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NACA M16 AIRFOIL (m16-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA M16 AIRFOIL (m16-il)
Reynolds number: 50,000
Max Cl/Cd: 38.95 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-m16-il-50000.txt
Download as CSV file: xf-m16-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M16 AIRFOIL                                
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5163   0.13160   0.12525   0.0219   1.0000   0.0924
  -9.250  -0.5185   0.13069   0.12443   0.0181   1.0000   0.0934
  -9.000  -0.5224   0.12998   0.12385   0.0136   1.0000   0.0939
  -8.750  -0.4966   0.11973   0.11351   0.0181   1.0000   0.0988
  -8.500  -0.4906   0.11635   0.11017   0.0166   1.0000   0.1027
  -8.250  -0.4890   0.11410   0.10799   0.0134   1.0000   0.1061
  -8.000  -0.4919   0.11314   0.10712   0.0078   1.0000   0.1075
  -7.750  -0.4794   0.10685   0.10088   0.0092   1.0000   0.1105
  -7.500  -0.4697   0.10274   0.09679   0.0086   1.0000   0.1158
  -7.250  -0.4641   0.10066   0.09475   0.0027   1.0000   0.1207
  -7.000  -0.4545   0.09609   0.09023   0.0012   1.0000   0.1244
  -6.750  -0.4433   0.09246   0.08662  -0.0006   1.0000   0.1331
  -6.250  -0.4186   0.08559   0.07977  -0.0073   1.0000   0.1484
  -6.000  -0.4058   0.08100   0.07519  -0.0081   1.0000   0.1546
  -5.500  -0.3700   0.07556   0.06960  -0.0176   1.0000   0.1781
  -5.250  -0.3529   0.07189   0.06591  -0.0195   1.0000   0.1920
  -5.000  -0.3375   0.06749   0.06156  -0.0202   1.0000   0.2065
  -4.750  -0.3248   0.06298   0.05716  -0.0191   1.0000   0.2247
  -4.500  -0.3104   0.05966   0.05387  -0.0200   1.0000   0.2519
  -4.250  -0.2999   0.05653   0.05080  -0.0197   1.0000   0.2809
  -4.000  -0.2981   0.05412   0.04846  -0.0178   1.0000   0.3085
  -3.750  -0.3023   0.05205   0.04647  -0.0146   1.0000   0.3375
  -3.000  -0.3147   0.04475   0.03943  -0.0020   1.0000   0.4669
  -2.750  -0.3125   0.04209   0.03683   0.0014   1.0000   0.5087
  -2.500  -0.3076   0.03942   0.03422   0.0046   1.0000   0.5505
  -2.250  -0.2978   0.03686   0.03169   0.0066   1.0000   0.5900
  -2.000  -0.2666   0.03399   0.02876   0.0041   0.9957   0.6204
  -1.750  -0.1803   0.03142   0.02559  -0.0129   0.9842   0.5984
  -1.500  -0.0231   0.03412   0.02598  -0.0435   0.9688   0.3017
  -1.250   0.0430   0.03319   0.02406  -0.0497   0.9572   0.2189
  -1.000   0.0939   0.03164   0.02197  -0.0536   0.9462   0.1889
  -0.750   0.1442   0.03034   0.02017  -0.0575   0.9354   0.1740
  -0.500   0.1981   0.02916   0.01852  -0.0620   0.9255   0.1660
  -0.250   0.2459   0.02828   0.01736  -0.0653   0.9146   0.1679
   0.000   0.2874   0.02787   0.01667  -0.0676   0.9025   0.1784
   0.250   0.3257   0.02734   0.01609  -0.0693   0.8907   0.1858
   0.500   0.3598   0.02701   0.01571  -0.0702   0.8790   0.1967
   0.750   0.3907   0.02677   0.01549  -0.0706   0.8675   0.2188
   1.000   0.4194   0.02557   0.01520  -0.0708   0.8572   0.3682
   1.250   0.4718   0.02501   0.01490  -0.0742   0.8450   1.0000
