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NACA 63-209 (naca63209-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 63-209 (naca63209-il)
Reynolds number: 50,000
Max Cl/Cd: 32.91 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca63209-il-50000-n5.txt
Download as CSV file: xf-naca63209-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 63-209                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5624   0.09658   0.08957  -0.0169   1.0000   0.0530
  -9.250  -0.5635   0.09164   0.08469  -0.0197   1.0000   0.0522
  -9.000  -0.5666   0.08624   0.07934  -0.0234   1.0000   0.0515
  -8.750  -0.5734   0.08043   0.07359  -0.0279   1.0000   0.0506
  -8.500  -0.5841   0.07533   0.06853  -0.0314   1.0000   0.0496
  -8.250  -0.5924   0.07036   0.06348  -0.0342   1.0000   0.0488
  -8.000  -0.5981   0.06551   0.05850  -0.0363   1.0000   0.0481
  -7.750  -0.6004   0.06076   0.05351  -0.0378   1.0000   0.0475
  -7.500  -0.5986   0.05613   0.04856  -0.0386   1.0000   0.0468
  -7.250  -0.5923   0.05181   0.04386  -0.0389   1.0000   0.0464
  -7.000  -0.5822   0.04782   0.03945  -0.0389   1.0000   0.0463
  -6.750  -0.5688   0.04421   0.03541  -0.0385   1.0000   0.0465
  -6.500  -0.5527   0.04102   0.03182  -0.0380   1.0000   0.0473
  -6.250  -0.5349   0.03842   0.02886  -0.0374   1.0000   0.0502
  -6.000  -0.5153   0.03585   0.02580  -0.0366   1.0000   0.0530
  -5.750  -0.4939   0.03335   0.02276  -0.0357   1.0000   0.0545
  -5.500  -0.4713   0.03117   0.02016  -0.0345   1.0000   0.0558
  -5.250  -0.4493   0.02905   0.01792  -0.0334   1.0000   0.0577
  -5.000  -0.4282   0.02754   0.01636  -0.0323   1.0000   0.0623
  -4.750  -0.4064   0.02630   0.01488  -0.0309   1.0000   0.0685
  -4.500  -0.3864   0.02491   0.01350  -0.0293   1.0000   0.0730
  -4.250  -0.3668   0.02378   0.01223  -0.0278   1.0000   0.0791
  -4.000  -0.3479   0.02273   0.01115  -0.0265   1.0000   0.0909
  -3.750  -0.3286   0.02162   0.01003  -0.0254   1.0000   0.1065
  -3.500  -0.3094   0.02028   0.00888  -0.0246   1.0000   0.1403
  -3.250  -0.2974   0.01764   0.00821  -0.0233   1.0000   0.4481
  -3.000  -0.2864   0.01734   0.00843  -0.0190   1.0000   0.6147
  -2.750  -0.2819   0.01751   0.00889  -0.0126   1.0000   0.7258
  -2.500  -0.2829   0.01780   0.00938  -0.0044   1.0000   0.8051
  -2.250  -0.2756   0.01789   0.00944   0.0013   1.0000   0.8576
  -2.000  -0.2545   0.01777   0.00913   0.0028   1.0000   0.8870
  -1.750  -0.2267   0.01764   0.00877   0.0024   1.0000   0.9124
  -1.500  -0.1902   0.01754   0.00840   0.0001   0.9993   0.9368
  -1.250  -0.1360   0.01756   0.00814  -0.0059   0.9924   0.9559
  -1.000  -0.0795   0.01759   0.00794  -0.0125   0.9857   0.9746
  -0.750  -0.0238   0.01758   0.00772  -0.0191   0.9779   0.9936
  -0.500   0.0158   0.01764   0.00764  -0.0228   0.9666   1.0000
  -0.250   0.0511   0.01773   0.00762  -0.0256   0.9544   1.0000
