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NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il)
Reynolds number: 100,000
Max Cl/Cd: 45.72 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651212a06-il-100000-n5.txt
Download as CSV file: xf-naca651212a06-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65(1)-212 a=0.6                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5196   0.09394   0.08895  -0.0366   1.0000   0.0340
 -10.500  -0.5255   0.08758   0.08266  -0.0407   1.0000   0.0337
 -10.250  -0.5349   0.08049   0.07559  -0.0459   1.0000   0.0330
 -10.000  -0.5507   0.07381   0.06889  -0.0509   1.0000   0.0323
  -9.750  -0.5709   0.06824   0.06326  -0.0543   1.0000   0.0323
  -9.500  -0.5899   0.06401   0.05895  -0.0552   1.0000   0.0318
  -9.250  -0.6077   0.06068   0.05553  -0.0540   1.0000   0.0317
  -9.000  -0.6218   0.05740   0.05211  -0.0523   1.0000   0.0316
  -8.750  -0.6384   0.05502   0.04961  -0.0486   1.0000   0.0316
  -8.500  -0.6330   0.05052   0.04473  -0.0498   0.9859   0.0315
  -8.250  -0.6193   0.04598   0.03971  -0.0515   0.9751   0.0315
  -8.000  -0.6029   0.04203   0.03526  -0.0524   0.9655   0.0317
  -7.750  -0.5838   0.03866   0.03137  -0.0529   0.9568   0.0321
  -7.500  -0.5608   0.03595   0.02813  -0.0535   0.9497   0.0338
  -7.250  -0.5396   0.03383   0.02552  -0.0531   0.9409   0.0350
  -7.000  -0.5137   0.03167   0.02289  -0.0534   0.9349   0.0356
  -6.750  -0.4909   0.02990   0.02079  -0.0528   0.9267   0.0361
  -6.500  -0.4642   0.02758   0.01825  -0.0531   0.9211   0.0371
  -6.250  -0.4398   0.02613   0.01670  -0.0529   0.9143   0.0385
  -6.000  -0.4146   0.02509   0.01557  -0.0527   0.9079   0.0410
  -5.750  -0.3887   0.02404   0.01438  -0.0525   0.9022   0.0433
  -5.500  -0.3647   0.02303   0.01324  -0.0518   0.8954   0.0448
  -5.250  -0.3398   0.02211   0.01221  -0.0512   0.8902   0.0464
  -5.000  -0.3190   0.02121   0.01130  -0.0502   0.8835   0.0485
  -4.750  -0.2974   0.02052   0.01061  -0.0494   0.8776   0.0528
  -4.500  -0.2748   0.01995   0.00992  -0.0486   0.8724   0.0572
  -4.250  -0.2542   0.01937   0.00926  -0.0475   0.8658   0.0616
  -4.000  -0.2316   0.01883   0.00866  -0.0466   0.8609   0.0702
  -3.750  -0.2102   0.01823   0.00813  -0.0457   0.8556   0.0892
  -3.500  -0.1944   0.01703   0.00757  -0.0443   0.8494   0.2066
  -3.250  -0.1860   0.01543   0.00747  -0.0411   0.8445   0.5311
  -3.000  -0.1673   0.01543   0.00772  -0.0388   0.8391   0.6371
  -2.750  -0.1491   0.01567   0.00815  -0.0358   0.8339   0.7065
  -2.500  -0.1308   0.01598   0.00849  -0.0325   0.8297   0.7593
  -2.250  -0.1080   0.01599   0.00842  -0.0310   0.8252   0.7826
  -2.000  -0.0826   0.01593   0.00825  -0.0307   0.8200   0.7920
  -1.750  -0.0558   0.01583   0.00804  -0.0306   0.8161   0.8006
  -1.500  -0.0272   0.01576   0.00787  -0.0306   0.8129   0.8079
  -1.250  -0.0009   0.01580   0.00786  -0.0304   0.8076   0.8151
  -1.000   0.0265   0.01583   0.00785  -0.0304   0.8031   0.8225
  -0.750   0.0563   0.01588   0.00786  -0.0306   0.7997   0.8284
  -0.500   0.0862   0.01591   0.00784  -0.0308   0.7969   0.8354
  -0.250   0.1140   0.01614   0.00808  -0.0309   0.7913   0.8414
   0.000   0.1432   0.01627   0.00821  -0.0311   0.7871   0.8485
   0.250   0.1735   0.01638   0.00829  -0.0315   0.7838   0.8560
