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NACA 67 (naca671215-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 67 (naca671215-il)
Reynolds number: 100,000
Max Cl/Cd: 34.85 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca671215-il-100000.txt
Download as CSV file: xf-naca671215-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5695   0.11943   0.11467  -0.0322   1.0000   0.1424
 -10.750  -0.5710   0.11666   0.11192  -0.0310   1.0000   0.1466
 -10.250  -0.6884   0.10496   0.10039  -0.0378   1.0000   0.1532
 -10.000  -0.6165   0.10448   0.09989  -0.0313   1.0000   0.1593
  -9.750  -0.6346   0.10036   0.09582  -0.0314   1.0000   0.1639
  -9.500  -0.6853   0.09485   0.09034  -0.0322   1.0000   0.1664
  -9.250  -0.7400   0.09150   0.08698  -0.0286   1.0000   0.1674
  -9.000  -0.7867   0.08955   0.08499  -0.0223   1.0000   0.1677
  -8.750  -0.8444   0.08807   0.08336  -0.0149   1.0000   0.1688
  -7.500  -0.9246   0.05748   0.05075   0.0070   1.0000   0.0959
  -7.250  -0.9300   0.05272   0.04482   0.0140   1.0000   0.0802
  -7.000  -0.9183   0.04911   0.04099   0.0161   1.0000   0.0792
  -6.750  -0.9080   0.04616   0.03769   0.0188   1.0000   0.0791
  -6.500  -0.8945   0.04318   0.03438   0.0210   1.0000   0.0784
  -6.250  -0.8791   0.04069   0.03153   0.0232   1.0000   0.0782
  -6.000  -0.8620   0.03860   0.02906   0.0252   1.0000   0.0786
  -5.750  -0.8449   0.03706   0.02711   0.0273   1.0000   0.0803
  -5.500  -0.8240   0.03486   0.02490   0.0279   1.0000   0.0837
  -5.250  -0.8025   0.03351   0.02342   0.0290   1.0000   0.0864
  -5.000  -0.7807   0.03235   0.02207   0.0302   1.0000   0.0899
  -4.750  -0.7594   0.03145   0.02093   0.0314   1.0000   0.0940
  -4.500  -0.7359   0.03009   0.01972   0.0319   1.0000   0.0994
  -4.250  -0.7151   0.02940   0.01892   0.0331   1.0000   0.1060
  -4.000  -0.6939   0.02840   0.01802   0.0340   1.0000   0.1123
  -3.750  -0.6747   0.02774   0.01738   0.0355   1.0000   0.1207
  -3.500  -0.6579   0.02693   0.01670   0.0372   1.0000   0.1307
  -3.250  -0.6424   0.02620   0.01605   0.0392   1.0000   0.1439
  -3.000  -0.6280   0.02542   0.01545   0.0414   1.0000   0.1702
  -2.750  -0.6251   0.02403   0.01784   0.0497   1.0000   0.7319
  -2.500  -0.6329   0.02527   0.01894   0.0591   1.0000   0.8375
  -2.250  -0.1356   0.03899   0.03140  -0.0207   1.0000   1.0000
  -2.000  -0.1259   0.03877   0.03111  -0.0187   1.0000   1.0000
  -1.750  -0.1158   0.03860   0.03086  -0.0168   1.0000   1.0000
  -1.500  -0.1056   0.03847   0.03066  -0.0149   1.0000   1.0000
  -1.250  -0.0953   0.03837   0.03050  -0.0129   1.0000   1.0000
  -1.000  -0.0848   0.03831   0.03038  -0.0110   1.0000   1.0000
  -0.750  -0.0743   0.03828   0.03031  -0.0090   1.0000   1.0000
  -0.500  -0.0638   0.03828   0.03027  -0.0071   1.0000   1.0000
  -0.250  -0.0532   0.03831   0.03026  -0.0052   1.0000   1.0000
   0.000  -0.0426   0.03837   0.03029  -0.0032   1.0000   1.0000
   0.250  -0.0320   0.03846   0.03036  -0.0013   1.0000   1.0000
   0.500  -0.0215   0.03858   0.03046   0.0006   1.0000   1.0000
   0.750  -0.0111   0.03873   0.03059   0.0026   1.0000   1.0000
