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NACA 64-012A AIRFOIL (n64012a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 64-012A AIRFOIL (n64012a-il)
Reynolds number: 100,000
Max Cl/Cd: 35.53 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-n64012a-il-100000-n5.txt
Download as CSV file: xf-n64012a-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.7268   0.10113   0.09592  -0.0123   1.0000   0.0288
 -12.250  -0.7458   0.09231   0.08705  -0.0181   1.0000   0.0285
 -12.000  -0.7676   0.08429   0.07894  -0.0235   1.0000   0.0283
 -11.750  -0.7898   0.07741   0.07193  -0.0277   1.0000   0.0281
 -11.500  -0.8112   0.07158   0.06595  -0.0306   1.0000   0.0280
 -11.250  -0.8315   0.06663   0.06080  -0.0320   1.0000   0.0279
 -11.000  -0.8500   0.06239   0.05635  -0.0321   1.0000   0.0279
 -10.750  -0.8668   0.05869   0.05241  -0.0309   1.0000   0.0279
 -10.500  -0.8813   0.05541   0.04885  -0.0285   1.0000   0.0281
 -10.250  -0.8906   0.05215   0.04521  -0.0261   1.0000   0.0285
  -9.750  -0.8905   0.04606   0.03850  -0.0222   1.0000   0.0297
  -9.500  -0.8817   0.04367   0.03592  -0.0208   1.0000   0.0304
  -9.250  -0.8714   0.04122   0.03320  -0.0193   1.0000   0.0309
  -9.000  -0.8587   0.03882   0.03048  -0.0179   1.0000   0.0314
  -8.750  -0.8436   0.03660   0.02797  -0.0165   1.0000   0.0320
  -8.500  -0.8263   0.03453   0.02564  -0.0154   1.0000   0.0328
  -8.250  -0.8071   0.03261   0.02348  -0.0143   1.0000   0.0337
  -8.000  -0.7868   0.03091   0.02156  -0.0133   1.0000   0.0350
  -7.750  -0.7660   0.02953   0.01993  -0.0123   1.0000   0.0369
  -7.500  -0.7449   0.02794   0.01821  -0.0114   1.0000   0.0386
  -7.250  -0.7249   0.02657   0.01685  -0.0105   1.0000   0.0402
  -7.000  -0.7054   0.02540   0.01565  -0.0093   1.0000   0.0420
  -6.750  -0.6868   0.02432   0.01452  -0.0079   1.0000   0.0441
  -6.500  -0.6690   0.02340   0.01350  -0.0063   1.0000   0.0471
  -6.250  -0.6541   0.02240   0.01252  -0.0044   1.0000   0.0507
  -6.000  -0.6389   0.02161   0.01172  -0.0025   1.0000   0.0552
  -5.750  -0.6238   0.02087   0.01090  -0.0003   1.0000   0.0598
  -5.500  -0.6105   0.02005   0.01014   0.0018   1.0000   0.0673
  -5.250  -0.5969   0.01932   0.00944   0.0040   1.0000   0.0776
  -5.000  -0.5837   0.01859   0.00877   0.0062   1.0000   0.0941
  -4.500  -0.5468   0.01602   0.00727   0.0073   0.9920   0.2739
  -4.250  -0.5220   0.01469   0.00707   0.0070   0.9826   0.4919
  -4.000  -0.4888   0.01451   0.00707   0.0060   0.9743   0.5736
  -3.750  -0.4561   0.01449   0.00709   0.0052   0.9650   0.6206
  -3.500  -0.4238   0.01458   0.00721   0.0047   0.9563   0.6624
  -3.250  -0.3912   0.01479   0.00744   0.0045   0.9482   0.6989
  -3.000  -0.3610   0.01483   0.00741   0.0043   0.9379   0.7205
  -2.750  -0.3271   0.01481   0.00731   0.0033   0.9298   0.7322
  -2.500  -0.2949   0.01475   0.00715   0.0025   0.9203   0.7419
  -2.250  -0.2643   0.01466   0.00696   0.0019   0.9103   0.7518
  -2.000  -0.2309   0.01458   0.00682   0.0009   0.9024   0.7594
  -1.750  -0.2025   0.01450   0.00665   0.0008   0.8915   0.7681
  -1.500  -0.1725   0.01444   0.00654   0.0005   0.8821   0.7761
  -1.250  -0.1422   0.01437   0.00641   0.0001   0.8733   0.7842
  -1.000  -0.1142   0.01433   0.00633   0.0001   0.8630   0.7928
  -0.750  -0.0847   0.01429   0.00626  -0.0001   0.8545   0.8008
