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NACA 67 (naca671215-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 67 (naca671215-il)
Reynolds number: 50,000
Max Cl/Cd: 21.4 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca671215-il-50000-n5.txt
Download as CSV file: xf-naca671215-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 67                                         
  
 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  -0.5688   0.11400   0.10679  -0.0495   1.0000   0.0602
 -11.750  -0.5881   0.10744   0.10026  -0.0517   1.0000   0.0597
 -11.500  -0.6193   0.09954   0.09238  -0.0546   1.0000   0.0583
 -11.250  -0.6629   0.09230   0.08510  -0.0558   1.0000   0.0570
 -11.000  -0.7156   0.08626   0.07891  -0.0541   1.0000   0.0557
 -10.500  -0.8095   0.07980   0.07200  -0.0429   1.0000   0.0544
 -10.250  -0.8346   0.07773   0.06982  -0.0373   1.0000   0.0544
 -10.000  -0.8564   0.07529   0.06722  -0.0321   1.0000   0.0543
  -9.750  -0.8759   0.07258   0.06430  -0.0270   1.0000   0.0543
  -9.500  -0.8917   0.06984   0.06130  -0.0221   1.0000   0.0544
  -9.250  -0.9005   0.06711   0.05842  -0.0180   1.0000   0.0549
  -9.000  -0.9027   0.06473   0.05592  -0.0147   1.0000   0.0556
  -8.750  -0.9030   0.06262   0.05368  -0.0115   1.0000   0.0566
  -8.500  -0.9040   0.06041   0.05126  -0.0080   1.0000   0.0578
  -8.250  -0.9046   0.05798   0.04855  -0.0045   1.0000   0.0588
  -8.000  -0.9030   0.05554   0.04577  -0.0010   1.0000   0.0599
  -7.750  -0.8988   0.05302   0.04287   0.0022   1.0000   0.0609
  -7.500  -0.8911   0.05056   0.03998   0.0052   1.0000   0.0618
  -7.250  -0.8786   0.04824   0.03713   0.0074   0.9991   0.0638
  -7.000  -0.8608   0.04614   0.03471   0.0085   0.9977   0.0662
  -6.750  -0.8396   0.04452   0.03296   0.0090   0.9962   0.0688
  -6.500  -0.8161   0.04296   0.03114   0.0094   0.9947   0.0718
  -6.250  -0.7915   0.04152   0.02932   0.0098   0.9934   0.0757
  -6.000  -0.7650   0.04011   0.02783   0.0098   0.9923   0.0796
  -5.750  -0.7368   0.03901   0.02665   0.0095   0.9911   0.0842
  -5.500  -0.7048   0.03813   0.02550   0.0089   0.9898   0.0905
  -5.250  -0.6694   0.03727   0.02471   0.0074   0.9886   0.0969
  -5.000  -0.6373   0.03665   0.02395   0.0066   0.9873   0.1062
  -4.750  -0.6109   0.03600   0.02328   0.0066   0.9859   0.1157
  -4.500  -0.5884   0.03534   0.02264   0.0072   0.9844   0.1278
  -4.250  -0.5710   0.03456   0.02193   0.0086   0.9823   0.1459
  -4.000  -0.5561   0.03362   0.02124   0.0104   0.9800   0.1774
  -3.750  -0.4743   0.03458   0.02553   0.0064   0.9827   0.7098
  -3.500  -0.4890   0.03432   0.02512   0.0138   0.9788   0.7601
  -3.250  -0.4874   0.03494   0.02554   0.0192   0.9756   0.8050
  -3.000  -0.3388   0.04092   0.03091   0.0040   0.9805   0.9113
  -2.750  -0.2700   0.04144   0.03108  -0.0039   0.9807   0.9346
  -2.250  -0.1970   0.04133   0.03052  -0.0094   0.9772   0.9539
  -2.000  -0.1621   0.04127   0.03028  -0.0121   0.9753   0.9610
  -1.750  -0.1290   0.04118   0.03003  -0.0144   0.9733   0.9670
  -1.500  -0.1003   0.04108   0.02980  -0.0159   0.9706   0.9729
  -1.250  -0.0688   0.04099   0.02960  -0.0179   0.9679   0.9776
  -1.000  -0.0376   0.04100   0.02950  -0.0199   0.9653   0.9822
  -0.750  -0.0049   0.04109   0.02951  -0.0223   0.9629   0.9861
  -0.500   0.0221   0.04101   0.02937  -0.0234   0.9593   0.9897
  -0.250   0.0502   0.04108   0.02939  -0.0248   0.9558   0.9934
   0.000   0.0814   0.04119   0.02947  -0.0269   0.9524   0.9963
   0.250   0.1135   0.04139   0.02964  -0.0290   0.9493   0.9993
