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NACA 64A-010 10.0% (naca64a010-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 64A-010 10.0% (naca64a010-il)
Reynolds number: 200,000
Max Cl/Cd: 36.91 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca64a010-il-200000-n5.txt
Download as CSV file: xf-naca64a010-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A-010 10.0%                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.5692   0.08747   0.08401  -0.0172   1.0000   0.0159
 -11.000  -0.6124   0.07026   0.06681  -0.0263   1.0000   0.0148
 -10.750  -0.6871   0.05259   0.04882  -0.0354   1.0000   0.0139
 -10.500  -0.7932   0.05622   0.05191  -0.0350   1.0000   0.0133
 -10.250  -0.8117   0.05266   0.04815  -0.0334   1.0000   0.0133
 -10.000  -0.8284   0.04954   0.04483  -0.0302   1.0000   0.0133
  -9.750  -0.8416   0.04598   0.04100  -0.0272   1.0000   0.0134
  -9.500  -0.8476   0.04265   0.03740  -0.0245   1.0000   0.0136
  -9.250  -0.8458   0.04005   0.03457  -0.0223   1.0000   0.0138
  -9.000  -0.8374   0.03839   0.03276  -0.0206   1.0000   0.0143
  -8.750  -0.8278   0.03656   0.03073  -0.0188   1.0000   0.0147
  -8.500  -0.8161   0.03486   0.02883  -0.0171   1.0000   0.0154
  -8.250  -0.8049   0.03262   0.02628  -0.0150   1.0000   0.0161
  -8.000  -0.7925   0.03008   0.02335  -0.0129   1.0000   0.0165
  -7.750  -0.7774   0.02783   0.02074  -0.0110   1.0000   0.0169
  -7.500  -0.7602   0.02591   0.01850  -0.0093   1.0000   0.0175
  -7.250  -0.7414   0.02429   0.01662  -0.0078   1.0000   0.0181
  -7.000  -0.7218   0.02298   0.01510  -0.0064   1.0000   0.0186
  -6.750  -0.7038   0.02151   0.01356  -0.0050   1.0000   0.0199
  -6.500  -0.6847   0.02067   0.01268  -0.0037   1.0000   0.0210
  -6.250  -0.6656   0.01978   0.01170  -0.0022   1.0000   0.0222
  -6.000  -0.6470   0.01883   0.01068  -0.0006   1.0000   0.0232
  -5.750  -0.6291   0.01797   0.00974   0.0012   1.0000   0.0244
  -5.500  -0.6116   0.01724   0.00893   0.0030   1.0000   0.0254
  -5.250  -0.5962   0.01639   0.00806   0.0051   1.0000   0.0272
  -5.000  -0.5795   0.01583   0.00750   0.0070   1.0000   0.0300
  -4.750  -0.5536   0.01525   0.00684   0.0069   0.9969   0.0331
  -4.500  -0.5209   0.01455   0.00607   0.0055   0.9903   0.0370
  -4.250  -0.4878   0.01400   0.00548   0.0040   0.9837   0.0451
  -4.000  -0.4549   0.01341   0.00492   0.0025   0.9769   0.0604
  -3.750  -0.4247   0.01269   0.00442   0.0015   0.9686   0.1034
  -3.500  -0.3980   0.01150   0.00388   0.0007   0.9599   0.2434
  -3.250  -0.3749   0.01016   0.00351   0.0007   0.9505   0.4614
  -3.000  -0.3480   0.00972   0.00340   0.0008   0.9402   0.5595
  -2.750  -0.3185   0.00949   0.00333   0.0006   0.9307   0.6168
  -2.500  -0.2880   0.00932   0.00333   0.0003   0.9223   0.6713
  -2.250  -0.2601   0.00923   0.00335   0.0007   0.9115   0.7130
  -2.000  -0.2301   0.00917   0.00326   0.0004   0.9011   0.7333
  -1.750  -0.1990   0.00910   0.00315  -0.0001   0.8913   0.7459
  -1.500  -0.1688   0.00904   0.00305  -0.0004   0.8806   0.7557
  -1.250  -0.1399   0.00899   0.00296  -0.0005   0.8692   0.7654
