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

NACA 16-021 (naca16021-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: NACA 16-021 (naca16021-il)
Reynolds number: 200,000
Max Cl/Cd: 33.65 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca16021-il-200000.txt
Download as CSV file: xf-naca16021-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 16-021                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -0.8482   0.12203   0.11783  -0.0673   1.0000   0.0471
 -18.000  -0.8872   0.11320   0.10886  -0.0700   1.0000   0.0467
 -17.750  -0.9258   0.10537   0.10085  -0.0715   1.0000   0.0465
 -17.500  -0.9627   0.09854   0.09382  -0.0718   1.0000   0.0463
 -17.250  -0.9981   0.09253   0.08760  -0.0711   1.0000   0.0462
 -17.000  -1.0313   0.08726   0.08211  -0.0694   1.0000   0.0461
 -16.750  -1.0626   0.08258   0.07720  -0.0669   1.0000   0.0462
 -16.500  -1.0911   0.07848   0.07286  -0.0638   1.0000   0.0462
 -16.250  -1.1174   0.07480   0.06895  -0.0603   1.0000   0.0464
 -16.000  -1.1420   0.07149   0.06539  -0.0563   1.0000   0.0465
 -15.750  -1.1648   0.06851   0.06216  -0.0519   1.0000   0.0467
 -15.500  -1.1863   0.06585   0.05924  -0.0473   1.0000   0.0469
 -15.250  -1.2074   0.06351   0.05664  -0.0422   1.0000   0.0472
 -15.000  -1.2197   0.06097   0.05387  -0.0380   1.0000   0.0476
 -14.750  -1.2060   0.05913   0.05205  -0.0372   1.0000   0.0486
 -14.500  -1.2051   0.05778   0.05064  -0.0343   1.0000   0.0494
 -14.250  -1.2036   0.05649   0.04927  -0.0315   1.0000   0.0502
 -14.000  -1.2037   0.05510   0.04775  -0.0283   1.0000   0.0509
 -13.750  -1.2038   0.05363   0.04612  -0.0249   1.0000   0.0518
 -13.500  -1.2030   0.05216   0.04445  -0.0216   1.0000   0.0525
 -13.250  -1.2024   0.05078   0.04286  -0.0181   1.0000   0.0534
 -13.000  -1.2042   0.04958   0.04143  -0.0141   1.0000   0.0541
 -12.750  -1.1811   0.04808   0.03984  -0.0142   1.0000   0.0556
 -12.500  -1.1642   0.04721   0.03900  -0.0132   1.0000   0.0569
 -12.250  -1.1527   0.04637   0.03810  -0.0112   1.0000   0.0581
 -12.000  -1.1405   0.04552   0.03716  -0.0093   1.0000   0.0594
 -11.750  -1.1287   0.04471   0.03623  -0.0073   1.0000   0.0608
 -11.500  -1.1195   0.04396   0.03532  -0.0048   1.0000   0.0621
 -11.250  -1.0925   0.04314   0.03449  -0.0052   1.0000   0.0641
 -11.000  -1.0760   0.04252   0.03390  -0.0040   1.0000   0.0658
 -10.750  -1.0621   0.04193   0.03329  -0.0023   1.0000   0.0675
 -10.500  -1.0496   0.04134   0.03263  -0.0003   1.0000   0.0695
 -10.250  -1.0385   0.04080   0.03197   0.0020   1.0000   0.0714
 -10.000  -1.0201   0.04012   0.03135   0.0030   1.0000   0.0741
  -9.750  -1.0095   0.03952   0.03078   0.0053   1.0000   0.0765
  -9.500  -0.9992   0.03896   0.03018   0.0077   1.0000   0.0792
  -9.250  -0.9892   0.03846   0.02958   0.0102   1.0000   0.0820
  -9.000  -0.9811   0.03765   0.02886   0.0129   1.0000   0.0857
  -8.750  -0.9736   0.03706   0.02827   0.0158   1.0000   0.0898
  -8.500  -0.9656   0.03650   0.02765   0.0187   1.0000   0.0946
  -8.250  -0.8717   0.03580   0.02711   0.0032   0.9799   0.1178
  -8.000  -0.8677   0.03500   0.02640   0.0067   0.9781   0.1297
  -7.750  -0.8631   0.03429   0.02577   0.0102   0.9767   0.1454
