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NACA 4421 (naca4421-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: NACA 4421 (naca4421-il)
Reynolds number: 50,000
Max Cl/Cd: 3.59 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca4421-il-50000.txt
Download as CSV file: xf-naca4421-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 4421                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3533   0.13538   0.12826  -0.0092   1.0000   0.3723
  -9.000  -0.3150   0.13107   0.12394  -0.0082   1.0000   0.3802
  -8.750  -0.3384   0.13116   0.12411  -0.0055   1.0000   0.3915
  -8.500  -0.3558   0.12939   0.12243  -0.0034   1.0000   0.3966
  -8.250  -0.3329   0.12684   0.11989  -0.0021   1.0000   0.4061
  -8.000  -0.3885   0.12846   0.12164   0.0021   1.0000   0.4168
  -7.750  -0.3587   0.12414   0.11733   0.0024   1.0000   0.4230
  -7.500  -0.5935   0.10199   0.09522  -0.0073   1.0000   0.2861
  -7.250  -0.6061   0.09793   0.09116  -0.0064   1.0000   0.2829
  -7.000  -0.6295   0.09287   0.08609  -0.0059   1.0000   0.2805
  -6.750  -0.6669   0.08544   0.07858  -0.0067   1.0000   0.2774
  -6.500  -0.6998   0.07738   0.07031  -0.0082   1.0000   0.2765
  -6.250  -0.7173   0.07078   0.06341  -0.0095   1.0000   0.2788
  -6.000  -0.7155   0.06256   0.05429  -0.0159   0.9942   0.2853
  -5.750  -0.6534   0.06437   0.05644  -0.0203   0.9780   0.2956
  -5.500  -0.6351   0.06042   0.05196  -0.0241   0.9685   0.3038
  -5.250  -0.6032   0.05939   0.05089  -0.0264   0.9571   0.3114
  -5.000  -0.5684   0.05834   0.04965  -0.0296   0.9465   0.3209
  -4.750  -0.5459   0.05611   0.04700  -0.0318   0.9372   0.3291
  -4.500  -0.5152   0.05605   0.04705  -0.0329   0.9270   0.3372
  -4.250  -0.4844   0.05465   0.04520  -0.0359   0.9176   0.3482
  -4.000  -0.4600   0.05431   0.04495  -0.0362   0.9080   0.3560
  -3.750  -0.4289   0.05380   0.04424  -0.0383   0.8993   0.3680
  -3.500  -0.4047   0.05345   0.04386  -0.0388   0.8904   0.3778
  -3.250  -0.3772   0.05318   0.04345  -0.0400   0.8816   0.3910
  -3.000  -0.3481   0.05317   0.04347  -0.0410   0.8730   0.4037
  -2.750  -0.3293   0.05297   0.04306  -0.0411   0.8655   0.4180
  -2.500  -0.2857   0.05328   0.04345  -0.0440   0.8574   0.4372
  -2.250  -0.2800   0.05329   0.04351  -0.0417   0.8497   0.4484
  -2.000  -0.2541   0.05348   0.04365  -0.0424   0.8422   0.4677
  -1.750  -0.2194   0.05395   0.04412  -0.0441   0.8350   0.4903
  -1.500  -0.2141   0.05433   0.04466  -0.0416   0.8290   0.5040
  -1.250  -0.1903   0.05477   0.04517  -0.0417   0.8219   0.5256
  -1.000  -0.1561   0.05541   0.04587  -0.0430   0.8144   0.5527
  -0.750  -0.1520   0.05601   0.04656  -0.0407   0.8102   0.5710
  -0.500  -0.1388   0.05668   0.04733  -0.0395   0.8053   0.5949
  -0.250  -0.1046   0.05740   0.04815  -0.0405   0.7978   0.6315
   0.000  -0.0908   0.05821   0.04911  -0.0389   0.7926   0.6630
