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NASA/LANGLEY 64-012 AIRFOIL (n64012-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NASA/LANGLEY 64-012 AIRFOIL (n64012-il)
Reynolds number: 1,000,000
Max Cl/Cd: 65.43 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012-il-1000000-n5.txt
Download as CSV file: xf-n64012-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA/LANGLEY 64-012 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
  ------ -------- --------- --------- -------- -------- --------
 -18.250  -1.1219   0.11239   0.11018   0.0097   1.0000   0.0071
 -18.000  -1.1586   0.09946   0.09708   0.0018   1.0000   0.0071
 -17.750  -1.1985   0.08676   0.08413  -0.0060   1.0000   0.0070
 -17.500  -1.2221   0.07812   0.07532  -0.0112   1.0000   0.0070
 -17.250  -1.2382   0.07141   0.06847  -0.0150   1.0000   0.0070
 -17.000  -1.2551   0.06505   0.06196  -0.0183   1.0000   0.0070
 -16.750  -1.2634   0.06035   0.05715  -0.0206   1.0000   0.0071
 -16.500  -1.2693   0.05623   0.05293  -0.0223   1.0000   0.0072
 -16.250  -1.2742   0.05249   0.04909  -0.0237   1.0000   0.0073
 -16.000  -1.2776   0.04909   0.04558  -0.0248   1.0000   0.0074
 -15.750  -1.2798   0.04599   0.04238  -0.0255   1.0000   0.0074
 -15.500  -1.2791   0.04334   0.03963  -0.0260   1.0000   0.0075
 -15.250  -1.2805   0.04056   0.03672  -0.0262   1.0000   0.0076
 -15.000  -1.2770   0.03841   0.03449  -0.0263   1.0000   0.0076
 -14.750  -1.2744   0.03625   0.03222  -0.0261   1.0000   0.0077
 -14.500  -1.2689   0.03445   0.03035  -0.0257   1.0000   0.0079
 -14.250  -1.2642   0.03264   0.02843  -0.0252   1.0000   0.0079
 -14.000  -1.2577   0.03106   0.02676  -0.0245   1.0000   0.0081
 -13.750  -1.2503   0.02962   0.02523  -0.0236   1.0000   0.0082
 -13.500  -1.2432   0.02820   0.02372  -0.0226   1.0000   0.0084
 -13.250  -1.2353   0.02691   0.02234  -0.0215   1.0000   0.0085
 -13.000  -1.2263   0.02575   0.02109  -0.0202   1.0000   0.0086
 -12.750  -1.2153   0.02480   0.02005  -0.0190   1.0000   0.0088
 -12.500  -1.2038   0.02392   0.01910  -0.0176   1.0000   0.0089
 -12.250  -1.1926   0.02308   0.01817  -0.0160   1.0000   0.0090
 -12.000  -1.1811   0.02231   0.01733  -0.0143   1.0000   0.0091
 -11.750  -1.1686   0.02163   0.01658  -0.0125   1.0000   0.0092
 -11.500  -1.1585   0.02062   0.01548  -0.0104   1.0000   0.0094
 -11.250  -1.1443   0.01967   0.01446  -0.0090   1.0000   0.0096
 -11.000  -1.1268   0.01895   0.01368  -0.0079   1.0000   0.0098
 -10.750  -1.1081   0.01827   0.01294  -0.0070   1.0000   0.0100
 -10.500  -1.0880   0.01768   0.01230  -0.0062   1.0000   0.0102
 -10.250  -1.0670   0.01712   0.01170  -0.0055   1.0000   0.0104
 -10.000  -1.0451   0.01662   0.01117  -0.0049   1.0000   0.0107
  -9.750  -1.0228   0.01613   0.01065  -0.0044   0.9911   0.0110
  -9.500  -0.9909   0.01559   0.01002  -0.0059   0.9537   0.0113
  -9.250  -0.9693   0.01515   0.00947  -0.0051   0.9298   0.0115
  -9.000  -0.9484   0.01473   0.00897  -0.0041   0.9115   0.0117
  -8.750  -0.9267   0.01434   0.00848  -0.0032   0.8959   0.0119
  -8.500  -0.9040   0.01397   0.00803  -0.0025   0.8824   0.0122
  -8.250  -0.8808   0.01362   0.00759  -0.0019   0.8700   0.0123
  -8.000  -0.8583   0.01312   0.00701  -0.0011   0.8581   0.0130
