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NACA 2421 (naca2421-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 2421 (naca2421-il)
Reynolds number: 50,000
Max Cl/Cd: 23.77 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca2421-il-50000-n5.txt
Download as CSV file: xf-naca2421-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 2421                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.4975   0.10376   0.09434  -0.0569   1.0000   0.1532
 -12.750  -0.4781   0.10424   0.09486  -0.0552   1.0000   0.1549
 -12.250  -0.7670   0.06191   0.05195  -0.0696   1.0000   0.1661
 -12.000  -0.7053   0.06536   0.05569  -0.0679   1.0000   0.1697
 -11.750  -0.7429   0.06088   0.05113  -0.0661   1.0000   0.1719
 -11.500  -0.7851   0.05706   0.04718  -0.0624   1.0000   0.1738
 -11.250  -0.8251   0.05425   0.04424  -0.0571   1.0000   0.1756
 -11.000  -0.8642   0.05216   0.04201  -0.0504   1.0000   0.1773
 -10.750  -0.8985   0.05016   0.03981  -0.0436   1.0000   0.1793
 -10.500  -0.8948   0.04951   0.03926  -0.0405   1.0000   0.1823
 -10.250  -0.8961   0.04873   0.03852  -0.0370   1.0000   0.1854
 -10.000  -0.9037   0.04755   0.03727  -0.0328   1.0000   0.1889
  -9.750  -0.9152   0.04603   0.03554  -0.0284   1.0000   0.1928
  -9.500  -0.9133   0.04517   0.03467  -0.0252   1.0000   0.1965
  -9.250  -0.9082   0.04458   0.03414  -0.0223   1.0000   0.2004
  -9.000  -0.9035   0.04356   0.03300  -0.0199   0.9989   0.2056
  -8.750  -0.8742   0.04255   0.03189  -0.0217   0.9921   0.2126
  -8.500  -0.8453   0.04180   0.03111  -0.0231   0.9845   0.2198
  -8.250  -0.8155   0.04082   0.02998  -0.0248   0.9775   0.2279
  -8.000  -0.7872   0.04023   0.02941  -0.0258   0.9690   0.2355
  -7.750  -0.7576   0.03933   0.02835  -0.0274   0.9617   0.2445
  -7.500  -0.7296   0.03884   0.02790  -0.0281   0.9528   0.2525
  -7.250  -0.6992   0.03806   0.02697  -0.0296   0.9456   0.2626
  -7.000  -0.6729   0.03761   0.02658  -0.0299   0.9361   0.2712
  -6.750  -0.6382   0.03693   0.02580  -0.0319   0.9298   0.2823
  -6.500  -0.6169   0.03650   0.02540  -0.0312   0.9190   0.2914
  -6.250  -0.5820   0.03591   0.02475  -0.0330   0.9124   0.3031
  -6.000  -0.5609   0.03550   0.02435  -0.0322   0.9018   0.3132
  -5.750  -0.5271   0.03500   0.02384  -0.0337   0.8946   0.3250
  -5.500  -0.5035   0.03458   0.02336  -0.0333   0.8847   0.3368
  -5.250  -0.4722   0.03419   0.02304  -0.0341   0.8765   0.3484
  -5.000  -0.4390   0.03371   0.02249  -0.0354   0.8697   0.3625
  -4.750  -0.4173   0.03347   0.02234  -0.0344   0.8585   0.3735
  -4.500  -0.3790   0.03301   0.02188  -0.0362   0.8526   0.3881
  -4.250  -0.3617   0.03281   0.02166  -0.0346   0.8409   0.4009
  -4.000  -0.3263   0.03245   0.02138  -0.0358   0.8339   0.4152
  -3.750  -0.3002   0.03218   0.02112  -0.0355   0.8247   0.4296
  -3.500  -0.2738   0.03192   0.02086  -0.0353   0.8153   0.4453
  -3.250  -0.2347   0.03152   0.02054  -0.0368   0.8100   0.4624
  -3.000  -0.2193   0.03152   0.02060  -0.0347   0.7972   0.4765
  -2.750  -0.1844   0.03117   0.02028  -0.0355   0.7907   0.4959
  -2.500  -0.1647   0.03111   0.02024  -0.0341   0.7797   0.5140
  -2.250  -0.1344   0.03088   0.02007  -0.0341   0.7715   0.5339
  -2.000  -0.0952   0.03047   0.01971  -0.0353   0.7666   0.5557
  -1.750  -0.0826   0.03068   0.02002  -0.0326   0.7529   0.5724
  -1.500  -0.0456   0.03032   0.01970  -0.0334   0.7470   0.5943
  -1.250  -0.0291   0.03048   0.01992  -0.0314   0.7351   0.6130
  -1.000   0.0030   0.03025   0.01972  -0.0314   0.7276   0.6348
  -0.750   0.0295   0.03020   0.01970  -0.0306   0.7190   0.6560
  -0.500   0.0512   0.03027   0.01982  -0.0291   0.7088   0.6769
  -0.250   0.0893   0.02997   0.01953  -0.0298   0.7030   0.6996
