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NACA 0012 AIRFOILS (n0012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012 AIRFOILS (n0012-il)
Reynolds number: 50,000
Max Cl/Cd: 26.54 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n0012-il-50000-n5.txt
Download as CSV file: xf-n0012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012 AIRFOILS                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.7967   0.08718   0.07926  -0.0211   1.0000   0.0718
 -11.750  -0.8409   0.07647   0.06839  -0.0284   1.0000   0.0708
 -11.500  -0.8751   0.06932   0.06102  -0.0318   1.0000   0.0705
 -11.250  -0.9008   0.06422   0.05569  -0.0322   1.0000   0.0706
 -11.000  -0.9203   0.06020   0.05141  -0.0308   1.0000   0.0712
 -10.750  -0.9332   0.05655   0.04743  -0.0289   1.0000   0.0721
 -10.500  -0.9408   0.05300   0.04344  -0.0270   1.0000   0.0736
 -10.250  -0.9394   0.05004   0.04017  -0.0253   1.0000   0.0757
 -10.000  -0.9268   0.04819   0.03830  -0.0242   1.0000   0.0785
  -9.750  -0.9169   0.04592   0.03579  -0.0228   1.0000   0.0815
  -9.500  -0.9070   0.04340   0.03287  -0.0212   1.0000   0.0849
  -9.250  -0.8921   0.04144   0.03079  -0.0200   1.0000   0.0887
  -9.000  -0.8759   0.03979   0.02903  -0.0189   1.0000   0.0933
  -8.750  -0.8596   0.03785   0.02668  -0.0176   1.0000   0.0987
  -8.500  -0.8413   0.03641   0.02536  -0.0166   1.0000   0.1041
  -8.250  -0.8228   0.03486   0.02354  -0.0154   1.0000   0.1113
  -8.000  -0.8043   0.03353   0.02227  -0.0143   1.0000   0.1185
  -7.750  -0.7850   0.03218   0.02078  -0.0131   1.0000   0.1277
  -7.500  -0.7664   0.03098   0.01955  -0.0119   1.0000   0.1384
  -7.250  -0.7478   0.02982   0.01843  -0.0106   1.0000   0.1500
  -7.000  -0.7294   0.02872   0.01733  -0.0093   1.0000   0.1644
  -6.750  -0.7109   0.02766   0.01630  -0.0080   1.0000   0.1813
  -6.500  -0.6925   0.02667   0.01535  -0.0066   1.0000   0.2017
  -6.250  -0.6748   0.02574   0.01453  -0.0051   1.0000   0.2241
  -6.000  -0.6567   0.02488   0.01376  -0.0036   1.0000   0.2509
  -5.750  -0.6386   0.02410   0.01309  -0.0021   1.0000   0.2810
  -5.500  -0.6206   0.02339   0.01250  -0.0005   1.0000   0.3132
  -5.250  -0.6025   0.02275   0.01198   0.0011   1.0000   0.3470
  -5.000  -0.5842   0.02218   0.01154   0.0028   1.0000   0.3820
  -4.750  -0.5655   0.02168   0.01116   0.0046   1.0000   0.4176
  -4.500  -0.5464   0.02123   0.01083   0.0063   1.0000   0.4537
  -4.250  -0.5270   0.02083   0.01051   0.0080   1.0000   0.4896
  -4.000  -0.5073   0.02048   0.01026   0.0098   1.0000   0.5251
  -3.750  -0.4879   0.02018   0.01007   0.0117   1.0000   0.5595
  -3.500  -0.4681   0.01993   0.00990   0.0136   1.0000   0.5934
  -3.250  -0.4481   0.01972   0.00979   0.0155   1.0000   0.6270
  -3.000  -0.4277   0.01956   0.00971   0.0174   1.0000   0.6601
  -2.750  -0.4071   0.01945   0.00966   0.0193   1.0000   0.6928
  -2.500  -0.3861   0.01938   0.00966   0.0211   1.0000   0.7253
  -2.250  -0.3639   0.01937   0.00970   0.0228   1.0000   0.7567
  -2.000  -0.3402   0.01942   0.00979   0.0242   1.0000   0.7876
  -1.750  -0.3144   0.01952   0.00990   0.0251   1.0000   0.8179
  -1.500  -0.2858   0.01966   0.01005   0.0253   1.0000   0.8478
  -1.250  -0.2542   0.01984   0.01020   0.0248   1.0000   0.8771
  -1.000  -0.2167   0.02005   0.01036   0.0229   1.0000   0.9040
