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NACA 0012-64 (naca001264-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0012-64 (naca001264-il)
Reynolds number: 200,000
Max Cl/Cd: 40.28 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001264-il-200000-n5.txt
Download as CSV file: xf-naca001264-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0012-64                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.250  -0.8927   0.09374   0.08947  -0.0304   1.0000   0.0264
 -15.000  -0.9339   0.08114   0.07665  -0.0390   1.0000   0.0261
 -14.750  -0.9666   0.07189   0.06716  -0.0449   1.0000   0.0261
 -14.500  -0.9943   0.06468   0.05969  -0.0487   1.0000   0.0261
 -14.250  -1.0182   0.05890   0.05362  -0.0506   1.0000   0.0263
 -14.000  -1.0379   0.05427   0.04871  -0.0511   1.0000   0.0265
 -13.750  -1.0446   0.05123   0.04555  -0.0506   1.0000   0.0268
 -13.500  -1.0470   0.04887   0.04311  -0.0498   1.0000   0.0272
 -13.250  -1.0483   0.04679   0.04092  -0.0486   1.0000   0.0275
 -13.000  -1.0494   0.04483   0.03884  -0.0471   1.0000   0.0279
 -12.750  -1.0498   0.04302   0.03690  -0.0453   1.0000   0.0284
 -12.500  -1.0500   0.04132   0.03503  -0.0431   1.0000   0.0290
 -12.250  -1.0498   0.03966   0.03318  -0.0406   1.0000   0.0296
 -12.000  -1.0490   0.03807   0.03138  -0.0377   1.0000   0.0304
 -11.750  -1.0474   0.03654   0.02962  -0.0346   1.0000   0.0311
 -11.500  -1.0445   0.03513   0.02794  -0.0314   1.0000   0.0318
 -11.250  -1.0381   0.03383   0.02639  -0.0286   1.0000   0.0323
 -11.000  -1.0271   0.03233   0.02483  -0.0267   1.0000   0.0331
 -10.750  -1.0153   0.03138   0.02385  -0.0246   1.0000   0.0339
 -10.500  -1.0034   0.03052   0.02292  -0.0224   1.0000   0.0347
 -10.250  -0.9912   0.02962   0.02191  -0.0201   1.0000   0.0355
 -10.000  -0.9783   0.02867   0.02082  -0.0179   1.0000   0.0364
  -9.750  -0.9646   0.02774   0.01975  -0.0157   1.0000   0.0372
  -9.500  -0.9506   0.02689   0.01876  -0.0135   1.0000   0.0382
  -9.250  -0.9361   0.02613   0.01784  -0.0114   1.0000   0.0390
  -9.000  -0.9214   0.02510   0.01676  -0.0093   1.0000   0.0398
  -8.750  -0.9072   0.02425   0.01587  -0.0072   1.0000   0.0406
  -8.500  -0.8931   0.02354   0.01513  -0.0049   1.0000   0.0414
  -8.250  -0.8788   0.02293   0.01448  -0.0027   1.0000   0.0424
  -8.000  -0.8642   0.02235   0.01385  -0.0004   1.0000   0.0435
  -7.750  -0.8495   0.02178   0.01322   0.0018   1.0000   0.0447
  -7.500  -0.8346   0.02121   0.01257   0.0040   1.0000   0.0458
  -7.250  -0.8196   0.02066   0.01195   0.0063   1.0000   0.0467
  -7.000  -0.8048   0.02010   0.01134   0.0085   1.0000   0.0476
  -6.750  -0.7802   0.01937   0.01062   0.0086   0.9980   0.0492
  -6.500  -0.7505   0.01881   0.01003   0.0077   0.9954   0.0513
  -6.250  -0.7204   0.01832   0.00950   0.0068   0.9927   0.0541
  -5.750  -0.6617   0.01728   0.00844   0.0053   0.9863   0.0609
  -5.500  -0.6300   0.01685   0.00798   0.0041   0.9839   0.0663
  -5.250  -0.6027   0.01638   0.00754   0.0038   0.9798   0.0732
  -5.000  -0.5729   0.01597   0.00714   0.0030   0.9762   0.0832
  -4.750  -0.5415   0.01553   0.00677   0.0019   0.9734   0.0978
  -4.500  -0.5127   0.01511   0.00644   0.0013   0.9697   0.1177
  -4.250  -0.4853   0.01468   0.00613   0.0010   0.9651   0.1440
  -4.000  -0.4546   0.01423   0.00585  -0.0001   0.9619   0.1794
  -3.750  -0.4227   0.01374   0.00555  -0.0014   0.9595   0.2244
  -3.500  -0.4011   0.01313   0.00527  -0.0006   0.9533   0.2921
  -3.250  -0.3792   0.01213   0.00495   0.0000   0.9486   0.4303
  -3.000  -0.3548   0.01132   0.00480   0.0005   0.9453   0.5670
  -2.750  -0.3331   0.01100   0.00478   0.0020   0.9390   0.6386
  -2.500  -0.3044   0.01083   0.00475   0.0020   0.9345   0.6829
  -2.250  -0.2725   0.01071   0.00473   0.0014   0.9313   0.7185
  -2.000  -0.2418   0.01064   0.00474   0.0011   0.9275   0.7505
  -1.750  -0.2157   0.01064   0.00482   0.0018   0.9210   0.7811
  -1.500  -0.1845   0.01063   0.00486   0.0015   0.9168   0.8053
  -1.250  -0.1505   0.01066   0.00492   0.0007   0.9137   0.8252
  -1.000  -0.1242   0.01077   0.00507   0.0015   0.9067   0.8450
  -0.750  -0.0926   0.01085   0.00516   0.0012   0.9016   0.8600
