   0.01225  -0.0096   0.4480   1.0000
   5.250   0.6395   0.02012   0.01240  -0.0084   0.4381   1.0000
   5.500   0.6595   0.02051   0.01289  -0.0072   0.4262   1.0000
   5.750   0.6810   0.02086   0.01325  -0.0060   0.4151   1.0000
   6.000   0.7046   0.02107   0.01336  -0.0050   0.4048   1.0000
   6.250   0.7265   0.02136   0.01371  -0.0039   0.3925   1.0000
   6.500   0.7481   0.02171   0.01412  -0.0027   0.3798   1.0000
   6.750   0.7704   0.02201   0.01446  -0.0016   0.3673   1.0000
   7.000   0.7933   0.02224   0.01468  -0.0006   0.3548   1.0000
   7.250   0.8167   0.02243   0.01485   0.0004   0.3419   1.0000
   7.500   0.8399   0.02260   0.01498   0.0014   0.3284   1.0000
   7.750   0.8623   0.02279   0.01516   0.0025   0.3139   1.0000
   8.000   0.8836   0.02303   0.01544   0.0037   0.2985   1.0000
   8.250   0.9036   0.02333   0.01583   0.0051   0.2819   1.0000
   8.500   0.9227   0.02365   0.01622   0.0064   0.2640   1.0000
   8.750   0.9413   0.02400   0.01658   0.0079   0.2450   1.0000
   9.000   0.9591   0.02441   0.01688   0.0093   0.2257   1.0000
   9.250   0.9736   0.02509   0.01762   0.0111   0.2045   1.0000
   9.500   0.9871   0.02585   0.01833   0.0128   0.1839   1.0000
   9.750   0.9986   0.02689   0.01930   0.0147   0.1644   1.0000
  10.000   1.0081   0.02810   0.02052   0.0166   0.1459   1.0000
  10.250   1.0166   0.02947   0.02183   0.0186   0.1304   1.0000
  10.500   1.0240   0.03098   0.02331   0.0206   0.1173   1.0000
  10.750   1.0313   0.03267   0.02495   0.0226   0.1066   1.0000
  11.000   1.0411   0.03443   0.02654   0.0242   0.0975   1.0000
  11.250   1.0432   0.03604   0.02834   0.0266   0.0906   1.0000
  11.500   1.0557   0.03809   0.03029   0.0278   0.0842   1.0000
  11.750   1.0575   0.04002   0.03246   0.0298   0.0798   1.0000
  12.000   1.0695   0.04186   0.03418   0.0308   0.0749   1.0000
  12.250   1.0729   0.04441   0.03690   0.0320   0.0714   1.0000
  12.500   1.0703   0.04689   0.03963   0.0332   0.0688   1.0000
  12.750   1.0696   0.04950   0.04241   0.0339   0.0665   1.0000
  13.000   1.0776   0.05179   0.04469   0.0344   0.0637   1.0000
  13.250   1.0808   0.05536   0.04832   0.0347   0.0616   1.0000
  13.500   1.0640   0.05900   0.05226   0.0342   0.0608   1.0000
  13.750   1.0465   0.06336   0.05689   0.0329   0.0602   1.0000
  14.000   1.0264   0.06840   0.06219   0.0308   0.0598   1.0000
  14.250   1.0033   0.07434   0.06837   0.0278   0.0598   1.0000
  14.500   0.9778   0.08109   0.07534   0.0240   0.0601   1.0000
  14.750   0.9455   0.08933   0.08379   0.0188   0.0605   1.0000
  15.000   0.9137   0.09842   0.09304   0.0133   0.0613   1.0000
  15.250   0.7041   0.15890   0.15362  -0.0230   0.0868   1.0000
  15.500   0.7178   0.16192   0.15666  -0.0224   0.0855   1.0000
<< Back to E169 (14.4%) (e169-il)

Polar data table (+)

Polar graphs


<< Back to E169 (14.4%) (e169-il)