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NACA 65(1)-212 (naca651212-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: NACA 65(1)-212 (naca651212-il)
Reynolds number: 100,000
Max Cl/Cd: 46.75 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca651212-il-100000.txt
Download as CSV file: xf-naca651212-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5648   0.09078   0.08598  -0.0434   1.0000   0.1444
  -9.500  -0.5125   0.08985   0.08498  -0.0348   1.0000   0.1554
  -9.250  -0.5602   0.08321   0.07848  -0.0434   1.0000   0.1584
  -9.000  -0.5273   0.08160   0.07687  -0.0384   1.0000   0.1703
  -8.750  -0.5692   0.07611   0.07149  -0.0431   1.0000   0.1721
  -8.500  -0.5565   0.07337   0.06880  -0.0411   1.0000   0.1840
  -8.250  -0.6001   0.06998   0.06544  -0.0410   1.0000   0.1867
  -8.000  -0.6537   0.06880   0.06411  -0.0376   1.0000   0.1885
  -6.250  -0.6694   0.03939   0.03224  -0.0196   1.0000   0.0913
  -6.000  -0.6535   0.03617   0.02854  -0.0174   1.0000   0.0807
  -5.750  -0.6361   0.03483   0.02631  -0.0147   1.0000   0.0738
  -5.500  -0.6180   0.03191   0.02318  -0.0135   1.0000   0.0727
  -5.250  -0.5994   0.03053   0.02146  -0.0122   1.0000   0.0735
  -5.000  -0.5654   0.02810   0.01874  -0.0137   0.9964   0.0751
  -4.750  -0.5294   0.02624   0.01674  -0.0153   0.9924   0.0760
  -4.500  -0.4948   0.02477   0.01524  -0.0167   0.9878   0.0784
  -4.250  -0.4572   0.02380   0.01421  -0.0188   0.9835   0.0841
  -4.000  -0.4269   0.02273   0.01315  -0.0195   0.9779   0.0897
  -3.750  -0.3938   0.02178   0.01231  -0.0210   0.9727   0.0980
  -3.500  -0.3641   0.02099   0.01156  -0.0220   0.9674   0.1149
  -3.250  -0.3385   0.01934   0.01055  -0.0227   0.9616   0.1967
  -3.000  -0.3298   0.01840   0.01198  -0.0171   0.9562   0.7176
  -2.750  -0.3164   0.01922   0.01278  -0.0125   0.9484   0.7615
  -2.500  -0.2981   0.02045   0.01402  -0.0076   0.9429   0.8046
  -2.250  -0.2947   0.02139   0.01498  -0.0002   0.9353   0.8426
  -2.000  -0.2704   0.02280   0.01633   0.0053   0.9309   0.8824
  -1.750  -0.2219   0.02323   0.01657   0.0019   0.9281   0.8973
  -1.500  -0.1993   0.02316   0.01637   0.0021   0.9215   0.9063
  -1.250  -0.1636   0.02316   0.01622  -0.0003   0.9164   0.9141
  -1.000  -0.1149   0.02324   0.01616  -0.0050   0.9132   0.9194
  -0.750  -0.0915   0.02324   0.01609  -0.0053   0.9066   0.9278
  -0.500  -0.0496   0.02328   0.01603  -0.0089   0.9020   0.9335
  -0.250   0.0047   0.02339   0.01606  -0.0147   0.8991   0.9376
   0.000   0.0297   0.02346   0.01609  -0.0154   0.8927   0.9460
   0.250   0.0803   0.02357   0.01616  -0.0208   0.8886   0.9501
   0.500   0.1308   0.02365   0.01622  -0.0260   0.8853   0.9551
   0.750   0.1792   0.02373   0.01630  -0.0309   0.8819   0.9598
   1.000   0.2131   0.02390   0.01650  -0.0335   0.8751   0.9667
   1.250   0.2601   0.02398   0.01662  -0.0381   0.8712   0.9721
   1.500   0.3203   0.02394   0.01665  -0.0450   0.8687   0.9748
   1.750   0.3473   0.02426   0.01703  -0.0465   0.8609   0.9837
   2.000   0.4017   0.02423   0.01712  -0.0524   0.8568   0.9875
   2.250   0.4573   0.02408   0.01709  -0.0582   0.8535   0.9912
   2.500   0.4916   0.02434   0.01750  -0.0610   0.8446   0.9990
   2.750   0.5336   0.02413   0.01742  -0.0638   0.8392   1.0000
   3.000   0.5282   0.02467   0.01802  -0.0591   0.8273   1.0000
   3.250   0.5346   0.02498   0.01840  -0.0561   0.8170   1.0000
   3.500   0.5738   0.02455   0.01814  -0.0576   0.8094   1.0000
   3.750   0.6521   0.02030   0.01407  -0.0589   0.7745   1.0000
   4.000   0.6782   0.01778   0.01153  -0.0538   0.7372   1.0000
   4.250   0.6935   0.01685   0.01067  -0.0499   0.7099   1.0000
   4.500   0.7080   0.01594   0.00979  -0.0458   0.6750   1.0000
   4.750   0.7116   0.01522   0.00897  -0.0397   0.6009   1.0000
   5.000   0.6896   0.01610   0.00839  -0.0299   0.3340   1.0000
   5.250   0.6650   0.01824   0.00929  -0.0220   0.1606   1.0000
   5.500   0.6647   0.01978   0.01036  -0.0177   0.1163   1.0000
   5.750   0.6756   0.02092   0.01139  -0.0153   0.0991   1.0000
   6.000   0.6892   0.02216   0.01255  -0.0133   0.0896   1.0000
   6.250   0.7089   0.02337   0.01372  -0.0120   0.0830   1.0000
   6.500   0.7351   0.02513   0.01530  -0.0119   0.0774   1.0000
   6.750   0.7631   0.02643   0.01669  -0.0118   0.0723   1.0000
   7.000   0.7947   0.02822   0.01853  -0.0123   0.0694   1.0000
   7.250   0.8276   0.03050   0.02085  -0.0130   0.0676   1.0000
   7.500   0.8588   0.03334   0.02382  -0.0135   0.0665   1.0000
   7.750   0.8833   0.03622   0.02699  -0.0131   0.0651   1.0000
   8.000   0.9042   0.03857   0.02973  -0.0120   0.0646   1.0000
   8.250   0.9267   0.04277   0.03419  -0.0116   0.0655   1.0000
   8.500   0.9389   0.04438   0.03671  -0.0082   0.0701   1.0000
   8.750   0.9513   0.04934   0.04212  -0.0064   0.0760   1.0000
  11.000   0.7228   0.11241   0.10767  -0.0173   0.1713   1.0000
  11.250   0.7366   0.11555   0.11084  -0.0165   0.1646   1.0000
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