   0.500   0.2028   0.01648   0.00838  -0.0317   0.7804   0.8654
   0.750   0.2172   0.01671   0.00861  -0.0298   0.7740   0.8890
   1.000   0.2389   0.01677   0.00865  -0.0288   0.7698   0.9056
   1.250   0.2683   0.01674   0.00863  -0.0291   0.7668   0.9163
   1.500   0.2976   0.01689   0.00883  -0.0299   0.7616   0.9264
   1.750   0.3307   0.01698   0.00899  -0.0313   0.7571   0.9355
   2.000   0.3660   0.01701   0.00906  -0.0329   0.7536   0.9443
   2.250   0.4059   0.01701   0.00912  -0.0354   0.7510   0.9504
   2.500   0.4403   0.01727   0.00951  -0.0375   0.7449   0.9599
   2.750   0.4803   0.01737   0.00972  -0.0403   0.7406   0.9667
   3.000   0.5194   0.01738   0.00983  -0.0427   0.7370   0.9743
   3.250   0.5569   0.01753   0.01015  -0.0452   0.7309   0.9829
   3.500   0.5949   0.01753   0.01030  -0.0475   0.7242   0.9914
   3.750   0.6318   0.01744   0.01035  -0.0493   0.7171   1.0000
   4.000   0.6503   0.01701   0.01000  -0.0468   0.7005   1.0000
   4.250   0.6675   0.01595   0.00888  -0.0429   0.6638   1.0000
   4.500   0.6824   0.01532   0.00814  -0.0393   0.6127   1.0000
   4.750   0.6973   0.01525   0.00801  -0.0364   0.5600   1.0000
   5.000   0.7069   0.01555   0.00765  -0.0324   0.4276   1.0000
   5.250   0.6987   0.01729   0.00833  -0.0267   0.2573   1.0000
   5.500   0.6955   0.01904   0.00927  -0.0224   0.1295   1.0000
   5.750   0.7016   0.02031   0.01014  -0.0193   0.0795   1.0000
   6.000   0.7130   0.02126   0.01098  -0.0169   0.0641   1.0000
   6.250   0.7268   0.02207   0.01184  -0.0148   0.0567   1.0000
   6.750   0.7525   0.02386   0.01373  -0.0107   0.0475   1.0000
   7.000   0.7658   0.02476   0.01467  -0.0088   0.0440   1.0000
   7.250   0.7775   0.02580   0.01573  -0.0067   0.0419   1.0000
   7.500   0.7904   0.02715   0.01705  -0.0048   0.0402   1.0000
   7.750   0.8104   0.02827   0.01827  -0.0037   0.0388   1.0000
   8.000   0.8326   0.02944   0.01958  -0.0031   0.0367   1.0000
   8.250   0.8552   0.03068   0.02090  -0.0026   0.0345   1.0000
   8.500   0.8798   0.03215   0.02245  -0.0024   0.0329   1.0000
   8.750   0.9060   0.03391   0.02429  -0.0025   0.0319   1.0000
   9.000   0.9331   0.03616   0.02665  -0.0028   0.0310   1.0000
   9.250   0.9587   0.03905   0.02975  -0.0029   0.0304   1.0000
   9.500   0.9759   0.04125   0.03229  -0.0018   0.0300   1.0000
   9.750   0.9886   0.04353   0.03494  -0.0002   0.0296   1.0000
  10.000   0.9971   0.04584   0.03763   0.0017   0.0290   1.0000
  10.250   1.0015   0.04823   0.04040   0.0040   0.0282   1.0000
  10.500   1.0013   0.05066   0.04316   0.0066   0.0275   1.0000
  10.750   0.9969   0.05335   0.04615   0.0093   0.0272   1.0000
  11.000   0.9886   0.05630   0.04939   0.0119   0.0270   1.0000
  11.250   0.9780   0.05947   0.05283   0.0141   0.0270   1.0000
  11.500   0.9641   0.06291   0.05653   0.0158   0.0270   1.0000
  11.750   0.9485   0.06670   0.06057   0.0168   0.0270   1.0000
  12.000   0.9303   0.07097   0.06506   0.0171   0.0271   1.0000
  12.250   0.9099   0.07578   0.07008   0.0166   0.0272   1.0000
  12.500   0.8878   0.08127   0.07575   0.0150   0.0273   1.0000
  12.750   0.8643   0.08759   0.08224   0.0123   0.0275   1.0000
  13.000   0.8386   0.09520   0.09000   0.0081   0.0278   1.0000
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