   0.000   0.0864   0.01785   0.00763  -0.0282   0.9427   1.0000
   0.250   0.1235   0.01799   0.00769  -0.0310   0.9320   1.0000
   0.500   0.1640   0.01814   0.00781  -0.0342   0.9226   1.0000
   0.750   0.1966   0.01831   0.00795  -0.0358   0.9107   1.0000
   1.000   0.2290   0.01849   0.00813  -0.0373   0.8989   1.0000
   1.250   0.2617   0.01869   0.00834  -0.0387   0.8876   1.0000
   1.500   0.2948   0.01889   0.00860  -0.0401   0.8768   1.0000
   1.750   0.3283   0.01908   0.00885  -0.0414   0.8661   1.0000
   2.000   0.3567   0.01932   0.00917  -0.0418   0.8535   1.0000
   2.250   0.3851   0.01958   0.00954  -0.0421   0.8410   1.0000
   2.500   0.4136   0.01983   0.00991  -0.0424   0.8286   1.0000
   2.750   0.4425   0.02008   0.01030  -0.0426   0.8160   1.0000
   3.000   0.4712   0.02032   0.01070  -0.0427   0.8030   1.0000
   3.250   0.4995   0.02054   0.01115  -0.0425   0.7890   1.0000
   3.500   0.5270   0.02072   0.01154  -0.0421   0.7734   1.0000
   3.750   0.5546   0.02081   0.01185  -0.0413   0.7557   1.0000
   4.000   0.5809   0.02068   0.01193  -0.0397   0.7313   1.0000
   4.250   0.6036   0.01996   0.01136  -0.0358   0.6847   1.0000
   4.500   0.6199   0.01919   0.01036  -0.0305   0.5937   1.0000
   4.750   0.6362   0.01933   0.01011  -0.0268   0.4673   1.0000
   5.000   0.6438   0.02130   0.01059  -0.0235   0.2236   1.0000
   5.250   0.6553   0.02390   0.01229  -0.0222   0.1221   1.0000
   5.500   0.6728   0.02564   0.01385  -0.0211   0.0949   1.0000
   5.750   0.6920   0.02720   0.01551  -0.0200   0.0832   1.0000
   6.000   0.7123   0.02873   0.01703  -0.0190   0.0725   1.0000
   6.250   0.7360   0.03019   0.01869  -0.0181   0.0651   1.0000
   6.500   0.7616   0.03215   0.02058  -0.0175   0.0609   1.0000
   6.750   0.7895   0.03394   0.02273  -0.0169   0.0561   1.0000
   7.000   0.8145   0.03587   0.02490  -0.0165   0.0514   1.0000
   7.250   0.8396   0.03851   0.02766  -0.0162   0.0492   1.0000
   7.500   0.8630   0.04156   0.03107  -0.0156   0.0480   1.0000
   7.750   0.8829   0.04474   0.03479  -0.0147   0.0472   1.0000
   8.000   0.8989   0.04823   0.03882  -0.0136   0.0466   1.0000
   8.250   0.9103   0.05184   0.04298  -0.0125   0.0455   1.0000
   8.500   0.9171   0.05556   0.04721  -0.0113   0.0441   1.0000
   8.750   0.9202   0.05937   0.05146  -0.0103   0.0428   1.0000
   9.000   0.9191   0.06338   0.05584  -0.0094   0.0420   1.0000
   9.250   0.9132   0.06762   0.06040  -0.0087   0.0418   1.0000
   9.500   0.9020   0.07199   0.06503  -0.0083   0.0420   1.0000
   9.750   0.8853   0.07625   0.06946  -0.0081   0.0423   1.0000
  10.000   0.8661   0.08119   0.07453  -0.0096   0.0427   1.0000
  10.250   0.8463   0.08708   0.08051  -0.0129   0.0432   1.0000
  10.500   0.8283   0.09395   0.08743  -0.0176   0.0437   1.0000
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