  -0.750  -0.1745   0.02026   0.01053   0.0199   1.0000   0.9288
  -0.500  -0.1277   0.02045   0.01068   0.0156   1.0000   0.9515
  -0.250  -0.0696   0.02062   0.01081   0.0089   0.9951   0.9702
   0.000   0.0000   0.02068   0.01086   0.0000   0.9836   0.9836
   0.250   0.0696   0.02061   0.01081  -0.0089   0.9702   0.9951
   0.500   0.1277   0.02045   0.01068  -0.0156   0.9515   1.0000
   0.750   0.1745   0.02026   0.01053  -0.0199   0.9288   1.0000
   1.000   0.2166   0.02005   0.01036  -0.0229   0.9041   1.0000
   1.250   0.2542   0.01983   0.01019  -0.0248   0.8771   1.0000
   1.500   0.2858   0.01966   0.01004  -0.0253   0.8478   1.0000
   1.750   0.3144   0.01952   0.00990  -0.0251   0.8179   1.0000
   2.000   0.3402   0.01942   0.00979  -0.0242   0.7876   1.0000
   2.250   0.3639   0.01937   0.00970  -0.0228   0.7568   1.0000
   2.500   0.3860   0.01938   0.00965  -0.0211   0.7253   1.0000
   2.750   0.4070   0.01944   0.00966  -0.0193   0.6929   1.0000
   3.000   0.4277   0.01956   0.00971  -0.0174   0.6601   1.0000
   3.250   0.4480   0.01972   0.00979  -0.0155   0.6270   1.0000
   3.500   0.4680   0.01993   0.00990  -0.0136   0.5934   1.0000
   3.750   0.4878   0.02018   0.01007  -0.0117   0.5595   1.0000
   4.250   0.5269   0.02083   0.01051  -0.0080   0.4896   1.0000
   4.500   0.5464   0.02123   0.01082  -0.0063   0.4537   1.0000
   4.750   0.5654   0.02167   0.01116  -0.0046   0.4177   1.0000
   5.000   0.5841   0.02218   0.01154  -0.0028   0.3820   1.0000
   5.250   0.6025   0.02275   0.01198  -0.0011   0.3471   1.0000
   5.500   0.6206   0.02338   0.01250   0.0005   0.3132   1.0000
   5.750   0.6386   0.02409   0.01308   0.0021   0.2810   1.0000
   6.000   0.6566   0.02487   0.01376   0.0036   0.2509   1.0000
   6.250   0.6748   0.02573   0.01453   0.0051   0.2241   1.0000
   6.500   0.6925   0.02667   0.01535   0.0066   0.2017   1.0000
   6.750   0.7109   0.02766   0.01630   0.0080   0.1813   1.0000
   7.000   0.7294   0.02871   0.01733   0.0093   0.1644   1.0000
   7.250   0.7479   0.02982   0.01843   0.0106   0.1500   1.0000
   7.500   0.7664   0.03098   0.01955   0.0119   0.1384   1.0000
   7.750   0.7851   0.03218   0.02078   0.0131   0.1277   1.0000
   8.000   0.8044   0.03353   0.02227   0.0143   0.1185   1.0000
   8.250   0.8228   0.03486   0.02354   0.0154   0.1113   1.0000
   8.500   0.8414   0.03641   0.02536   0.0166   0.1041   1.0000
   8.750   0.8597   0.03785   0.02668   0.0175   0.0987   1.0000
   9.000   0.8760   0.03979   0.02903   0.0189   0.0932   1.0000
   9.250   0.8922   0.04144   0.03079   0.0200   0.0887   1.0000
   9.500   0.9071   0.04340   0.03287   0.0212   0.0849   1.0000
   9.750   0.9171   0.04592   0.03580   0.0227   0.0815   1.0000
  10.000   0.9270   0.04819   0.03830   0.0241   0.0785   1.0000
  10.250   0.9397   0.05004   0.04016   0.0252   0.0757   1.0000
  10.500   0.9411   0.05302   0.04346   0.0269   0.0736   1.0000
  10.750   0.9335   0.05656   0.04745   0.0288   0.0721   1.0000
  11.000   0.9206   0.06023   0.05144   0.0307   0.0711   1.0000
  11.250   0.9012   0.06425   0.05572   0.0321   0.0706   1.0000
  11.500   0.8756   0.06936   0.06106   0.0316   0.0704   1.0000
  11.750   0.8414   0.07654   0.06847   0.0283   0.0708   1.0000
  12.000   0.7971   0.08731   0.07940   0.0209   0.0718   1.0000
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