   0.500   0.1308   0.04143   0.02968  -0.0282   0.9439   1.0000
   0.750   0.1528   0.04161   0.02987  -0.0283   0.9391   1.0000
   1.000   0.1749   0.04183   0.03009  -0.0283   0.9342   1.0000
   1.250   0.1912   0.04194   0.03024  -0.0272   0.9278   1.0000
   1.500   0.2170   0.04223   0.03056  -0.0279   0.9227   1.0000
   1.750   0.2325   0.04238   0.03075  -0.0266   0.9156   1.0000
   2.000   0.2551   0.04262   0.03105  -0.0267   0.9092   1.0000
   2.250   0.2765   0.04287   0.03136  -0.0264   0.9025   1.0000
   2.500   0.2954   0.04306   0.03163  -0.0257   0.8946   1.0000
   2.750   0.3207   0.04333   0.03199  -0.0262   0.8877   1.0000
   3.000   0.3388   0.04349   0.03225  -0.0252   0.8784   1.0000
   3.250   0.3612   0.04369   0.03256  -0.0250   0.8700   1.0000
   3.500   0.3856   0.04386   0.03286  -0.0251   0.8611   1.0000
   3.750   0.4030   0.04397   0.03311  -0.0238   0.8504   1.0000
   4.000   0.4372   0.04407   0.03337  -0.0254   0.8423   1.0000
   4.250   0.4565   0.04401   0.03346  -0.0243   0.8296   1.0000
   4.500   0.4774   0.04386   0.03349  -0.0233   0.8161   1.0000
   4.750   0.5010   0.04358   0.03339  -0.0226   0.8020   1.0000
   5.000   0.5268   0.04306   0.03307  -0.0220   0.7865   1.0000
   5.250   0.5568   0.04210   0.03235  -0.0215   0.7683   1.0000
   5.500   0.5751   0.04105   0.03149  -0.0188   0.7451   1.0000
   5.750   0.5948   0.03963   0.03027  -0.0160   0.7173   1.0000
   6.000   0.6079   0.03821   0.02903  -0.0118   0.6818   1.0000
   6.250   0.6178   0.03700   0.02798  -0.0072   0.6390   1.0000
   6.500   0.6399   0.03531   0.02637  -0.0038   0.5750   1.0000
   6.750   0.7032   0.03286   0.02235  -0.0042   0.3237   1.0000
   7.000   0.6962   0.03425   0.02312   0.0009   0.2444   1.0000
   7.250   0.6933   0.03556   0.02400   0.0051   0.1932   1.0000
   7.500   0.6947   0.03674   0.02488   0.0088   0.1609   1.0000
   7.750   0.7000   0.03775   0.02576   0.0119   0.1394   1.0000
   8.000   0.7078   0.03868   0.02662   0.0147   0.1256   1.0000
   8.250   0.7182   0.03959   0.02744   0.0172   0.1154   1.0000
   8.500   0.7337   0.04034   0.02829   0.0191   0.1054   1.0000
   8.750   0.7574   0.04114   0.02915   0.0199   0.0971   1.0000
   9.000   0.7868   0.04198   0.03001   0.0199   0.0894   1.0000
   9.250   0.8255   0.04311   0.03134   0.0186   0.0821   1.0000
   9.500   0.8581   0.04445   0.03271   0.0178   0.0765   1.0000
   9.750   0.8893   0.04619   0.03469   0.0172   0.0716   1.0000
  10.000   0.9096   0.04787   0.03662   0.0182   0.0678   1.0000
  10.250   0.9235   0.04937   0.03817   0.0198   0.0647   1.0000
  10.500   0.9354   0.05131   0.04032   0.0217   0.0625   1.0000
  10.750   0.9341   0.05309   0.04247   0.0258   0.0608   1.0000
  11.000   0.9306   0.05488   0.04456   0.0300   0.0595   1.0000
  11.250   0.9233   0.05651   0.04642   0.0346   0.0584   1.0000
  11.500   0.9144   0.05821   0.04833   0.0391   0.0572   1.0000
  11.750   0.9055   0.05987   0.05014   0.0433   0.0563   1.0000
  12.250   0.8906   0.06365   0.05420   0.0504   0.0544   1.0000
  12.500   0.8869   0.06605   0.05668   0.0528   0.0535   1.0000
  12.750   0.8721   0.06888   0.05971   0.0559   0.0532   1.0000
  13.000   0.8536   0.07206   0.06313   0.0586   0.0531   1.0000
  13.250   0.8311   0.07572   0.06705   0.0609   0.0530   1.0000
  13.500   0.8093   0.07972   0.07126   0.0622   0.0530   1.0000
  13.750   0.7860   0.08424   0.07597   0.0626   0.0531   1.0000
  14.000   0.7627   0.08927   0.08115   0.0621   0.0532   1.0000
  14.250   0.6804   0.10331   0.09558   0.0549   0.0555   1.0000
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