Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 64A410 (naca64a410-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.63 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca64a410-il-1000000.txt
Download as CSV file: xf-naca64a410-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 64A410                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3298   0.09418   0.09264  -0.0417   1.0000   0.0114
 -10.250  -0.3324   0.09049   0.08897  -0.0422   1.0000   0.0117
 -10.000  -0.4436   0.09566   0.09403  -0.0368   1.0000   0.0105
  -9.750  -0.4400   0.09225   0.09063  -0.0385   1.0000   0.0107
  -9.500  -0.4373   0.08862   0.08702  -0.0404   1.0000   0.0110
  -9.250  -0.4365   0.08474   0.08316  -0.0425   1.0000   0.0113
  -9.000  -0.4411   0.08106   0.07951  -0.0437   1.0000   0.0117
  -8.000  -0.4543   0.02912   0.02633  -0.0893   0.9572   0.0095
  -7.750  -0.4453   0.02309   0.01964  -0.0888   0.9495   0.0097
  -7.500  -0.4339   0.01792   0.01378  -0.0880   0.9433   0.0104
  -7.250  -0.4097   0.01712   0.01287  -0.0878   0.9390   0.0108
  -7.000  -0.3852   0.01631   0.01194  -0.0876   0.9344   0.0112
  -6.750  -0.3608   0.01536   0.01082  -0.0872   0.9302   0.0117
  -6.500  -0.3359   0.01432   0.00960  -0.0869   0.9262   0.0122
  -6.250  -0.3107   0.01340   0.00854  -0.0866   0.9217   0.0127
  -6.000  -0.2849   0.01273   0.00776  -0.0863   0.9174   0.0132
  -5.750  -0.2594   0.01192   0.00680  -0.0860   0.9133   0.0138
  -5.500  -0.2348   0.01092   0.00573  -0.0857   0.9090   0.0149
  -5.250  -0.2083   0.01054   0.00531  -0.0855   0.9044   0.0157
  -5.000  -0.1819   0.01011   0.00482  -0.0853   0.9002   0.0165
  -4.750  -0.1553   0.00969   0.00434  -0.0851   0.8955   0.0172
  -4.500  -0.1288   0.00935   0.00394  -0.0849   0.8891   0.0180
  -4.250  -0.1029   0.00884   0.00333  -0.0846   0.8828   0.0192
  -4.000  -0.0762   0.00845   0.00292  -0.0844   0.8773   0.0211
  -3.750  -0.0490   0.00822   0.00265  -0.0844   0.8720   0.0226
  -3.500  -0.0216   0.00803   0.00241  -0.0843   0.8668   0.0243
  -3.250   0.0055   0.00772   0.00205  -0.0842   0.8605   0.0278
  -3.000   0.0329   0.00758   0.00189  -0.0841   0.8542   0.0328
  -2.750   0.0602   0.00734   0.00166  -0.0840   0.8463   0.0418
  -2.500   0.0877   0.00720   0.00147  -0.0840   0.8394   0.0510
  -2.250   0.1150   0.00694   0.00135  -0.0840   0.8314   0.0933
  -2.000   0.1426   0.00685   0.00127  -0.0840   0.8238   0.1119
  -1.750   0.1703   0.00676   0.00117  -0.0840   0.8145   0.1218
  -1.500   0.1977   0.00665   0.00107  -0.0839   0.8030   0.1343
  -1.250   0.2240   0.00629   0.00096  -0.0839   0.7917   0.2295
  -1.000   0.2488   0.00563   0.00085  -0.0837   0.7803   0.4276
  -0.750   0.2750   0.00541   0.00083  -0.0836   0.7682   0.5166
  -0.500   0.3019   0.00533   0.00083  -0.0834   0.7561   0.5612
  -0.250   0.3289   0.00527   0.00085  -0.0833   0.7444   0.6036
   0.000   0.3558   0.00523   0.00089  -0.0831   0.7331   0.6441
   0.250   0.3828   0.00524   0.00092  -0.0830   0.7216   0.6703
   0.500   0.4098   0.00525   0.00096  -0.0828   0.7101   0.6958
   0.750   0.4369   0.00528   0.00100  -0.0827   0.6983   0.7147
   1.000   0.4642   0.00533   0.00104  -0.0826   0.6851   0.7291
   1.250   0.4905   0.00542   0.00109  -0.0823   0.6609   0.7432
   1.500   0.5162   0.00556   0.00114  -0.0819   0.6297   0.7569
   1.750   0.5420   0.00571   0.00121  -0.0815   0.6006   0.7706
   2.000   0.5679   0.00586   0.00129  -0.0812   0.5722   0.7850
   2.250   0.5929   0.00604   0.00139  -0.0807   0.5365   0.8029
