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NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-012A AIRFOIL (n64012a-il)
Reynolds number: 1,000,000
Max Cl/Cd: 64.88 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012a-il-1000000-n5.txt
Download as CSV file: xf-n64012a-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64-012A AIRFOIL                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -18.000  -1.0719   0.12038   0.11827   0.0105   1.0000   0.0068
 -17.750  -1.1445   0.10053   0.09818  -0.0001   1.0000   0.0067
 -17.500  -1.1872   0.08762   0.08507  -0.0074   1.0000   0.0067
 -17.250  -1.2161   0.07821   0.07549  -0.0127   1.0000   0.0066
 -17.000  -1.2366   0.07087   0.06799  -0.0166   1.0000   0.0067
 -16.750  -1.2513   0.06493   0.06190  -0.0195   1.0000   0.0067
 -16.500  -1.2633   0.05976   0.05660  -0.0218   1.0000   0.0067
 -16.250  -1.2714   0.05539   0.05209  -0.0235   1.0000   0.0067
 -16.000  -1.2771   0.05153   0.04810  -0.0248   1.0000   0.0068
 -15.750  -1.2815   0.04797   0.04440  -0.0258   1.0000   0.0068
 -15.500  -1.2922   0.04386   0.04014  -0.0266   1.0000   0.0069
 -15.250  -1.2969   0.04061   0.03675  -0.0269   1.0000   0.0070
 -15.000  -1.2973   0.03796   0.03400  -0.0269   1.0000   0.0072
 -14.750  -1.2945   0.03575   0.03168  -0.0267   1.0000   0.0073
 -14.500  -1.2895   0.03383   0.02968  -0.0263   1.0000   0.0074
 -14.250  -1.2828   0.03215   0.02790  -0.0257   1.0000   0.0075
 -14.000  -1.2748   0.03065   0.02632  -0.0250   1.0000   0.0076
 -13.750  -1.2658   0.02929   0.02488  -0.0242   1.0000   0.0077
 -13.500  -1.2561   0.02804   0.02355  -0.0232   1.0000   0.0078
 -13.250  -1.2456   0.02690   0.02231  -0.0221   1.0000   0.0079
 -13.000  -1.2345   0.02584   0.02117  -0.0209   1.0000   0.0081
 -12.750  -1.2228   0.02485   0.02009  -0.0195   1.0000   0.0082
 -12.500  -1.2104   0.02393   0.01909  -0.0181   1.0000   0.0084
 -12.250  -1.1971   0.02310   0.01817  -0.0166   1.0000   0.0085
 -12.000  -1.1827   0.02235   0.01734  -0.0151   1.0000   0.0087
 -11.750  -1.1667   0.02167   0.01659  -0.0138   1.0000   0.0089
 -11.500  -1.1488   0.02100   0.01585  -0.0127   1.0000   0.0091
 -11.250  -1.1301   0.02037   0.01515  -0.0118   1.0000   0.0092
 -11.000  -1.1109   0.01974   0.01443  -0.0108   1.0000   0.0093
 -10.750  -1.0913   0.01913   0.01376  -0.0099   1.0000   0.0094
 -10.500  -1.0753   0.01813   0.01267  -0.0086   1.0000   0.0097
 -10.250  -1.0568   0.01736   0.01184  -0.0074   1.0000   0.0099
 -10.000  -1.0368   0.01674   0.01117  -0.0065   1.0000   0.0101
  -9.750  -1.0159   0.01621   0.01060  -0.0056   1.0000   0.0104
  -9.500  -0.9944   0.01575   0.01010  -0.0049   1.0000   0.0107
  -9.250  -0.9729   0.01531   0.00963  -0.0040   1.0000   0.0109
  -9.000  -0.9518   0.01486   0.00915  -0.0031   1.0000   0.0112
  -8.750  -0.9313   0.01441   0.00866  -0.0020   1.0000   0.0114
  -8.500  -0.9040   0.01394   0.00814  -0.0024   0.9962   0.0117
  -8.250  -0.8741   0.01347   0.00762  -0.0033   0.9894   0.0120
  -8.000  -0.8436   0.01303   0.00714  -0.0043   0.9812   0.0123
  -7.750  -0.8130   0.01264   0.00670  -0.0053   0.9712   0.0125
  -7.500  -0.7840   0.01221   0.00623  -0.0059   0.9577   0.0130
