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NACA 65(1)-212 a=0.6 (naca651212a06-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NACA 65(1)-212 a=0.6 (naca651212a06-il)
Reynolds number: 50,000
Max Cl/Cd: 29.47 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca651212a06-il-50000-n5.txt
Download as CSV file: xf-naca651212a06-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.5124   0.12761   0.12036  -0.0243   1.0000   0.0718
 -11.750  -0.4992   0.12331   0.11603  -0.0239   1.0000   0.0670
 -11.500  -0.5176   0.11530   0.10812  -0.0316   1.0000   0.0592
 -11.250  -0.5105   0.11123   0.10406  -0.0321   1.0000   0.0584
 -11.000  -0.5097   0.10653   0.09940  -0.0342   1.0000   0.0581
 -10.750  -0.5108   0.10153   0.09444  -0.0368   1.0000   0.0577
 -10.500  -0.5136   0.09620   0.08916  -0.0399   1.0000   0.0574
 -10.250  -0.5177   0.09061   0.08362  -0.0434   1.0000   0.0569
 -10.000  -0.5260   0.08495   0.07799  -0.0472   1.0000   0.0563
  -9.750  -0.5391   0.07954   0.07260  -0.0507   1.0000   0.0557
  -9.500  -0.5545   0.07495   0.06800  -0.0528   1.0000   0.0550
  -9.250  -0.5720   0.07119   0.06421  -0.0531   1.0000   0.0545
  -9.000  -0.5879   0.06774   0.06070  -0.0524   1.0000   0.0542
  -8.750  -0.6012   0.06450   0.05735  -0.0510   1.0000   0.0541
  -8.500  -0.6138   0.06166   0.05438  -0.0486   1.0000   0.0539
  -8.250  -0.6268   0.05924   0.05182  -0.0451   1.0000   0.0537
  -8.000  -0.6391   0.05697   0.04937  -0.0413   1.0000   0.0535
  -7.750  -0.6488   0.05469   0.04687  -0.0375   1.0000   0.0532
  -7.500  -0.6552   0.05231   0.04423  -0.0339   1.0000   0.0532
  -7.250  -0.6576   0.04995   0.04158  -0.0307   1.0000   0.0530
  -7.000  -0.6504   0.04715   0.03839  -0.0291   0.9974   0.0532
  -6.750  -0.6275   0.04390   0.03461  -0.0300   0.9902   0.0536
  -6.500  -0.6016   0.04115   0.03132  -0.0310   0.9838   0.0557
  -6.250  -0.5748   0.03881   0.02838  -0.0316   0.9773   0.0582
  -6.000  -0.5452   0.03669   0.02569  -0.0323   0.9719   0.0594
  -5.750  -0.5150   0.03442   0.02329  -0.0333   0.9668   0.0610
  -5.500  -0.4806   0.03270   0.02143  -0.0347   0.9628   0.0636
  -5.250  -0.4515   0.03149   0.02006  -0.0351   0.9572   0.0683
  -5.000  -0.4178   0.03040   0.01868  -0.0359   0.9527   0.0728
  -4.750  -0.3844   0.02911   0.01739  -0.0371   0.9491   0.0772
  -4.500  -0.3615   0.02830   0.01645  -0.0365   0.9423   0.0835
  -4.250  -0.3336   0.02736   0.01545  -0.0372   0.9372   0.0942
  -4.000  -0.3092   0.02646   0.01447  -0.0372   0.9316   0.1065
  -3.750  -0.2884   0.02539   0.01358  -0.0368   0.9252   0.1369
  -3.500  -0.2790   0.02269   0.01311  -0.0349   0.9202   0.4689
  -3.250  -0.2700   0.02287   0.01375  -0.0297   0.9129   0.6551
  -3.000  -0.2557   0.02365   0.01470  -0.0239   0.9076   0.7629
  -2.750  -0.1996   0.02561   0.01657  -0.0221   0.9081   0.8450
  -2.500  -0.1560   0.02573   0.01636  -0.0251   0.9050   0.8556
  -2.250  -0.1296   0.02581   0.01620  -0.0254   0.8990   0.8671
  -2.000  -0.1017   0.02584   0.01602  -0.0261   0.8935   0.8788
  -1.500  -0.0532   0.02582   0.01567  -0.0264   0.8823   0.9032
  -1.250  -0.0200   0.02579   0.01547  -0.0282   0.8778   0.9132
  -1.000   0.0194   0.02576   0.01529  -0.0311   0.8745   0.9220
  -0.750   0.0485   0.02581   0.01524  -0.0323   0.8687   0.9323
  -0.500   0.0921   0.02584   0.01517  -0.0362   0.8647   0.9391