   2.500   0.6174   0.00626   0.00152  -0.0801   0.4947   0.8222
   2.750   0.6394   0.00654   0.00169  -0.0791   0.4335   0.8575
   3.000   0.6643   0.00760   0.00220  -0.0792   0.2570   1.0000
   3.250   0.6833   0.00852   0.00260  -0.0780   0.1410   1.0000
   3.500   0.7086   0.00881   0.00281  -0.0777   0.1243   1.0000
   3.750   0.7344   0.00906   0.00300  -0.0774   0.1151   1.0000
   4.000   0.7609   0.00922   0.00317  -0.0773   0.1102   1.0000
   4.250   0.7868   0.00944   0.00336  -0.0771   0.1029   1.0000
   4.500   0.8131   0.00962   0.00353  -0.0769   0.0924   1.0000
   4.750   0.8362   0.01012   0.00380  -0.0763   0.0500   1.0000
   5.000   0.8607   0.01049   0.00414  -0.0758   0.0398   1.0000
   5.250   0.8859   0.01078   0.00442  -0.0755   0.0331   1.0000
   5.500   0.9100   0.01118   0.00478  -0.0749   0.0246   1.0000
   5.750   0.9337   0.01162   0.00522  -0.0743   0.0201   1.0000
   6.000   0.9581   0.01196   0.00558  -0.0738   0.0183   1.0000
   6.250   0.9815   0.01241   0.00603  -0.0732   0.0164   1.0000
   6.500   1.0030   0.01306   0.00675  -0.0721   0.0151   1.0000
   6.750   1.0264   0.01348   0.00721  -0.0715   0.0146   1.0000
   7.000   1.0490   0.01397   0.00775  -0.0707   0.0140   1.0000
   7.250   1.0709   0.01451   0.00833  -0.0698   0.0135   1.0000
   7.500   1.0923   0.01508   0.00895  -0.0689   0.0130   1.0000
   7.750   1.1133   0.01568   0.00961  -0.0679   0.0126   1.0000
   8.000   1.1335   0.01633   0.01030  -0.0668   0.0122   1.0000
   8.250   1.1515   0.01719   0.01121  -0.0654   0.0116   1.0000
   8.500   1.1609   0.01915   0.01330  -0.0626   0.0109   1.0000
   8.750   1.1817   0.01972   0.01394  -0.0616   0.0107   1.0000
   9.000   1.2011   0.02046   0.01475  -0.0604   0.0105   1.0000
   9.250   1.2196   0.02134   0.01573  -0.0591   0.0102   1.0000
   9.500   1.2370   0.02234   0.01682  -0.0577   0.0100   1.0000
   9.750   1.2535   0.02341   0.01799  -0.0561   0.0097   1.0000
  10.000   1.2696   0.02440   0.01908  -0.0546   0.0094   1.0000
  10.250   1.2848   0.02526   0.02001  -0.0529   0.0091   1.0000
  10.500   1.2991   0.02603   0.02086  -0.0512   0.0088   1.0000
  10.750   1.3124   0.02685   0.02174  -0.0494   0.0085   1.0000
  11.000   1.3240   0.02792   0.02289  -0.0475   0.0083   1.0000
  11.250   1.3328   0.02946   0.02454  -0.0454   0.0081   1.0000
  11.500   1.3257   0.03423   0.02970  -0.0416   0.0077   1.0000
  11.750   1.3290   0.03584   0.03149  -0.0390   0.0076   1.0000
  12.000   1.3338   0.03724   0.03303  -0.0368   0.0075   1.0000
  12.250   1.3359   0.03905   0.03500  -0.0346   0.0073   1.0000
  12.500   1.3344   0.04132   0.03746  -0.0323   0.0072   1.0000
  12.750   1.3302   0.04394   0.04027  -0.0302   0.0071   1.0000
  13.000   1.3218   0.04711   0.04366  -0.0282   0.0070   1.0000
  13.250   1.3105   0.05072   0.04747  -0.0266   0.0069   1.0000
  13.500   1.2958   0.05494   0.05191  -0.0255   0.0068   1.0000
  13.750   1.2783   0.05975   0.05693  -0.0251   0.0068   1.0000
  14.000   1.2588   0.06519   0.06257  -0.0256   0.0067   1.0000
  14.250   1.2349   0.07168   0.06927  -0.0271   0.0067   1.0000
  14.500   1.2092   0.07920   0.07698  -0.0298   0.0068   1.0000
  14.750   1.1810   0.08796   0.08594  -0.0339   0.0068   1.0000
  15.000   1.1498   0.09855   0.09671  -0.0399   0.0069   1.0000
  15.250   1.1168   0.11119   0.10952  -0.0478   0.0070   1.0000
<< Back to NACA 64A410 (naca64a410-il)

Polar data table (+)

Polar graphs


<< Back to NACA 64A410 (naca64a410-il)