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NLR-7223-43 AIRFOIL (nl722343-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NLR-7223-43 AIRFOIL (nl722343-il)
Reynolds number: 50,000
Max Cl/Cd: 30.38 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nl722343-il-50000.txt
Download as CSV file: xf-nl722343-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NLR-7223-43 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4739   0.10424   0.09715  -0.0068   1.0000   0.2891
  -8.500  -0.4727   0.10158   0.09455  -0.0059   1.0000   0.3086
  -8.250  -0.4822   0.09976   0.09285  -0.0052   1.0000   0.3270
  -8.000  -0.4588   0.09536   0.08842  -0.0030   1.0000   0.3499
  -7.750  -0.4680   0.09387   0.08704  -0.0014   1.0000   0.3732
  -7.500  -0.4499   0.09022   0.08341   0.0010   1.0000   0.4023
  -7.250  -0.4372   0.08718   0.08041   0.0033   1.0000   0.4322
  -7.000  -0.4364   0.08528   0.07859   0.0064   1.0000   0.4657
  -5.250  -0.4880   0.03627   0.02980  -0.0233   1.0000   0.2179
  -5.000  -0.4668   0.03032   0.02281  -0.0266   1.0000   0.1564
  -4.750  -0.4602   0.04102   0.03168  -0.0279   1.0000   0.1281
  -4.500  -0.4395   0.03748   0.02805  -0.0270   1.0000   0.1219
  -4.250  -0.4141   0.03537   0.02502  -0.0257   1.0000   0.1136
  -4.000  -0.3907   0.03314   0.02242  -0.0246   1.0000   0.1134
  -3.750  -0.3667   0.03078   0.01982  -0.0235   1.0000   0.1140
  -3.500  -0.3417   0.02883   0.01759  -0.0223   1.0000   0.1142
  -3.250  -0.3165   0.02693   0.01559  -0.0211   1.0000   0.1160
  -3.000  -0.2921   0.02548   0.01415  -0.0195   1.0000   0.1226
  -2.750  -0.2684   0.02423   0.01286  -0.0176   1.0000   0.1318
  -2.500  -0.0800   0.02015   0.01141  -0.0287   1.0000   1.0000
  -2.250  -0.0717   0.01992   0.01095  -0.0261   1.0000   1.0000
  -2.000  -0.0642   0.01972   0.01058  -0.0233   1.0000   1.0000
  -1.750  -0.0574   0.01953   0.01024  -0.0205   1.0000   1.0000
  -1.500  -0.0512   0.01935   0.00995  -0.0175   1.0000   1.0000
  -1.250  -0.0458   0.01918   0.00967  -0.0144   1.0000   1.0000
  -1.000  -0.0409   0.01901   0.00941  -0.0113   1.0000   1.0000
  -0.750  -0.0367   0.01883   0.00914  -0.0081   1.0000   1.0000
  -0.500  -0.0326   0.01865   0.00889  -0.0048   1.0000   1.0000
  -0.250  -0.0278   0.01847   0.00866  -0.0018   1.0000   1.0000
   0.000  -0.0198   0.01835   0.00846   0.0007   1.0000   1.0000
   0.250  -0.0067   0.01831   0.00834   0.0023   1.0000   1.0000
   0.500   0.0103   0.01836   0.00829   0.0032   1.0000   1.0000
   0.750   0.0295   0.01848   0.00833   0.0037   1.0000   1.0000
   1.000   0.0501   0.01865   0.00844   0.0040   1.0000   1.0000
   1.250   0.0714   0.01888   0.00863   0.0041   1.0000   1.0000
   1.500   0.0929   0.01916   0.00889   0.0041   1.0000   1.0000
   1.750   0.1145   0.01950   0.00922   0.0041   1.0000   1.0000
   2.000   0.1358   0.01990   0.00962   0.0040   1.0000   1.0000
   2.250   0.1566   0.02036   0.01012   0.0039   1.0000   1.0000
   2.500   0.1768   0.02091   0.01072   0.0037   1.0000   1.0000
   2.750   0.1959   0.02155   0.01144   0.0035   1.0000   1.0000
   3.000   0.2720   0.02294   0.01309  -0.0071   0.9694   1.0000
   3.250   0.3748   0.02327   0.01386  -0.0202   0.9182   1.0000
   3.500   0.4731   0.02168   0.01288  -0.0290   0.8508   1.0000
   3.750   0.5608   0.01846   0.00968  -0.0304   0.6564   1.0000
   4.000   0.5959   0.01986   0.00979  -0.0292   0.5112   1.0000
   4.250   0.6252   0.02123   0.01073  -0.0292   0.4578   1.0000
   4.500   0.6552   0.02243   0.01179  -0.0295   0.4243   1.0000
   4.750   0.6845   0.02360   0.01287  -0.0298   0.3993   1.0000
   5.000   0.7126   0.02481   0.01411  -0.0298   0.3789   1.0000
   5.250   0.7389   0.02604   0.01543  -0.0297   0.3603   1.0000
   5.500   0.7646   0.02736   0.01684  -0.0294   0.3432   1.0000
   5.750   0.7894   0.02877   0.01836  -0.0290   0.3268   1.0000
   6.000   0.8135   0.03030   0.02007  -0.0284   0.3106   1.0000
   6.250   0.8365   0.03194   0.02187  -0.0277   0.2941   1.0000
   6.500   0.8589   0.03367   0.02371  -0.0269   0.2767   1.0000
   6.750   0.8809   0.03560   0.02572  -0.0260   0.2588   1.0000
   7.000   0.8974   0.03775   0.02824  -0.0245   0.2403   1.0000
   7.250   0.9132   0.03983   0.03058  -0.0228   0.2193   1.0000
   7.500   0.9324   0.04168   0.03235  -0.0215   0.1967   1.0000
   7.750   0.9423   0.04436   0.03546  -0.0193   0.1778   1.0000
   8.000   0.9529   0.04727   0.03868  -0.0173   0.1617   1.0000
   8.250   0.9634   0.05042   0.04205  -0.0156   0.1494   1.0000
   8.500   0.9783   0.05307   0.04472  -0.0143   0.1376   1.0000
   8.750   0.9690   0.05826   0.05059  -0.0119   0.1349   1.0000
   9.000   0.9583   0.06367   0.05643  -0.0102   0.1337   1.0000
   9.250   0.9439   0.06921   0.06227  -0.0091   0.1339   1.0000
   9.500   0.9263   0.07487   0.06812  -0.0086   0.1350   1.0000
   9.750   0.9075   0.08040   0.07373  -0.0084   0.1362   1.0000
  10.000   0.8919   0.08601   0.07937  -0.0089   0.1374   1.0000
  10.250   0.8827   0.09186   0.08523  -0.0100   0.1383   1.0000
  10.500   0.7575   0.12562   0.11860  -0.0461   0.3042   1.0000
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