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NACA-0009 9.0% smoothed (n0009sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA-0009 9.0% smoothed (n0009sm-il)
Reynolds number: 500,000
Max Cl/Cd: 55.91 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n0009sm-il-500000.txt
Download as CSV file: xf-n0009sm-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA-0009 9.0% smoothed                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.9606   0.06449   0.06155  -0.0264   1.0000   0.0073
 -13.250  -0.9745   0.05737   0.05426  -0.0319   1.0000   0.0074
 -13.000  -1.0011   0.04929   0.04597  -0.0377   1.0000   0.0072
 -12.750  -1.0177   0.04406   0.04052  -0.0404   1.0000   0.0073
 -12.500  -1.0291   0.04040   0.03666  -0.0409   1.0000   0.0073
 -12.250  -1.0369   0.03768   0.03375  -0.0399   1.0000   0.0074
 -12.000  -1.0608   0.03389   0.02966  -0.0366   1.0000   0.0075
 -11.750  -1.0741   0.03140   0.02693  -0.0323   1.0000   0.0076
 -11.500  -1.0836   0.02901   0.02431  -0.0279   1.0000   0.0079
 -11.250  -1.0805   0.02724   0.02237  -0.0250   1.0000   0.0082
 -11.000  -1.0713   0.02596   0.02096  -0.0227   1.0000   0.0085
 -10.750  -1.0593   0.02486   0.01974  -0.0206   1.0000   0.0089
 -10.500  -1.0463   0.02376   0.01851  -0.0186   1.0000   0.0094
 -10.250  -1.0324   0.02269   0.01729  -0.0166   1.0000   0.0101
 -10.000  -1.0141   0.02207   0.01653  -0.0151   1.0000   0.0108
  -9.750  -1.0053   0.02030   0.01459  -0.0124   1.0000   0.0121
  -9.500  -0.9869   0.01967   0.01392  -0.0109   1.0000   0.0134
  -9.250  -0.9677   0.01908   0.01326  -0.0095   1.0000   0.0148
  -9.000  -0.9473   0.01860   0.01267  -0.0082   1.0000   0.0160
  -8.750  -0.9343   0.01724   0.01122  -0.0058   1.0000   0.0185
  -8.500  -0.9127   0.01692   0.01089  -0.0047   1.0000   0.0209
  -8.250  -0.8880   0.01701   0.01092  -0.0041   1.0000   0.0230
  -8.000  -0.8723   0.01595   0.00984  -0.0020   1.0000   0.0269
  -7.750  -0.8495   0.01580   0.00964  -0.0011   1.0000   0.0299
  -7.500  -0.8256   0.01582   0.00959  -0.0003   1.0000   0.0319
  -7.250  -0.8101   0.01469   0.00841   0.0018   1.0000   0.0354
  -7.000  -0.7886   0.01438   0.00808   0.0030   1.0000   0.0381
  -6.750  -0.7671   0.01405   0.00770   0.0043   1.0000   0.0407
  -6.500  -0.7446   0.01388   0.00746   0.0054   1.0000   0.0426
  -6.250  -0.7271   0.01308   0.00661   0.0073   1.0000   0.0464
  -6.000  -0.7062   0.01272   0.00625   0.0086   1.0000   0.0496
  -5.750  -0.6849   0.01241   0.00589   0.0099   1.0000   0.0527
  -5.500  -0.6630   0.01219   0.00562   0.0111   1.0000   0.0548
  -5.250  -0.6448   0.01154   0.00494   0.0130   1.0000   0.0595
  -5.000  -0.6239   0.01121   0.00461   0.0144   1.0000   0.0637
  -4.750  -0.6024   0.01098   0.00432   0.0156   1.0000   0.0675
  -4.500  -0.5825   0.01056   0.00394   0.0172   1.0000   0.0756
  -4.250  -0.5614   0.01029   0.00366   0.0185   1.0000   0.0844
  -4.000  -0.5410   0.00995   0.00341   0.0199   1.0000   0.0999
  -3.750  -0.5211   0.00958   0.00319   0.0214   1.0000   0.1309
  -3.500  -0.5018   0.00916   0.00300   0.0228   1.0000   0.1834
  -3.250  -0.4658   0.00869   0.00286   0.0207   0.9968   0.2576
  -3.000  -0.4292   0.00831   0.00278   0.0185   0.9935   0.3301
  -2.750  -0.3949   0.00794   0.00265   0.0169   0.9891   0.3905
  -2.500  -0.3587   0.00762   0.00255   0.0149   0.9850   0.4506
  -2.250  -0.3206   0.00730   0.00247   0.0126   0.9818   0.5164
  -2.000  -0.2893   0.00697   0.00236   0.0118   0.9754   0.5718
  -1.750  -0.2533   0.00667   0.00226   0.0101   0.9709   0.6279
  -1.500  -0.2183   0.00637   0.00218   0.0087   0.9663   0.6827
  -1.250  -0.1878   0.00605   0.00212   0.0084   0.9595   0.7449
  -1.000  -0.1507   0.00577   0.00207   0.0068   0.9555   0.8048
  -0.750  -0.1175   0.00559   0.00201   0.0061   0.9471   0.8417
  -0.500  -0.0775   0.00546   0.00197   0.0039   0.9408   0.8719