  -7.500  -0.8518   0.03352   0.02515   0.0122   0.9738   0.1699
  -7.250  -0.8357   0.03253   0.02442   0.0131   0.9675   0.2109
  -7.000  -0.8389   0.03149   0.02364   0.0181   0.9641   0.2533
  -6.750  -0.8475   0.03045   0.02292   0.0242   0.9623   0.3065
  -6.500  -0.8601   0.02930   0.02215   0.0312   0.9602   0.3739
  -6.250  -0.8766   0.02789   0.02120   0.0393   0.9534   0.4541
  -6.000  -0.9012   0.02680   0.02054   0.0496   0.9508   0.5232
  -5.750  -0.8347   0.02804   0.02284   0.0428   0.9483   0.7025
  -5.500  -0.7977   0.02917   0.02397   0.0414   0.9460   0.7398
  -5.250  -0.7422   0.03111   0.02583   0.0365   0.9441   0.7616
  -4.750  -0.7226   0.03219   0.02681   0.0444   0.9344   0.7891
  -4.500  -0.6485   0.03512   0.02963   0.0363   0.9328   0.7916
  -4.250  -0.6310   0.03555   0.02996   0.0382   0.9305   0.8043
  -4.000  -0.5583   0.03779   0.03208   0.0297   0.9295   0.8053
  -3.250  -0.4205   0.04272   0.03683   0.0205   0.9198   0.8219
  -3.000  -0.3539   0.04447   0.03853   0.0132   0.9186   0.8244
  -2.750  -0.3345   0.04469   0.03869   0.0142   0.9162   0.8354
  -2.500  -0.2827   0.04524   0.03917   0.0088   0.9150   0.8376
  -2.250  -0.2551   0.04570   0.03962   0.0084   0.9096   0.8398
  -2.000  -0.2242   0.04608   0.03997   0.0071   0.9062   0.8431
  -1.750  -0.2161   0.04581   0.03966   0.0101   0.9026   0.8530
  -1.500  -0.1669   0.04607   0.03987   0.0051   0.9010   0.8544
  -1.250  -0.1192   0.04629   0.04007   0.0003   0.8997   0.8563
  -1.000  -0.1465   0.04620   0.03998   0.0104   0.8908   0.8679
  -0.750  -0.1018   0.04635   0.04010   0.0062   0.8883   0.8692
  -0.500  -0.0562   0.04646   0.04020   0.0018   0.8864   0.8708
  -0.250  -0.0101   0.04651   0.04025  -0.0027   0.8848   0.8729
   0.000   0.0271   0.04657   0.04030  -0.0054   0.8824   0.8762
   0.250   0.0102   0.04651   0.04025   0.0026   0.8729   0.8848
   0.500   0.0562   0.04646   0.04021  -0.0018   0.8708   0.8864
   0.750   0.1018   0.04635   0.04010  -0.0062   0.8692   0.8883
   1.000   0.1464   0.04620   0.03997  -0.0104   0.8679   0.8908
   1.250   0.1192   0.04628   0.04006  -0.0003   0.8563   0.8997
   1.500   0.1671   0.04606   0.03986  -0.0051   0.8544   0.9010
   1.750   0.2161   0.04580   0.03965  -0.0101   0.8530   0.9026
   2.000   0.2243   0.04607   0.03995  -0.0071   0.8431   0.9063
   2.250   0.2547   0.04569   0.03960  -0.0083   0.8398   0.9097
   2.500   0.2826   0.04523   0.03916  -0.0088   0.8376   0.9150
   2.750   0.3342   0.04469   0.03868  -0.0141   0.8354   0.9162
   3.000   0.3538   0.04446   0.03851  -0.0132   0.8244   0.9186
   3.250   0.4204   0.04270   0.03681  -0.0205   0.8219   0.9198
   3.500   0.5146   0.03939   0.03357  -0.0323   0.8201   0.9203
   4.000   0.5584   0.03776   0.03206  -0.0298   0.8054   0.9295
   4.250   0.6310   0.03553   0.02994  -0.0382   0.8043   0.9305
   4.500   0.6486   0.03510   0.02960  -0.0363   0.7917   0.9329
   4.750   0.7224   0.03218   0.02680  -0.0444   0.7892   0.9344
   5.250   0.7425   0.03108   0.02580  -0.0366   0.7616   0.9441
   5.500   0.7977   0.02914   0.02394  -0.0414   0.7399   0.9460
   5.750   0.8348   0.02801   0.02281  -0.0428   0.7025   0.9483
   6.000   0.9012   0.02678   0.02051  -0.0496   0.5233   0.9507
   6.250   0.8765   0.02786   0.02118  -0.0393   0.4539   0.9534