  -1.000  -0.1114   0.00895   0.00288  -0.0006   0.8582   0.7757
  -0.750  -0.0828   0.00892   0.00282  -0.0006   0.8477   0.7850
  -0.500  -0.0550   0.00890   0.00278  -0.0004   0.8368   0.7950
  -0.250  -0.0278   0.00889   0.00275  -0.0002   0.8258   0.8058
   0.000   0.0000   0.00888   0.00275   0.0000   0.8155   0.8155
   0.250   0.0278   0.00889   0.00275   0.0002   0.8057   0.8257
   0.500   0.0550   0.00890   0.00278   0.0004   0.7950   0.8368
   0.750   0.0828   0.00892   0.00282   0.0006   0.7850   0.8477
   1.000   0.1114   0.00895   0.00288   0.0006   0.7757   0.8582
   1.250   0.1399   0.00899   0.00295   0.0005   0.7654   0.8692
   1.500   0.1688   0.00904   0.00305   0.0004   0.7557   0.8806
   1.750   0.1990   0.00910   0.00315   0.0001   0.7459   0.8913
   2.000   0.2301   0.00917   0.00326  -0.0004   0.7333   0.9011
   2.250   0.2602   0.00924   0.00336  -0.0007   0.7131   0.9115
   2.500   0.2880   0.00932   0.00333  -0.0003   0.6716   0.9223
   2.750   0.3185   0.00949   0.00333  -0.0006   0.6171   0.9307
   3.000   0.3481   0.00972   0.00340  -0.0009   0.5599   0.9402
   3.250   0.3750   0.01016   0.00351  -0.0007   0.4628   0.9505
   3.500   0.3980   0.01150   0.00388  -0.0007   0.2438   0.9598
   3.750   0.4246   0.01270   0.00442  -0.0015   0.1023   0.9686
   4.000   0.4549   0.01341   0.00492  -0.0025   0.0606   0.9768
   4.250   0.4877   0.01400   0.00548  -0.0040   0.0449   0.9837
   4.500   0.5209   0.01455   0.00607  -0.0055   0.0371   0.9902
   4.750   0.5535   0.01525   0.00684  -0.0069   0.0330   0.9969
   5.000   0.5797   0.01582   0.00749  -0.0070   0.0297   1.0000
   5.250   0.5961   0.01640   0.00807  -0.0051   0.0269   1.0000
   5.500   0.6115   0.01725   0.00894  -0.0030   0.0254   1.0000
   5.750   0.6291   0.01798   0.00975  -0.0012   0.0243   1.0000
   6.000   0.6470   0.01884   0.01068   0.0006   0.0232   1.0000
   6.250   0.6656   0.01978   0.01170   0.0022   0.0222   1.0000
   6.500   0.6847   0.02068   0.01270   0.0037   0.0210   1.0000
   6.750   0.7037   0.02146   0.01350   0.0050   0.0197   1.0000
   7.000   0.7218   0.02300   0.01511   0.0064   0.0185   1.0000
   7.250   0.7414   0.02428   0.01661   0.0078   0.0180   1.0000
   7.500   0.7601   0.02592   0.01851   0.0093   0.0174   1.0000
   7.750   0.7774   0.02782   0.02072   0.0110   0.0170   1.0000
   8.000   0.7925   0.03009   0.02336   0.0129   0.0165   1.0000
   8.250   0.8047   0.03267   0.02633   0.0151   0.0161   1.0000
   8.500   0.8157   0.03500   0.02898   0.0171   0.0155   1.0000
   8.750   0.8271   0.03674   0.03093   0.0189   0.0148   1.0000
   9.000   0.8375   0.03838   0.03275   0.0206   0.0143   1.0000
   9.250   0.8467   0.03987   0.03437   0.0222   0.0138   1.0000
   9.500   0.8474   0.04267   0.03742   0.0245   0.0135   1.0000
   9.750   0.8428   0.04590   0.04094   0.0271   0.0135   1.0000
  10.000   0.8301   0.04943   0.04473   0.0301   0.0133   1.0000
  10.250   0.8124   0.05262   0.04811   0.0333   0.0133   1.0000
  10.500   0.7939   0.05619   0.05188   0.0349   0.0133   1.0000
  10.750   0.7721   0.06071   0.05659   0.0346   0.0133   1.0000
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