  -0.250  -0.0411   0.00539   0.00196   0.0024   0.9290   0.8971
   0.000   0.0000   0.00536   0.00195   0.0000   0.9152   0.9152
   0.250   0.0411   0.00539   0.00196  -0.0025   0.8974   0.9291
   0.500   0.0775   0.00545   0.00197  -0.0038   0.8717   0.9408
   0.750   0.1176   0.00559   0.00201  -0.0061   0.8410   0.9472
   1.000   0.1507   0.00576   0.00207  -0.0068   0.8052   0.9555
   1.250   0.1876   0.00605   0.00212  -0.0084   0.7446   0.9594
   1.500   0.2183   0.00637   0.00219  -0.0087   0.6833   0.9665
   1.750   0.2534   0.00666   0.00226  -0.0101   0.6290   0.9709
   2.000   0.2894   0.00697   0.00236  -0.0118   0.5719   0.9754
   2.250   0.3208   0.00729   0.00247  -0.0126   0.5167   0.9818
   2.500   0.3587   0.00762   0.00254  -0.0149   0.4506   0.9850
   2.750   0.3949   0.00794   0.00265  -0.0169   0.3904   0.9892
   3.000   0.4291   0.00831   0.00277  -0.0184   0.3299   0.9935
   3.250   0.4659   0.00869   0.00286  -0.0207   0.2566   0.9968
   3.500   0.5018   0.00916   0.00300  -0.0228   0.1827   1.0000
   3.750   0.5210   0.00957   0.00319  -0.0213   0.1315   1.0000
   4.000   0.5408   0.00995   0.00341  -0.0199   0.0997   1.0000
   4.250   0.5613   0.01028   0.00366  -0.0185   0.0844   1.0000
   4.500   0.5823   0.01056   0.00393  -0.0171   0.0755   1.0000
   4.750   0.6022   0.01098   0.00431  -0.0156   0.0674   1.0000
   5.000   0.6238   0.01121   0.00461  -0.0143   0.0636   1.0000
   5.250   0.6446   0.01153   0.00494  -0.0130   0.0594   1.0000
   5.500   0.6628   0.01220   0.00562  -0.0111   0.0549   1.0000
   5.750   0.6847   0.01242   0.00590  -0.0099   0.0527   1.0000
   6.000   0.7060   0.01273   0.00625  -0.0086   0.0496   1.0000
   6.250   0.7270   0.01308   0.00661  -0.0072   0.0464   1.0000
   6.500   0.7443   0.01390   0.00748  -0.0053   0.0426   1.0000
   6.750   0.7669   0.01407   0.00772  -0.0042   0.0407   1.0000
   7.000   0.7885   0.01438   0.00808  -0.0030   0.0381   1.0000
   7.250   0.8099   0.01470   0.00843  -0.0018   0.0354   1.0000
   7.500   0.8255   0.01582   0.00959   0.0003   0.0319   1.0000
   7.750   0.8495   0.01580   0.00964   0.0011   0.0299   1.0000
   8.000   0.8722   0.01596   0.00985   0.0021   0.0269   1.0000
   8.250   0.8884   0.01695   0.01086   0.0040   0.0230   1.0000
   8.500   0.9127   0.01692   0.01089   0.0047   0.0209   1.0000
   8.750   0.9343   0.01724   0.01123   0.0058   0.0185   1.0000
   9.000   0.9476   0.01857   0.01263   0.0082   0.0160   1.0000
   9.250   0.9683   0.01901   0.01318   0.0094   0.0147   1.0000
   9.500   0.9872   0.01964   0.01389   0.0109   0.0133   1.0000
   9.750   1.0051   0.02033   0.01462   0.0124   0.0121   1.0000
  10.000   1.0138   0.02213   0.01660   0.0152   0.0108   1.0000
  10.250   1.0302   0.02299   0.01763   0.0169   0.0102   1.0000
  10.500   1.0455   0.02389   0.01866   0.0187   0.0096   1.0000
  10.750   1.0594   0.02488   0.01976   0.0206   0.0089   1.0000
  11.000   1.0708   0.02606   0.02108   0.0227   0.0086   1.0000
  11.250   1.0802   0.02733   0.02247   0.0250   0.0082   1.0000
  11.500   1.0836   0.02905   0.02435   0.0279   0.0079   1.0000
  11.750   1.0759   0.03134   0.02686   0.0321   0.0076   1.0000
  12.000   1.0573   0.03426   0.03007   0.0368   0.0075   1.0000
  12.250   1.0474   0.03678   0.03279   0.0394   0.0074   1.0000
  12.750   1.0188   0.04405   0.04050   0.0402   0.0073   1.0000
  13.000   0.9975   0.04994   0.04663   0.0372   0.0074   1.0000
  13.250   0.9841   0.05587   0.05273   0.0329   0.0074   1.0000
  13.500   0.9716   0.06249   0.05950   0.0278   0.0074   1.0000
  13.750   0.9556   0.07034   0.06750   0.0221   0.0075   1.0000
  14.000   0.9304   0.08038   0.07769   0.0154   0.0075   1.0000
  14.250   0.9222   0.08669   0.08407   0.0118   0.0077   1.0000
  14.500   0.8787   0.10107   0.09862   0.0040   0.0080   1.0000
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