   6.500   0.8599   0.02927   0.02212  -0.0311   0.3737   0.9602
   6.750   0.8475   0.03041   0.02288  -0.0242   0.3067   0.9622
   7.000   0.8389   0.03146   0.02361  -0.0181   0.2533   0.9641
   7.250   0.8358   0.03249   0.02439  -0.0131   0.2110   0.9676
   7.500   0.8515   0.03348   0.02510  -0.0121   0.1701   0.9737
   7.750   0.8627   0.03424   0.02572  -0.0101   0.1456   0.9765
   8.000   0.8675   0.03495   0.02634  -0.0067   0.1298   0.9780
   8.250   0.8718   0.03575   0.02705  -0.0032   0.1178   0.9799
   8.500   0.9659   0.03645   0.02760  -0.0188   0.0946   1.0000
   8.750   0.9739   0.03701   0.02822  -0.0159   0.0898   1.0000
   9.000   0.9814   0.03759   0.02880  -0.0130   0.0857   1.0000
   9.250   0.9895   0.03841   0.02952  -0.0103   0.0820   1.0000
   9.500   0.9996   0.03891   0.03012  -0.0078   0.0791   1.0000
   9.750   1.0099   0.03946   0.03072  -0.0053   0.0764   1.0000
  10.000   1.0206   0.04006   0.03129  -0.0031   0.0741   1.0000
  10.250   1.0388   0.04074   0.03191  -0.0021   0.0714   1.0000
  10.500   1.0499   0.04129   0.03257   0.0002   0.0695   1.0000
  10.750   1.0626   0.04187   0.03322   0.0022   0.0675   1.0000
  11.000   1.0766   0.04246   0.03384   0.0039   0.0658   1.0000
  11.250   1.0930   0.04308   0.03442   0.0051   0.0641   1.0000
  11.500   1.1203   0.04391   0.03526   0.0046   0.0621   1.0000
  11.750   1.1294   0.04466   0.03617   0.0072   0.0608   1.0000
  12.000   1.1411   0.04546   0.03710   0.0092   0.0594   1.0000
  12.250   1.1535   0.04631   0.03804   0.0111   0.0581   1.0000
  12.500   1.1649   0.04715   0.03894   0.0131   0.0569   1.0000
  12.750   1.1817   0.04802   0.03978   0.0141   0.0556   1.0000
  13.000   1.2054   0.04953   0.04138   0.0139   0.0541   1.0000
  13.250   1.2034   0.05073   0.04280   0.0180   0.0534   1.0000
  13.500   1.2040   0.05210   0.04439   0.0214   0.0526   1.0000
  13.750   1.2047   0.05357   0.04606   0.0248   0.0518   1.0000
  14.000   1.2045   0.05504   0.04769   0.0282   0.0510   1.0000
  14.250   1.2045   0.05644   0.04921   0.0314   0.0502   1.0000
  14.500   1.2059   0.05769   0.05055   0.0342   0.0493   1.0000
  14.750   1.2069   0.05906   0.05197   0.0371   0.0486   1.0000
  15.000   1.2194   0.06086   0.05376   0.0381   0.0476   1.0000
  15.250   1.2079   0.06343   0.05655   0.0421   0.0472   1.0000
  15.500   1.1871   0.06576   0.05915   0.0472   0.0469   1.0000
  15.750   1.1661   0.06842   0.06206   0.0518   0.0467   1.0000
  16.000   1.1434   0.07139   0.06528   0.0562   0.0465   1.0000
  16.250   1.1188   0.07468   0.06882   0.0602   0.0464   1.0000
  16.500   1.0920   0.07836   0.07274   0.0638   0.0462   1.0000
  16.750   1.0632   0.08248   0.07709   0.0669   0.0461   1.0000
  17.000   1.0325   0.08711   0.08195   0.0693   0.0461   1.0000
  17.250   0.9994   0.09236   0.08742   0.0710   0.0462   1.0000
  17.500   0.9643   0.09834   0.09362   0.0718   0.0463   1.0000
  17.750   0.9265   0.10527   0.10075   0.0715   0.0465   1.0000
  18.000   0.8878   0.11312   0.10877   0.0700   0.0467   1.0000
  18.250   0.8479   0.12212   0.11792   0.0672   0.0471   1.0000
<< Back to NACA 16-021 (naca16021-il)

Polar data table (+)

Polar graphs


<< Back to NACA 16-021 (naca16021-il)