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NACA M23 AIRFOIL (m23-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA M23 AIRFOIL (m23-il)
Reynolds number: 50,000
Max Cl/Cd: 23.56 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-m23-il-50000-n5.txt
Download as CSV file: xf-m23-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA M23 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3161   0.11599   0.11041  -0.0097   0.8411   0.0589
  -8.250  -0.3158   0.11526   0.10967  -0.0135   0.8307   0.0595
  -8.000  -0.3126   0.11481   0.10918  -0.0183   0.8209   0.0599
  -7.750  -0.2981   0.10607   0.10045  -0.0134   0.8134   0.0624
  -7.500  -0.2908   0.10281   0.09717  -0.0137   0.8053   0.0650
  -7.250  -0.2820   0.09998   0.09430  -0.0158   0.7970   0.0678
  -7.000  -0.2735   0.09766   0.09193  -0.0184   0.7896   0.0705
  -6.750  -0.2597   0.09681   0.09100  -0.0245   0.7811   0.0728
  -6.500  -0.2436   0.09668   0.09067  -0.0303   0.7743   0.0736
  -6.250  -0.2352   0.08950   0.08357  -0.0280   0.7672   0.0751
  -6.000  -0.2251   0.08536   0.07941  -0.0270   0.7609   0.0785
  -5.750  -0.2091   0.08266   0.07663  -0.0294   0.7537   0.0842
  -5.500  -0.1797   0.08382   0.07745  -0.0372   0.7467   0.0884
  -5.250  -0.1733   0.07723   0.07097  -0.0348   0.7409   0.0906
  -5.000  -0.1579   0.07377   0.06746  -0.0354   0.7342   0.0944
  -4.750  -0.1375   0.07157   0.06506  -0.0373   0.7289   0.1004
  -4.500  -0.1117   0.06934   0.06264  -0.0409   0.7214   0.1043
  -4.250  -0.0982   0.06573   0.05898  -0.0401   0.7160   0.1108
  -3.750  -0.0536   0.06071   0.05365  -0.0431   0.7036   0.1239
  -3.500  -0.0254   0.05956   0.05213  -0.0449   0.6987   0.1324
  -3.250  -0.0070   0.05613   0.04870  -0.0452   0.6916   0.1378
  -3.000   0.0162   0.05412   0.04646  -0.0458   0.6865   0.1496
  -2.750   0.0384   0.05205   0.04422  -0.0463   0.6807   0.1646
  -2.500   0.0618   0.05009   0.04209  -0.0469   0.6745   0.1793
  -2.250   0.0841   0.04811   0.03991  -0.0467   0.6701   0.1948
  -2.000   0.1082   0.04660   0.03823  -0.0475   0.6634   0.2210
  -1.500   0.1854   0.04319   0.03368  -0.0488   0.6544   0.0996
  -1.250   0.2132   0.04191   0.03219  -0.0497   0.6471   0.0981
  -0.750   0.2707   0.03926   0.02878  -0.0492   0.6379   0.0860
  -0.500   0.2980   0.03823   0.02756  -0.0497   0.6312   0.0836
  -0.250   0.3256   0.03712   0.02614  -0.0493   0.6267   0.0814
   0.000   0.3540   0.03628   0.02502  -0.0495   0.6215   0.0796
   0.250   0.3826   0.03562   0.02408  -0.0498   0.6154   0.0784
   0.500   0.4113   0.03477   0.02295  -0.0495   0.6114   0.0777
   0.750   0.4420   0.03443   0.02238  -0.0504   0.6054   0.0789
   1.000   0.4743   0.03419   0.02189  -0.0514   0.5997   0.0835
   1.250   0.5078   0.03366   0.02101  -0.0517   0.5959   0.0868
   1.500   0.5387   0.03368   0.02087  -0.0529   0.5894   0.0880
   1.750   0.5669   0.03342   0.02054  -0.0531   0.5842   0.0900
