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NACA 66(2)-215 (naca662215-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 66(2)-215 (naca662215-il)
Reynolds number: 100,000
Max Cl/Cd: 37.57 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca662215-il-100000.txt
Download as CSV file: xf-naca662215-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66(2)-215                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.4662   0.11008   0.10524  -0.0472   1.0000   0.1595
 -11.000  -0.4975   0.10840   0.10368  -0.0451   1.0000   0.1646
 -10.750  -0.5763   0.10467   0.10018  -0.0470   1.0000   0.1667
 -10.500  -0.5235   0.10388   0.09930  -0.0402   1.0000   0.1721
 -10.250  -0.5359   0.10191   0.09738  -0.0380   1.0000   0.1772
 -10.000  -0.6103   0.09690   0.09255  -0.0404   1.0000   0.1814
  -9.750  -0.5795   0.09572   0.09134  -0.0354   1.0000   0.1875
  -9.500  -0.5994   0.09284   0.08853  -0.0341   1.0000   0.1931
  -9.250  -0.4955   0.09386   0.08982  -0.0263   1.0000   0.2066
  -7.000  -0.8760   0.04936   0.04215   0.0014   1.0000   0.0956
  -6.750  -0.8652   0.04524   0.03698   0.0054   1.0000   0.0801
  -6.500  -0.8478   0.04329   0.03475   0.0072   1.0000   0.0783
  -6.250  -0.8324   0.04112   0.03224   0.0090   1.0000   0.0784
  -6.000  -0.8148   0.03893   0.02976   0.0105   1.0000   0.0782
  -5.750  -0.7956   0.03682   0.02741   0.0118   1.0000   0.0777
  -5.500  -0.7753   0.03504   0.02536   0.0131   1.0000   0.0775
  -5.250  -0.7544   0.03358   0.02367   0.0143   1.0000   0.0777
  -5.000  -0.7337   0.03255   0.02239   0.0156   1.0000   0.0788
  -4.750  -0.7116   0.03084   0.02073   0.0163   1.0000   0.0814
  -4.500  -0.6908   0.02979   0.01969   0.0173   1.0000   0.0841
  -4.250  -0.6702   0.02893   0.01881   0.0184   1.0000   0.0864
  -4.000  -0.6505   0.02818   0.01803   0.0197   1.0000   0.0896
  -3.750  -0.6320   0.02751   0.01734   0.0211   1.0000   0.0937
  -3.500  -0.6158   0.02664   0.01660   0.0227   1.0000   0.0998
  -3.250  -0.5985   0.02608   0.01598   0.0242   1.0000   0.1065
  -3.000  -0.5823   0.02537   0.01536   0.0257   1.0000   0.1165
  -2.750  -0.5657   0.02460   0.01480   0.0272   1.0000   0.1433
  -2.500  -0.5752   0.02201   0.01547   0.0349   1.0000   0.6861
  -2.250  -0.5744   0.02369   0.01720   0.0436   1.0000   0.7883
  -2.000  -0.2752   0.03714   0.03009   0.0103   0.9786   0.9332
  -1.750  -0.2182   0.03725   0.03002   0.0035   0.9750   0.9407
  -1.500  -0.1906   0.03733   0.02999   0.0020   0.9730   0.9480
  -1.250  -0.1493   0.03740   0.02993  -0.0021   0.9700   0.9536
  -1.000  -0.1360   0.03736   0.02983  -0.0008   0.9681   0.9599
  -0.750  -0.0978   0.03729   0.02969  -0.0044   0.9651   0.9644
  -0.500  -0.0671   0.03743   0.02975  -0.0066   0.9616   0.9690
  -0.250  -0.0320   0.03778   0.03004  -0.0096   0.9573   0.9730
   0.000  -0.0067   0.03765   0.02989  -0.0108   0.9532   0.9764
   0.250   0.0218   0.03779   0.02999  -0.0125   0.9489   0.9798
   0.500   0.0603   0.03823   0.03041  -0.0161   0.9428   0.9824