  -0.500  -0.0570   0.01425   0.00619   0.0000   0.8449   0.8101
  -0.250  -0.0283   0.01425   0.00619   0.0000   0.8357   0.8179
   0.000   0.0000   0.01422   0.00613   0.0000   0.8275   0.8275
   0.250   0.0283   0.01425   0.00619   0.0000   0.8179   0.8357
   0.500   0.0570   0.01425   0.00619   0.0000   0.8101   0.8448
   0.750   0.0847   0.01429   0.00626   0.0001   0.8008   0.8545
   1.000   0.1143   0.01433   0.00633  -0.0001   0.7928   0.8630
   1.250   0.1422   0.01437   0.00641  -0.0001   0.7842   0.8733
   1.500   0.1725   0.01444   0.00654  -0.0005   0.7761   0.8821
   1.750   0.2025   0.01450   0.00665  -0.0008   0.7681   0.8915
   2.000   0.2309   0.01458   0.00682  -0.0009   0.7594   0.9024
   2.250   0.2643   0.01466   0.00696  -0.0019   0.7518   0.9103
   2.500   0.2949   0.01475   0.00715  -0.0025   0.7419   0.9203
   2.750   0.3271   0.01481   0.00731  -0.0033   0.7322   0.9298
   3.000   0.3610   0.01483   0.00741  -0.0043   0.7205   0.9379
   3.250   0.3912   0.01479   0.00744  -0.0045   0.6989   0.9482
   3.500   0.4238   0.01458   0.00721  -0.0047   0.6624   0.9563
   3.750   0.4561   0.01449   0.00709  -0.0052   0.6205   0.9650
   4.000   0.4888   0.01451   0.00707  -0.0060   0.5737   0.9743
   4.250   0.5220   0.01469   0.00707  -0.0070   0.4920   0.9826
   4.500   0.5468   0.01602   0.00727  -0.0073   0.2740   0.9920
   5.000   0.5837   0.01859   0.00877  -0.0062   0.0941   1.0000
   5.250   0.5969   0.01932   0.00944  -0.0040   0.0776   1.0000
   5.500   0.6105   0.02005   0.01014  -0.0018   0.0673   1.0000
   5.750   0.6238   0.02086   0.01089   0.0003   0.0598   1.0000
   6.000   0.6389   0.02160   0.01172   0.0025   0.0552   1.0000
   6.250   0.6541   0.02240   0.01252   0.0044   0.0507   1.0000
   6.500   0.6690   0.02340   0.01350   0.0063   0.0471   1.0000
   6.750   0.6868   0.02431   0.01452   0.0079   0.0441   1.0000
   7.000   0.7054   0.02540   0.01565   0.0093   0.0420   1.0000
   7.250   0.7249   0.02657   0.01685   0.0105   0.0402   1.0000
   7.500   0.7449   0.02794   0.01821   0.0114   0.0386   1.0000
   7.750   0.7660   0.02953   0.01993   0.0123   0.0369   1.0000
   8.000   0.7869   0.03091   0.02156   0.0133   0.0350   1.0000
   8.250   0.8072   0.03261   0.02348   0.0143   0.0337   1.0000
   8.500   0.8264   0.03453   0.02565   0.0153   0.0328   1.0000
   8.750   0.8437   0.03660   0.02798   0.0165   0.0320   1.0000
   9.000   0.8588   0.03883   0.03049   0.0178   0.0314   1.0000
   9.250   0.8715   0.04123   0.03320   0.0193   0.0309   1.0000
   9.500   0.8819   0.04368   0.03592   0.0208   0.0304   1.0000
   9.750   0.8907   0.04606   0.03850   0.0222   0.0297   1.0000
  10.250   0.8908   0.05217   0.04523   0.0260   0.0285   1.0000
  10.500   0.8815   0.05543   0.04887   0.0284   0.0281   1.0000
  10.750   0.8670   0.05872   0.05245   0.0308   0.0279   1.0000
  11.000   0.8503   0.06243   0.05639   0.0320   0.0279   1.0000
  11.250   0.8318   0.06669   0.06087   0.0319   0.0279   1.0000
  11.500   0.8116   0.07166   0.06602   0.0304   0.0280   1.0000
  11.750   0.7903   0.07749   0.07202   0.0275   0.0281   1.0000
  12.000   0.7681   0.08440   0.07905   0.0233   0.0283   1.0000
  12.250   0.7463   0.09246   0.08720   0.0178   0.0285   1.0000
  12.500   0.7273   0.10136   0.09615   0.0120   0.0288   1.0000
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