   1.500   0.4955   0.02577   0.01546  -0.0737   0.8323   1.0000
   1.750   0.5184   0.02658   0.01614  -0.0732   0.8199   1.0000
   2.000   0.5413   0.02741   0.01688  -0.0727   0.8078   1.0000
   2.250   0.5645   0.02825   0.01769  -0.0722   0.7962   1.0000
   2.500   0.5891   0.02904   0.01842  -0.0717   0.7852   1.0000
   2.750   0.6121   0.02990   0.01927  -0.0711   0.7738   1.0000
   3.000   0.6317   0.03101   0.02040  -0.0706   0.7618   1.0000
   3.250   0.6517   0.03213   0.02155  -0.0701   0.7501   1.0000
   3.500   0.6726   0.03325   0.02277  -0.0696   0.7391   1.0000
   3.750   0.6966   0.03415   0.02374  -0.0689   0.7290   1.0000
   4.000   0.7168   0.03537   0.02505  -0.0685   0.7179   1.0000
   4.250   0.7338   0.03686   0.02664  -0.0681   0.7061   1.0000
   4.500   0.7514   0.03839   0.02829  -0.0677   0.6950   1.0000
   4.750   0.7724   0.03966   0.02975  -0.0671   0.6845   1.0000
   5.000   0.7954   0.04078   0.03105  -0.0665   0.6745   1.0000
   5.250   0.8084   0.04277   0.03320  -0.0662   0.6625   1.0000
   5.500   0.8216   0.04480   0.03540  -0.0659   0.6510   1.0000
   5.750   0.8373   0.04663   0.03743  -0.0654   0.6399   1.0000
   6.000   0.8596   0.04794   0.03900  -0.0646   0.6293   1.0000
   6.250   0.8820   0.04896   0.04038  -0.0632   0.6163   1.0000
   6.500   0.9482   0.02904   0.02054  -0.0350   0.5116   1.0000
   6.750   0.9613   0.02468   0.01565  -0.0259   0.3350   1.0000
   7.000   0.9590   0.02880   0.01783  -0.0239   0.1380   1.0000
   7.250   0.9664   0.03174   0.02055  -0.0225   0.1134   1.0000
   7.500   0.9758   0.03411   0.02289  -0.0208   0.1026   1.0000
   7.750   0.9876   0.03618   0.02496  -0.0187   0.0960   1.0000
   8.000   1.0088   0.03798   0.02678  -0.0163   0.0914   1.0000
   8.250   1.0398   0.03981   0.02870  -0.0144   0.0866   1.0000
   8.500   1.0737   0.04289   0.03157  -0.0135   0.0809   1.0000
   8.750   1.1015   0.04584   0.03488  -0.0124   0.0799   1.0000
   9.000   1.1273   0.04956   0.03900  -0.0115   0.0803   1.0000
   9.250   1.1504   0.05398   0.04374  -0.0107   0.0813   1.0000
   9.500   1.1591   0.05682   0.04749  -0.0088   0.0840   1.0000
   9.750   1.1620   0.06133   0.05271  -0.0074   0.0873   1.0000
  10.000   1.1644   0.06624   0.05805  -0.0064   0.0903   1.0000
  10.250   1.1690   0.07156   0.06362  -0.0057   0.0927   1.0000
  10.500   1.1622   0.07602   0.06849  -0.0049   0.0952   1.0000
  10.750   1.1270   0.08023   0.07317  -0.0045   0.0971   1.0000
  11.000   1.0954   0.08518   0.07832  -0.0057   0.0981   1.0000
  11.250   1.0632   0.09146   0.08473  -0.0092   0.0986   1.0000
  11.500   1.0290   0.09943   0.09278  -0.0148   0.0992   1.0000
  11.750   0.9944   0.10946   0.10282  -0.0222   0.1008   1.0000
  12.000   0.9769   0.11852   0.11179  -0.0273   0.1043   1.0000
  12.250   0.9496   0.13124   0.12443  -0.0364   0.1110   1.0000
  12.500   0.7928   0.12374   0.11722  -0.0188   0.1047   1.0000
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