   0.750   0.0790   0.03820   0.03037  -0.0160   0.9373   0.9852
   1.000   0.1207   0.03852   0.03069  -0.0201   0.9309   0.9874
   1.250   0.1438   0.03866   0.03085  -0.0208   0.9239   0.9898
   1.500   0.1774   0.03896   0.03117  -0.0233   0.9169   0.9918
   1.750   0.2027   0.03922   0.03146  -0.0243   0.9086   0.9939
   2.000   0.2400   0.03951   0.03180  -0.0274   0.9009   0.9954
   2.250   0.2642   0.03972   0.03206  -0.0281   0.8915   0.9973
   2.500   0.3131   0.04009   0.03250  -0.0330   0.8836   0.9987
   2.750   0.3281   0.04020   0.03267  -0.0319   0.8721   1.0000
   3.000   0.3530   0.04043   0.03298  -0.0323   0.8619   1.0000
   3.250   0.3888   0.04058   0.03322  -0.0344   0.8525   1.0000
   3.500   0.4006   0.04070   0.03341  -0.0324   0.8398   1.0000
   3.750   0.4232   0.04082   0.03363  -0.0321   0.8283   1.0000
   4.000   0.4707   0.04073   0.03369  -0.0357   0.8198   1.0000
   4.250   0.4849   0.04068   0.03374  -0.0338   0.8060   1.0000
   4.500   0.5058   0.04054   0.03371  -0.0328   0.7925   1.0000
   4.750   0.5644   0.03906   0.03246  -0.0363   0.7758   1.0000
   5.000   0.8355   0.02224   0.01634  -0.0588   0.6730   1.0000
   5.250   0.8182   0.02218   0.01387  -0.0469   0.2862   1.0000
   5.500   0.7925   0.02401   0.01477  -0.0383   0.1649   1.0000
   5.750   0.7779   0.02512   0.01552  -0.0313   0.1295   1.0000
   6.000   0.7689   0.02585   0.01616  -0.0253   0.1164   1.0000
   6.250   0.7615   0.02655   0.01684  -0.0197   0.1080   1.0000
   6.500   0.7561   0.02722   0.01750  -0.0146   0.1020   1.0000
   6.750   0.7525   0.02794   0.01820  -0.0098   0.0970   1.0000
   7.000   0.7532   0.02853   0.01881  -0.0057   0.0919   1.0000
   7.250   0.7577   0.02933   0.01952  -0.0023   0.0872   1.0000
   7.500   0.7810   0.03031   0.02047  -0.0014   0.0831   1.0000
   7.750   0.8128   0.03136   0.02155  -0.0019   0.0786   1.0000
   8.000   0.9180   0.03505   0.02517  -0.0149   0.0715   1.0000
   8.250   0.9515   0.03688   0.02725  -0.0158   0.0704   1.0000
   8.500   0.9719   0.03855   0.02918  -0.0145   0.0693   1.0000
   8.750   0.9854   0.04017   0.03108  -0.0123   0.0683   1.0000
   9.000   0.9934   0.04174   0.03290  -0.0092   0.0674   1.0000
   9.250   0.9988   0.04354   0.03497  -0.0058   0.0673   1.0000
   9.500   1.0003   0.04552   0.03724  -0.0018   0.0680   1.0000
   9.750   0.9970   0.04747   0.03945   0.0029   0.0690   1.0000
  10.000   0.9903   0.04937   0.04156   0.0080   0.0699   1.0000
  10.250   0.9859   0.05165   0.04402   0.0124   0.0710   1.0000
  10.500   1.0059   0.05638   0.04886   0.0126   0.0734   1.0000
  10.750   0.9605   0.05713   0.05044   0.0230   0.0790   1.0000
  11.000   0.9776   0.06411   0.05754   0.0223   0.0851   1.0000
  11.250   0.8856   0.06173   0.05601   0.0328   0.0992   1.0000
  11.500   0.8449   0.06328   0.05780   0.0383   0.0986   1.0000
  11.750   0.7987   0.06604   0.06082   0.0422   0.0977   1.0000
  12.000   0.6238   0.11231   0.10739   0.0154   0.1966   1.0000
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