   1.000  -0.0007   0.03891   0.03076   0.0045   1.0000   1.0000
   1.250   0.0095   0.03912   0.03097   0.0064   1.0000   1.0000
   1.500   0.0195   0.03935   0.03121   0.0083   1.0000   1.0000
   1.750   0.0294   0.03962   0.03148   0.0102   1.0000   1.0000
   2.000   0.0391   0.03992   0.03180   0.0121   1.0000   1.0000
   2.250   0.0486   0.04025   0.03215   0.0140   1.0000   1.0000
   2.500   0.0578   0.04061   0.03254   0.0159   1.0000   1.0000
   2.750   0.0667   0.04101   0.03297   0.0178   1.0000   1.0000
   3.000   0.2482   0.04221   0.03438  -0.0127   0.9264   1.0000
   3.250   0.2885   0.04234   0.03460  -0.0157   0.9077   1.0000
   3.500   0.3282   0.04244   0.03479  -0.0185   0.8910   1.0000
   3.750   0.3664   0.04242   0.03488  -0.0208   0.8751   1.0000
   4.000   0.4041   0.04228   0.03486  -0.0228   0.8598   1.0000
   4.250   0.4443   0.04192   0.03463  -0.0249   0.8442   1.0000
   4.500   0.4954   0.04098   0.03387  -0.0283   0.8273   1.0000
   4.750   0.6039   0.03747   0.03065  -0.0390   0.8071   1.0000
   5.000   0.6394   0.03521   0.02857  -0.0382   0.7827   1.0000
   5.250   0.7047   0.03179   0.02542  -0.0415   0.7628   1.0000
   5.750   0.8072   0.02316   0.01665  -0.0395   0.5514   1.0000
   6.000   0.7343   0.02755   0.02159  -0.0268   0.6562   1.0000
   6.250   0.7925   0.02696   0.01731  -0.0267   0.1643   1.0000
   6.500   0.7965   0.02798   0.01816  -0.0227   0.1428   1.0000
   6.750   0.8053   0.02893   0.01898  -0.0196   0.1288   1.0000
   7.000   0.8221   0.02995   0.01984  -0.0180   0.1172   1.0000
   7.250   0.8453   0.03084   0.02072  -0.0172   0.1078   1.0000
   7.500   0.8834   0.03214   0.02202  -0.0191   0.0981   1.0000
   7.750   0.9460   0.03433   0.02413  -0.0258   0.0876   1.0000
   8.000   0.9796   0.03580   0.02576  -0.0270   0.0817   1.0000
   8.250   1.0242   0.03837   0.02836  -0.0305   0.0760   1.0000
   8.500   1.0449   0.04017   0.03054  -0.0291   0.0739   1.0000
   8.750   1.0606   0.04199   0.03267  -0.0270   0.0716   1.0000
   9.000   1.0740   0.04368   0.03454  -0.0249   0.0692   1.0000
   9.250   1.0913   0.04574   0.03666  -0.0237   0.0668   1.0000
   9.500   1.1032   0.04864   0.03983  -0.0215   0.0661   1.0000
   9.750   1.1059   0.05092   0.04244  -0.0175   0.0663   1.0000
  10.000   1.1030   0.05329   0.04516  -0.0126   0.0665   1.0000
  10.250   1.0796   0.05525   0.04765  -0.0041   0.0678   1.0000
  10.500   1.0507   0.05788   0.05077   0.0048   0.0697   1.0000
  10.750   1.0260   0.06014   0.05331   0.0125   0.0710   1.0000
  11.000   0.9998   0.06184   0.05520   0.0203   0.0720   1.0000
  11.250   0.9733   0.06350   0.05703   0.0278   0.0730   1.0000
  11.500   0.9481   0.06531   0.05896   0.0345   0.0739   1.0000
  11.750   0.9234   0.06732   0.06109   0.0408   0.0747   1.0000
  12.000   0.9106   0.07014   0.06397   0.0451   0.0759   1.0000
  12.250   0.9110   0.07352   0.06742   0.0478   0.0780   1.0000
  12.500   0.8080   0.07482   0.06918   0.0597   0.0814   1.0000
  12.750   0.7556   0.08043   0.07500   0.0621   0.0843   1.0000
  13.000   0.7304   0.08617   0.08081   0.0621   0.0875   1.0000
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