  -7.750  -0.8343   0.01275   0.00659  -0.0007   0.8469   0.0136
  -7.500  -0.8096   0.01243   0.00622  -0.0003   0.8365   0.0141
  -7.250  -0.7846   0.01213   0.00587   0.0000   0.8267   0.0146
  -7.000  -0.7593   0.01184   0.00551   0.0003   0.8168   0.0152
  -6.750  -0.7336   0.01157   0.00519   0.0005   0.8078   0.0157
  -6.250  -0.6818   0.01102   0.00455   0.0009   0.7899   0.0176
  -6.000  -0.6556   0.01078   0.00427   0.0010   0.7814   0.0191
  -5.750  -0.6290   0.01056   0.00402   0.0011   0.7725   0.0205
  -5.500  -0.6022   0.01037   0.00378   0.0012   0.7643   0.0218
  -5.250  -0.5756   0.01013   0.00353   0.0013   0.7560   0.0242
  -5.000  -0.5486   0.00994   0.00331   0.0013   0.7486   0.0265
  -4.750  -0.5213   0.00977   0.00311   0.0013   0.7406   0.0288
  -4.500  -0.4943   0.00956   0.00290   0.0013   0.7332   0.0329
  -4.250  -0.4669   0.00940   0.00271   0.0013   0.7250   0.0366
  -4.000  -0.4397   0.00919   0.00252   0.0013   0.7173   0.0449
  -3.750  -0.4127   0.00895   0.00233   0.0013   0.7092   0.0621
  -3.500  -0.3861   0.00862   0.00212   0.0013   0.7021   0.0964
  -3.250  -0.3598   0.00822   0.00190   0.0013   0.6947   0.1450
  -3.000  -0.3338   0.00777   0.00168   0.0013   0.6880   0.2111
  -2.750  -0.3081   0.00724   0.00144   0.0014   0.6809   0.2924
  -2.500  -0.2821   0.00676   0.00123   0.0014   0.6744   0.3690
  -2.250  -0.2557   0.00635   0.00109   0.0014   0.6676   0.4501
  -2.000  -0.2282   0.00617   0.00102   0.0013   0.6608   0.4926
  -1.750  -0.2002   0.00603   0.00098   0.0012   0.6538   0.5261
  -1.500  -0.1724   0.00590   0.00095   0.0012   0.6470   0.5607
  -1.250  -0.1439   0.00585   0.00093   0.0010   0.6409   0.5766
  -1.000  -0.1151   0.00584   0.00090   0.0008   0.6346   0.5848
  -0.750  -0.0864   0.00582   0.00088   0.0006   0.6290   0.5921
  -0.500  -0.0576   0.00581   0.00087   0.0004   0.6231   0.5993
  -0.250  -0.0288   0.00580   0.00086   0.0002   0.6174   0.6056
   0.000   0.0000   0.00579   0.00086   0.0000   0.6119   0.6118
   0.250   0.0289   0.00580   0.00086  -0.0002   0.6056   0.6173
   0.500   0.0576   0.00581   0.00087  -0.0004   0.5992   0.6231
   0.750   0.0865   0.00582   0.00088  -0.0006   0.5921   0.6290
   1.000   0.1152   0.00584   0.00090  -0.0008   0.5848   0.6346
   1.250   0.1440   0.00585   0.00093  -0.0010   0.5766   0.6409
   1.500   0.1725   0.00590   0.00095  -0.0012   0.5606   0.6470
   1.750   0.2003   0.00603   0.00098  -0.0012   0.5262   0.6538
   2.000   0.2282   0.00617   0.00102  -0.0013   0.4926   0.6608
   2.250   0.2558   0.00636   0.00109  -0.0014   0.4498   0.6675
   2.500   0.2821   0.00677   0.00123  -0.0014   0.3684   0.6744
   2.750   0.3081   0.00724   0.00144  -0.0014   0.2917   0.6809
   3.000   0.3338   0.00777   0.00168  -0.0014   0.2109   0.6880
   3.250   0.3599   0.00822   0.00190  -0.0013   0.1450   0.6947
   3.500   0.3862   0.00862   0.00212  -0.0013   0.0964   0.7021
   3.750   0.4127   0.00895   0.00233  -0.0013   0.0616   0.7092
   4.000   0.4397   0.00919   0.00252  -0.0013   0.0450   0.7173
   4.250   0.4669   0.00940   0.00271  -0.0013   0.0365   0.7249
   4.500   0.4943   0.00956   0.00290  -0.0013   0.0328   0.7332
   4.750   0.5214   0.00977   0.00311  -0.0013   0.0288   0.7406
   5.000   0.5486   0.00994   0.00331  -0.0013   0.0265   0.7486