   2.000   0.5927   0.03304   0.02004  -0.0523   0.5808   0.0931
   2.250   0.6148   0.03356   0.02055  -0.0525   0.5738   0.0969
   2.500   0.6376   0.03363   0.02049  -0.0517   0.5690   0.1023
   2.750   0.6610   0.03341   0.02022  -0.0505   0.5658   0.1112
   3.000   0.6802   0.03437   0.02127  -0.0508   0.5583   0.1288
   3.250   0.7009   0.03428   0.02151  -0.0499   0.5538   0.2107
   3.500   0.7785   0.03304   0.02121  -0.0590   0.5505   1.0000
   3.750   0.7947   0.03472   0.02291  -0.0593   0.5422   1.0000
   4.000   0.8167   0.03518   0.02326  -0.0584   0.5382   1.0000
   4.250   0.8377   0.03581   0.02381  -0.0576   0.5340   1.0000
   4.500   0.8515   0.03749   0.02555  -0.0574   0.5263   1.0000
   4.750   0.8737   0.03789   0.02592  -0.0564   0.5227   1.0000
   5.000   0.8853   0.03972   0.02781  -0.0560   0.5156   1.0000
   5.250   0.9020   0.04080   0.02892  -0.0552   0.5102   1.0000
   5.500   0.9253   0.04105   0.02920  -0.0542   0.5072   1.0000
   5.750   0.9254   0.04407   0.03233  -0.0537   0.4978   1.0000
   6.000   0.9456   0.04468   0.03297  -0.0527   0.4940   1.0000
   6.250   0.9632   0.04561   0.03395  -0.0518   0.4898   1.0000
   6.500   0.9587   0.04896   0.03741  -0.0512   0.4804   1.0000
   6.750   0.9828   0.04914   0.03770  -0.0501   0.4777   1.0000
   7.250   0.9876   0.05442   0.04315  -0.0488   0.4633   1.0000
   7.750   0.9845   0.06007   0.04894  -0.0469   0.4490   1.0000
   8.250   0.9821   0.06572   0.05475  -0.0452   0.4352   1.0000
   8.500   1.0018   0.06653   0.05570  -0.0444   0.4319   1.0000
   8.750   0.9831   0.07130   0.06052  -0.0440   0.4218   1.0000
   9.000   1.0057   0.07183   0.06127  -0.0431   0.4188   1.0000
   9.250   0.9868   0.07676   0.06623  -0.0430   0.4089   1.0000
   9.500   1.0059   0.07769   0.06736  -0.0422   0.4052   1.0000
   9.750   0.9942   0.08197   0.07171  -0.0422   0.3967   1.0000
  10.000   1.0077   0.08351   0.07344  -0.0416   0.3918   1.0000
  10.250   1.0083   0.08624   0.07630  -0.0411   0.3838   1.0000
  10.500   1.0359   0.08373   0.07407  -0.0385   0.3691   1.0000
  10.750   1.0637   0.08135   0.07195  -0.0361   0.3565   1.0000
  11.000   1.0871   0.07814   0.06900  -0.0332   0.3352   1.0000
  11.250   1.1141   0.07475   0.06593  -0.0305   0.3150   1.0000
  11.500   1.1040   0.07840   0.06970  -0.0305   0.2966   1.0000
  11.750   1.0983   0.08098   0.07241  -0.0302   0.2692   1.0000
  12.000   1.0890   0.08492   0.07652  -0.0305   0.2404   1.0000
  12.250   1.0872   0.08469   0.07437  -0.0276   0.0726   1.0000
  12.500   1.0751   0.08974   0.07931  -0.0283   0.0622   1.0000
  12.750   1.0659   0.09451   0.08405  -0.0290   0.0559   1.0000
  13.000   1.0597   0.09891   0.08849  -0.0296   0.0511   1.0000
  13.250   1.0536   0.10331   0.09290  -0.0303   0.0476   1.0000
  13.500   1.0498   0.10738   0.09699  -0.0309   0.0446   1.0000
  13.750   1.0490   0.11098   0.10070  -0.0314   0.0417   1.0000
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