   0.250  -0.0868   0.05904   0.05012  -0.0362   0.7902   0.6950
   0.500  -0.0808   0.05981   0.05110  -0.0336   0.7877   0.7367
   0.750  -0.0769   0.06060   0.05217  -0.0300   0.7867   0.7874
   1.000  -0.0740   0.06157   0.05344  -0.0259   0.7884   0.8565
   1.250  -0.0395   0.06439   0.05648  -0.0306   0.8006   0.9567
   1.500   0.0285   0.06485   0.05648  -0.0406   0.7695   1.0000
   1.750   0.0437   0.06665   0.05801  -0.0421   0.7726   1.0000
   2.000  -0.0223   0.07040   0.06186  -0.0366   0.8562   1.0000
   2.250  -0.0206   0.07028   0.06161  -0.0348   0.8454   1.0000
   2.500   0.0290   0.07431   0.06538  -0.0402   0.8367   1.0000
   2.750   0.0193   0.07363   0.06463  -0.0367   0.8273   1.0000
   3.000   0.0590   0.07671   0.06752  -0.0403   0.8176   1.0000
   3.250   0.0590   0.07728   0.06803  -0.0383   0.8092   1.0000
   3.500   0.0916   0.07977   0.07038  -0.0407   0.7981   1.0000
   3.750   0.1019   0.08152   0.07204  -0.0403   0.7919   1.0000
   4.000   0.1226   0.08308   0.07352  -0.0410   0.7787   1.0000
   4.250   0.1465   0.08604   0.07638  -0.0425   0.7729   1.0000
   4.500   0.1527   0.08665   0.07695  -0.0412   0.7595   1.0000
   4.750   0.1942   0.09101   0.08119  -0.0449   0.7532   1.0000
   5.000   0.1837   0.09049   0.08066  -0.0416   0.7401   1.0000
   5.250   0.2285   0.09493   0.08501  -0.0455   0.7331   1.0000
   5.500   0.2130   0.09453   0.08461  -0.0419   0.7219   1.0000
   5.750   0.2514   0.09815   0.08816  -0.0448   0.7131   1.0000
   6.000   0.2440   0.09885   0.08884  -0.0425   0.7037   1.0000
   6.250   0.2717   0.10157   0.09153  -0.0441   0.6939   1.0000
   6.500   0.2813   0.10393   0.09385  -0.0439   0.6873   1.0000
   6.750   0.2949   0.10548   0.09539  -0.0438   0.6746   1.0000
   7.000   0.3348   0.11044   0.10030  -0.0469   0.6694   1.0000
   7.250   0.3173   0.10964   0.09951  -0.0437   0.6563   1.0000
   7.500   0.3606   0.11442   0.10426  -0.0468   0.6494   1.0000
   7.750   0.3419   0.11414   0.10398  -0.0439   0.6384   1.0000
   8.000   0.3754   0.11777   0.10760  -0.0459   0.6298   1.0000
   8.250   0.3692   0.11896   0.10880  -0.0444   0.6208   1.0000
   8.500   0.3933   0.12172   0.11156  -0.0454   0.6104   1.0000
   8.750   0.4046   0.12470   0.11454  -0.0458   0.6042   1.0000
   9.000   0.4134   0.12609   0.11593  -0.0454   0.5909   1.0000
   9.250   0.4464   0.13109   0.12092  -0.0475   0.5853   1.0000
   9.500   0.4344   0.13070   0.12055  -0.0456   0.5715   1.0000
   9.750   0.4806   0.13688   0.12674  -0.0486   0.5650   1.0000
  10.000   0.4561   0.13550   0.12538  -0.0461   0.5519   1.0000
  10.250   0.5069   0.14206   0.13196  -0.0490   0.5444   1.0000
  10.500   0.4780   0.14045   0.13037  -0.0467   0.5321   1.0000
  10.750   0.5262   0.14670   0.13664  -0.0491   0.5239   1.0000
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