  -0.500  -0.0589   0.01085   0.00515   0.0003   0.8978   0.8696
  -0.250  -0.0317   0.01089   0.00519   0.0006   0.8898   0.8774
   0.000   0.0000   0.01086   0.00516   0.0000   0.8842   0.8842
   0.250   0.0317   0.01089   0.00519  -0.0006   0.8774   0.8898
   0.500   0.0589   0.01085   0.00515  -0.0003   0.8696   0.8978
   0.750   0.0926   0.01085   0.00516  -0.0012   0.8600   0.9016
   1.000   0.1242   0.01077   0.00507  -0.0015   0.8451   0.9066
   1.250   0.1505   0.01066   0.00492  -0.0007   0.8252   0.9137
   1.500   0.1845   0.01063   0.00486  -0.0015   0.8053   0.9168
   1.750   0.2157   0.01064   0.00482  -0.0018   0.7811   0.9210
   2.000   0.2418   0.01064   0.00474  -0.0011   0.7505   0.9275
   2.250   0.2724   0.01071   0.00473  -0.0014   0.7185   0.9313
   2.500   0.3044   0.01083   0.00475  -0.0020   0.6830   0.9345
   2.750   0.3331   0.01100   0.00478  -0.0019   0.6385   0.9390
   3.000   0.3548   0.01132   0.00480  -0.0005   0.5672   0.9453
   3.250   0.3792   0.01212   0.00495   0.0000   0.4305   0.9486
   3.500   0.4010   0.01312   0.00527   0.0006   0.2921   0.9533
   3.750   0.4227   0.01373   0.00555   0.0014   0.2244   0.9595
   4.000   0.4546   0.01423   0.00584   0.0001   0.1793   0.9619
   4.250   0.4853   0.01468   0.00613  -0.0010   0.1440   0.9652
   4.500   0.5127   0.01511   0.00644  -0.0013   0.1177   0.9697
   4.750   0.5415   0.01553   0.00676  -0.0019   0.0978   0.9735
   5.000   0.5729   0.01596   0.00714  -0.0030   0.0832   0.9762
   5.250   0.6027   0.01638   0.00754  -0.0038   0.0733   0.9798
   5.500   0.6301   0.01685   0.00798  -0.0041   0.0663   0.9839
   5.750   0.6618   0.01728   0.00844  -0.0053   0.0609   0.9864
   6.000   0.6912   0.01785   0.00898  -0.0061   0.0569   0.9895
   6.250   0.7204   0.01831   0.00950  -0.0068   0.0541   0.9928
   6.500   0.7505   0.01880   0.01003  -0.0077   0.0513   0.9954
   6.750   0.7803   0.01937   0.01062  -0.0086   0.0492   0.9981
   7.000   0.8047   0.02010   0.01134  -0.0085   0.0476   1.0000
   7.250   0.8195   0.02065   0.01194  -0.0063   0.0467   1.0000
   7.500   0.8345   0.02120   0.01257  -0.0040   0.0458   1.0000
   7.750   0.8494   0.02177   0.01322  -0.0018   0.0447   1.0000
   8.000   0.8641   0.02234   0.01385   0.0005   0.0436   1.0000
   8.250   0.8787   0.02292   0.01447   0.0027   0.0424   1.0000
   8.500   0.8930   0.02354   0.01513   0.0050   0.0414   1.0000
   8.750   0.9072   0.02424   0.01587   0.0072   0.0406   1.0000
   9.000   0.9213   0.02510   0.01675   0.0094   0.0398   1.0000
   9.250   0.9361   0.02612   0.01783   0.0114   0.0390   1.0000
   9.500   0.9506   0.02689   0.01875   0.0135   0.0382   1.0000
   9.750   0.9647   0.02773   0.01975   0.0157   0.0372   1.0000
  10.000   0.9783   0.02866   0.02082   0.0179   0.0364   1.0000
  10.250   0.9913   0.02962   0.02191   0.0201   0.0355   1.0000
  10.500   1.0036   0.03052   0.02291   0.0223   0.0347   1.0000
  10.750   1.0155   0.03138   0.02384   0.0245   0.0339   1.0000
  11.000   1.0273   0.03233   0.02483   0.0266   0.0331   1.0000
  11.250   1.0384   0.03384   0.02640   0.0285   0.0323   1.0000
  11.500   1.0448   0.03513   0.02794   0.0314   0.0318   1.0000
  12.000   1.0495   0.03807   0.03139   0.0376   0.0304   1.0000
  12.250   1.0504   0.03966   0.03319   0.0404   0.0296   1.0000
  12.500   1.0507   0.04132   0.03503   0.0430   0.0290   1.0000
  12.750   1.0507   0.04302   0.03689   0.0451   0.0284   1.0000
  13.000   1.0503   0.04483   0.03884   0.0470   0.0279   1.0000
  13.250   1.0493   0.04678   0.04091   0.0485   0.0275   1.0000
  13.500   1.0482   0.04886   0.04309   0.0496   0.0271   1.0000
  13.750   1.0458   0.05122   0.04555   0.0504   0.0268   1.0000
  14.000   1.0389   0.05430   0.04873   0.0509   0.0265   1.0000
  14.250   1.0188   0.05898   0.05371   0.0504   0.0263   1.0000
  14.500   0.9948   0.06481   0.05983   0.0483   0.0261   1.0000
  14.750   0.9671   0.07205   0.06734   0.0446   0.0261   1.0000
  15.000   0.9343   0.08141   0.07694   0.0385   0.0261   1.0000
  15.250   0.8921   0.09429   0.09003   0.0297   0.0264   1.0000
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