   5.250   0.5756   0.01013   0.00353  -0.0013   0.0242   0.7560
   5.500   0.6023   0.01037   0.00378  -0.0012   0.0217   0.7644
   5.750   0.6291   0.01056   0.00402  -0.0011   0.0204   0.7726
   6.000   0.6557   0.01078   0.00427  -0.0011   0.0190   0.7815
   6.250   0.6819   0.01102   0.00455  -0.0009   0.0177   0.7899
   6.750   0.7336   0.01157   0.00519  -0.0005   0.0157   0.8080
   7.000   0.7593   0.01185   0.00551  -0.0003   0.0152   0.8168
   7.250   0.7847   0.01213   0.00587   0.0000   0.0146   0.8268
   7.500   0.8097   0.01243   0.00622   0.0003   0.0140   0.8366
   7.750   0.8343   0.01276   0.00659   0.0007   0.0135   0.8468
   8.000   0.8584   0.01312   0.00701   0.0011   0.0129   0.8581
   8.250   0.8808   0.01362   0.00759   0.0019   0.0123   0.8699
   8.500   0.9042   0.01396   0.00802   0.0025   0.0121   0.8823
   8.750   0.9268   0.01434   0.00848   0.0032   0.0120   0.8959
   9.000   0.9484   0.01474   0.00898   0.0041   0.0117   0.9117
   9.250   0.9693   0.01516   0.00949   0.0051   0.0115   0.9297
   9.500   0.9909   0.01559   0.01003   0.0059   0.0113   0.9536
   9.750   1.0228   0.01614   0.01065   0.0044   0.0110   0.9903
  10.000   1.0451   0.01664   0.01119   0.0049   0.0107   1.0000
  10.250   1.0669   0.01715   0.01174   0.0055   0.0104   1.0000
  10.500   1.0882   0.01767   0.01230   0.0061   0.0102   1.0000
  10.750   1.1082   0.01828   0.01295   0.0069   0.0100   1.0000
  11.000   1.1270   0.01896   0.01369   0.0079   0.0098   1.0000
  11.250   1.1444   0.01970   0.01449   0.0089   0.0096   1.0000
  11.500   1.1585   0.02065   0.01551   0.0104   0.0094   1.0000
  11.750   1.1684   0.02168   0.01663   0.0125   0.0092   1.0000
  12.000   1.1810   0.02235   0.01737   0.0143   0.0091   1.0000
  12.250   1.1927   0.02310   0.01820   0.0160   0.0090   1.0000
  12.500   1.2039   0.02395   0.01913   0.0176   0.0089   1.0000
  12.750   1.2153   0.02483   0.02009   0.0189   0.0088   1.0000
  13.000   1.2264   0.02578   0.02112   0.0202   0.0086   1.0000
  13.250   1.2348   0.02698   0.02242   0.0215   0.0085   1.0000
  13.500   1.2437   0.02819   0.02372   0.0226   0.0083   1.0000
  13.750   1.2498   0.02970   0.02532   0.0236   0.0083   1.0000
  14.000   1.2577   0.03110   0.02681   0.0244   0.0081   1.0000
  14.250   1.2630   0.03279   0.02860   0.0251   0.0080   1.0000
  14.500   1.2707   0.03431   0.03020   0.0256   0.0078   1.0000
  14.750   1.2736   0.03637   0.03236   0.0260   0.0078   1.0000
  15.000   1.2775   0.03841   0.03449   0.0262   0.0077   1.0000
  15.250   1.2825   0.04039   0.03655   0.0262   0.0075   1.0000
  15.500   1.2813   0.04314   0.03942   0.0259   0.0075   1.0000
  15.750   1.2822   0.04576   0.04214   0.0255   0.0074   1.0000
  16.000   1.2777   0.04914   0.04564   0.0247   0.0073   1.0000
  16.250   1.2775   0.05213   0.04871   0.0237   0.0072   1.0000
  16.500   1.2705   0.05614   0.05283   0.0223   0.0072   1.0000
  16.750   1.2649   0.06020   0.05699   0.0205   0.0071   1.0000
  17.000   1.2488   0.06610   0.06306   0.0177   0.0071   1.0000
  17.250   1.2429   0.07074   0.06778   0.0152   0.0070   1.0000
  17.500   1.2204   0.07855   0.07576   0.0107   0.0070   1.0000
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