   0.000   0.1034   0.03039   0.02003  -0.0273   0.6908   0.7189
   0.250   0.1385   0.03029   0.01994  -0.0275   0.6838   0.7400
   0.500   0.1648   0.03049   0.02017  -0.0267   0.6747   0.7603
   0.750   0.1912   0.03070   0.02041  -0.0259   0.6651   0.7806
   1.000   0.2349   0.03052   0.02020  -0.0275   0.6595   0.8009
   1.250   0.2499   0.03114   0.02088  -0.0253   0.6476   0.8212
   1.500   0.2901   0.03112   0.02081  -0.0267   0.6405   0.8411
   1.750   0.3199   0.03146   0.02114  -0.0267   0.6315   0.8612
   2.000   0.3583   0.03179   0.02147  -0.0283   0.6221   0.8788
   2.250   0.4175   0.03161   0.02119  -0.0329   0.6160   0.8937
   2.500   0.4441   0.03238   0.02202  -0.0334   0.6041   0.9120
   2.750   0.4986   0.03226   0.02182  -0.0377   0.5967   0.9270
   3.000   0.5369   0.03276   0.02234  -0.0402   0.5859   0.9428
   3.250   0.5932   0.03264   0.02216  -0.0453   0.5767   0.9539
   3.500   0.6347   0.03290   0.02242  -0.0484   0.5656   0.9676
   3.750   0.6839   0.03273   0.02218  -0.0523   0.5551   0.9795
   4.000   0.7252   0.03301   0.02247  -0.0556   0.5433   0.9922
   4.250   0.7681   0.03284   0.02222  -0.0587   0.5335   1.0000
   4.500   0.7675   0.03328   0.02266  -0.0546   0.5246   1.0000
   4.750   0.7699   0.03362   0.02298  -0.0509   0.5158   1.0000
   5.000   0.7940   0.03340   0.02262  -0.0501   0.5091   1.0000
   5.250   0.7740   0.03446   0.02377  -0.0432   0.4992   1.0000
   5.500   0.7906   0.03450   0.02373  -0.0412   0.4916   1.0000
   5.750   0.7895   0.03512   0.02434  -0.0369   0.4834   1.0000
   6.000   0.7873   0.03579   0.02500  -0.0325   0.4747   1.0000
   6.250   0.8226   0.03543   0.02451  -0.0330   0.4680   1.0000
   6.500   0.7914   0.03704   0.02620  -0.0249   0.4582   1.0000
   6.750   0.8127   0.03711   0.02620  -0.0236   0.4506   1.0000
   7.000   0.8067   0.03804   0.02713  -0.0188   0.4424   1.0000
   7.250   0.8045   0.03896   0.02804  -0.0147   0.4336   1.0000
   7.500   0.8422   0.03856   0.02754  -0.0155   0.4267   1.0000
   7.750   0.8098   0.04092   0.03000  -0.0086   0.4164   1.0000
   8.000   0.8469   0.04040   0.02940  -0.0090   0.4095   1.0000
   8.250   0.8226   0.04295   0.03204  -0.0039   0.3993   1.0000
   8.500   0.8486   0.04292   0.03195  -0.0033   0.3918   1.0000
   8.750   0.8415   0.04490   0.03399  -0.0003   0.3826   1.0000
   9.000   0.8520   0.04586   0.03495   0.0013   0.3740   1.0000
   9.250   0.8734   0.04615   0.03520   0.0022   0.3668   1.0000
   9.500   0.8535   0.04942   0.03858   0.0051   0.3564   1.0000
   9.750   0.9023   0.04768   0.03671   0.0047   0.3509   1.0000
  10.000   0.8510   0.05382   0.04305   0.0080   0.3389   1.0000
  10.250   0.8915   0.05241   0.04155   0.0084   0.3335   1.0000
  10.500   0.8419   0.05943   0.04875   0.0102   0.3215   1.0000
  10.750   0.8747   0.05849   0.04776   0.0109   0.3161   1.0000
  11.000   0.8230   0.06680   0.05623   0.0112   0.3036   1.0000
  11.250   0.8502   0.06627   0.05568   0.0121   0.2984   1.0000
  11.500   0.9034   0.06293   0.05224   0.0132   0.2953   1.0000
  11.750   0.8229   0.07538   0.06491   0.0120   0.2807   1.0000
  12.000   0.8698   0.07221   0.06169   0.0135   0.2782   1.0000
  12.250   0.7978   0.08505   0.07468   0.0108   0.2635   1.0000
  12.500   0.8388   0.08224   0.07184   0.0125   0.2614   1.0000
  13.000   0.7398   0.10436   0.09415   0.0062   0.2356   1.0000
  13.250   0.7579   0.10483   0.09464   0.0068   0.2315   1.0000
  13.500   0.7881   0.10318   0.09299   0.0082   0.2293   1.0000
  14.000   0.7670   0.11395   0.10385   0.0052   0.2141   1.0000
  14.500   0.7491   0.12461   0.11457   0.0016   0.1998   1.0000
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