  -0.250   0.1339   0.02586   0.01511  -0.0398   0.8611   0.9470
   0.000   0.1786   0.02590   0.01508  -0.0439   0.8578   0.9541
   0.250   0.2119   0.02605   0.01522  -0.0462   0.8519   0.9641
   0.500   0.2512   0.02614   0.01531  -0.0495   0.8476   0.9734
   0.750   0.2955   0.02618   0.01536  -0.0535   0.8443   0.9817
   1.000   0.3302   0.02639   0.01561  -0.0563   0.8386   0.9932
   1.250   0.3574   0.02660   0.01585  -0.0575   0.8328   1.0000
   1.500   0.3780   0.02674   0.01603  -0.0570   0.8280   1.0000
   1.750   0.3707   0.02725   0.01654  -0.0521   0.8182   1.0000
   2.000   0.3918   0.02746   0.01678  -0.0515   0.8132   1.0000
   2.250   0.3885   0.02803   0.01734  -0.0471   0.8039   1.0000
   2.500   0.4100   0.02833   0.01768  -0.0464   0.7986   1.0000
   2.750   0.4135   0.02891   0.01828  -0.0431   0.7900   1.0000
   3.000   0.4346   0.02927   0.01873  -0.0423   0.7840   1.0000
   3.250   0.4445   0.02983   0.01933  -0.0398   0.7757   1.0000
   3.500   0.4665   0.03021   0.01981  -0.0391   0.7689   1.0000
   3.750   0.4801   0.03074   0.02043  -0.0372   0.7601   1.0000
   4.000   0.5058   0.03105   0.02092  -0.0369   0.7530   1.0000
   4.250   0.5192   0.03162   0.02160  -0.0350   0.7430   1.0000
   4.500   0.5516   0.03174   0.02193  -0.0354   0.7364   1.0000
   4.750   0.5645   0.03229   0.02263  -0.0333   0.7246   1.0000
   5.000   0.5864   0.03254   0.02312  -0.0322   0.7133   1.0000
   5.250   0.6183   0.03226   0.02313  -0.0317   0.7019   1.0000
   5.500   0.6733   0.02698   0.01811  -0.0272   0.6416   1.0000
   5.750   0.6804   0.02550   0.01671  -0.0210   0.5752   1.0000
   6.000   0.7049   0.02392   0.01458  -0.0163   0.4011   1.0000
   6.250   0.6936   0.02600   0.01512  -0.0105   0.2138   1.0000
   6.500   0.6849   0.02820   0.01662  -0.0064   0.1407   1.0000
   6.750   0.6849   0.03003   0.01811  -0.0033   0.1103   1.0000
   7.000   0.6908   0.03160   0.01957  -0.0010   0.0958   1.0000
   7.250   0.6998   0.03309   0.02103   0.0010   0.0869   1.0000
   7.500   0.7119   0.03447   0.02244   0.0027   0.0787   1.0000
   7.750   0.7291   0.03575   0.02380   0.0041   0.0720   1.0000
   8.000   0.7549   0.03695   0.02510   0.0050   0.0673   1.0000
   8.250   0.7988   0.03835   0.02656   0.0041   0.0617   1.0000
   8.500   0.8421   0.04011   0.02863   0.0026   0.0562   1.0000
   8.750   0.8813   0.04240   0.03109   0.0014   0.0539   1.0000
   9.000   0.9138   0.04518   0.03402   0.0007   0.0521   1.0000
   9.250   0.9350   0.04796   0.03714   0.0013   0.0507   1.0000
   9.500   0.9474   0.05053   0.04022   0.0028   0.0491   1.0000
   9.750   0.9560   0.05330   0.04342   0.0046   0.0476   1.0000
  10.000   0.9612   0.05627   0.04677   0.0064   0.0469   1.0000
  10.250   0.9618   0.05943   0.05029   0.0084   0.0466   1.0000
  10.500   0.9569   0.06255   0.05373   0.0108   0.0465   1.0000
  10.750   0.9473   0.06575   0.05722   0.0131   0.0465   1.0000
  11.000   0.9340   0.06921   0.06093   0.0150   0.0465   1.0000
  11.250   0.9187   0.07291   0.06488   0.0162   0.0466   1.0000
  11.500   0.9005   0.07707   0.06925   0.0167   0.0468   1.0000
  11.750   0.8806   0.08170   0.07407   0.0163   0.0471   1.0000
  12.000   0.8588   0.08701   0.07955   0.0148   0.0474   1.0000
  12.250   0.8359   0.09312   0.08579   0.0123   0.0478   1.0000
  12.500   0.8131   0.10008   0.09285   0.0086   0.0482   1.0000
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