  -7.250  -0.7578   0.01180   0.00577  -0.0058   0.9405   0.0137
  -7.000  -0.7331   0.01150   0.00541  -0.0054   0.9214   0.0143
  -6.750  -0.7088   0.01125   0.00508  -0.0048   0.9027   0.0149
  -6.500  -0.6841   0.01101   0.00477  -0.0043   0.8855   0.0155
  -6.250  -0.6589   0.01080   0.00448  -0.0039   0.8693   0.0162
  -6.000  -0.6334   0.01059   0.00420  -0.0035   0.8545   0.0170
  -5.750  -0.6081   0.01035   0.00391  -0.0032   0.8408   0.0189
  -5.500  -0.5821   0.01015   0.00367  -0.0029   0.8280   0.0209
  -5.250  -0.5558   0.00997   0.00344  -0.0028   0.8164   0.0231
  -5.000  -0.5297   0.00976   0.00322  -0.0026   0.8057   0.0269
  -4.750  -0.5032   0.00959   0.00302  -0.0024   0.7955   0.0309
  -4.500  -0.4767   0.00940   0.00282  -0.0023   0.7857   0.0371
  -4.250  -0.4503   0.00919   0.00263  -0.0022   0.7764   0.0469
  -4.000  -0.4238   0.00900   0.00245  -0.0020   0.7670   0.0588
  -3.750  -0.3973   0.00878   0.00228  -0.0019   0.7585   0.0755
  -3.500  -0.3714   0.00851   0.00209  -0.0017   0.7504   0.1042
  -3.250  -0.3465   0.00806   0.00186  -0.0015   0.7419   0.1648
  -3.000  -0.3229   0.00750   0.00162  -0.0010   0.7337   0.2523
  -2.750  -0.2981   0.00706   0.00142  -0.0007   0.7252   0.3232
  -2.500  -0.2742   0.00656   0.00122  -0.0002   0.7176   0.4116
  -2.250  -0.2486   0.00625   0.00112   0.0000   0.7099   0.4760
  -2.000  -0.2219   0.00609   0.00106   0.0002   0.7028   0.5118
  -1.750  -0.1951   0.00594   0.00101   0.0003   0.6950   0.5471
  -1.500  -0.1680   0.00584   0.00097   0.0004   0.6875   0.5755
  -1.250  -0.1404   0.00578   0.00095   0.0004   0.6795   0.5943
  -1.000  -0.1126   0.00574   0.00092   0.0004   0.6727   0.6095
  -0.750  -0.0847   0.00570   0.00091   0.0003   0.6655   0.6220
  -0.250  -0.0282   0.00569   0.00088   0.0001   0.6513   0.6374
   0.000   0.0000   0.00570   0.00088   0.0000   0.6442   0.6442
   0.250   0.0283   0.00569   0.00088  -0.0001   0.6374   0.6513
   0.750   0.0847   0.00570   0.00091  -0.0003   0.6221   0.6655
   1.000   0.1127   0.00574   0.00092  -0.0004   0.6095   0.6727
   1.250   0.1404   0.00578   0.00095  -0.0004   0.5942   0.6795
   1.500   0.1681   0.00584   0.00097  -0.0004   0.5755   0.6875
   1.750   0.1951   0.00594   0.00101  -0.0003   0.5469   0.6949
   2.000   0.2219   0.00610   0.00106  -0.0002   0.5115   0.7028
   2.250   0.2487   0.00625   0.00112   0.0000   0.4759   0.7099
   2.500   0.2741   0.00657   0.00122   0.0002   0.4098   0.7176
   2.750   0.2982   0.00706   0.00142   0.0007   0.3233   0.7252
   3.000   0.3229   0.00750   0.00162   0.0010   0.2527   0.7338
   3.250   0.3465   0.00807   0.00186   0.0015   0.1641   0.7420
   3.500   0.3714   0.00851   0.00209   0.0017   0.1044   0.7504
   3.750   0.3973   0.00878   0.00228   0.0019   0.0757   0.7585
   4.000   0.4239   0.00900   0.00245   0.0020   0.0587   0.7670
   4.250   0.4503   0.00919   0.00263   0.0022   0.0469   0.7764
   4.500   0.4768   0.00940   0.00282   0.0023   0.0371   0.7857
   4.750   0.5033   0.00959   0.00302   0.0024   0.0309   0.7955
   5.000   0.5297   0.00976   0.00322   0.0026   0.0269   0.8057
   5.250   0.5559   0.00997   0.00344   0.0028   0.0231   0.8165
   5.500   0.5821   0.01015   0.00367   0.0029   0.0209   0.8280
   5.750   0.6081   0.01035   0.00391   0.0032   0.0189   0.8407
   6.000   0.6335   0.01059   0.00420   0.0035   0.0170   0.8544
   6.250   0.6590   0.01080   0.00448   0.0039   0.0162   0.8692
   6.500   0.6841   0.01101   0.00477   0.0043   0.0155   0.8857
   6.750   0.7088   0.01124   0.00508   0.0048   0.0149   0.9029
   7.000   0.7332   0.01150   0.00541   0.0054   0.0143   0.9214
   7.250   0.7578   0.01180   0.00577   0.0058   0.0137   0.9403
   7.500   0.7841   0.01221   0.00623   0.0059   0.0130   0.9576
   7.750   0.8130   0.01264   0.00670   0.0053   0.0125   0.9713
   8.000   0.8435   0.01303   0.00714   0.0043   0.0123   0.9813
   8.250   0.8739   0.01347   0.00762   0.0033   0.0120   0.9894
   8.500   0.9038   0.01394   0.00814   0.0024   0.0117   0.9961
   8.750   0.9313   0.01441   0.00866   0.0020   0.0114   1.0000
   9.000   0.9518   0.01486   0.00914   0.0031   0.0112   1.0000
   9.250   0.9729   0.01531   0.00963   0.0040   0.0109   1.0000
   9.500   0.9944   0.01575   0.01010   0.0049   0.0107   1.0000
   9.750   1.0159   0.01621   0.01060   0.0057   0.0104   1.0000
  10.000   1.0367   0.01674   0.01117   0.0065   0.0101   1.0000
  10.250   1.0567   0.01736   0.01184   0.0075   0.0099   1.0000
  10.500   1.0752   0.01813   0.01267   0.0086   0.0097   1.0000
  10.750   1.0913   0.01912   0.01375   0.0100   0.0094   1.0000
  11.000   1.1109   0.01973   0.01443   0.0108   0.0093   1.0000
  11.250   1.1301   0.02036   0.01514   0.0118   0.0092   1.0000
  11.500   1.1488   0.02100   0.01585   0.0127   0.0091   1.0000
  11.750   1.1669   0.02165   0.01657   0.0137   0.0089   1.0000
  12.000   1.1828   0.02234   0.01734   0.0151   0.0087   1.0000
  12.250   1.1973   0.02309   0.01816   0.0165   0.0085   1.0000
  12.500   1.2107   0.02393   0.01908   0.0180   0.0084   1.0000
  12.750   1.2231   0.02485   0.02009   0.0195   0.0082   1.0000
  13.000   1.2349   0.02584   0.02117   0.0208   0.0081   1.0000
  13.250   1.2461   0.02689   0.02231   0.0220   0.0079   1.0000
  13.500   1.2568   0.02803   0.02353   0.0231   0.0078   1.0000
  13.750   1.2664   0.02928   0.02487   0.0241   0.0077   1.0000
  14.000   1.2755   0.03064   0.02631   0.0249   0.0076   1.0000
  14.250   1.2837   0.03213   0.02789   0.0256   0.0075   1.0000
  14.500   1.2905   0.03381   0.02965   0.0261   0.0074   1.0000
  14.750   1.2955   0.03573   0.03166   0.0265   0.0072   1.0000
  15.000   1.2985   0.03793   0.03397   0.0267   0.0071   1.0000
  15.250   1.2978   0.04061   0.03676   0.0267   0.0070   1.0000
  15.500   1.2931   0.04388   0.04016   0.0264   0.0069   1.0000
  15.750   1.2829   0.04795   0.04438   0.0256   0.0068   1.0000
  16.000   1.2790   0.05145   0.04802   0.0246   0.0068   1.0000
  16.250   1.2734   0.05530   0.05199   0.0233   0.0067   1.0000
  16.500   1.2649   0.05973   0.05657   0.0216   0.0067   1.0000
  16.750   1.2538   0.06478   0.06175   0.0193   0.0067   1.0000
  17.000   1.2393   0.07068   0.06780   0.0164   0.0066   1.0000
  17.250   1.2183   0.07812   0.07540   0.0124   0.0066   1.0000
  17.500   1.1893   0.08755   0.08500   0.0071   0.0067   1.0000
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