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NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: NACA 0010-64 (naca001064-il)
Reynolds number: 500,000
Max Cl/Cd: 49.19 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca001064-il-500000.txt
Download as CSV file: xf-naca001064-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0010-64                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6948   0.08601   0.08371  -0.0253   1.0000   0.0200
 -13.000  -0.7777   0.10123   0.09887  -0.0092   1.0000   0.0196
 -12.750  -0.8634   0.07215   0.06964  -0.0290   1.0000   0.0182
 -12.500  -0.9109   0.05996   0.05719  -0.0381   1.0000   0.0176
 -12.250  -0.9548   0.05178   0.04872  -0.0405   1.0000   0.0174
 -12.000  -0.9836   0.04678   0.04344  -0.0392   1.0000   0.0174
 -11.750  -1.0042   0.04313   0.03952  -0.0361   1.0000   0.0177
 -11.500  -1.0203   0.04009   0.03620  -0.0319   1.0000   0.0180
 -11.250  -1.0286   0.03708   0.03286  -0.0282   1.0000   0.0184
 -11.000  -1.0298   0.03448   0.02990  -0.0250   1.0000   0.0189
 -10.750  -1.0232   0.03284   0.02795  -0.0224   1.0000   0.0193
 -10.500  -1.0234   0.02932   0.02411  -0.0192   1.0000   0.0199
 -10.250  -1.0091   0.02827   0.02300  -0.0176   1.0000   0.0205
 -10.000  -0.9936   0.02756   0.02223  -0.0159   1.0000   0.0211
  -9.750  -0.9780   0.02682   0.02140  -0.0142   1.0000   0.0218
  -9.500  -0.9625   0.02603   0.02050  -0.0123   1.0000   0.0227
  -9.250  -0.9470   0.02521   0.01950  -0.0102   1.0000   0.0237
  -9.000  -0.9307   0.02477   0.01889  -0.0082   1.0000   0.0244
  -8.750  -0.9189   0.02220   0.01611  -0.0059   1.0000   0.0255
  -8.500  -0.9022   0.02140   0.01529  -0.0041   1.0000   0.0264
  -8.250  -0.8850   0.02081   0.01464  -0.0024   1.0000   0.0273
  -8.000  -0.8674   0.02027   0.01403  -0.0006   1.0000   0.0285
  -7.750  -0.8496   0.01974   0.01341   0.0012   1.0000   0.0297
  -7.500  -0.8312   0.01936   0.01293   0.0030   1.0000   0.0306
  -7.250  -0.8143   0.01795   0.01138   0.0049   1.0000   0.0318
  -7.000  -0.7973   0.01693   0.01035   0.0067   1.0000   0.0331
  -6.750  -0.7789   0.01646   0.00986   0.0083   1.0000   0.0344
  -6.500  -0.7600   0.01602   0.00939   0.0099   1.0000   0.0358
  -6.250  -0.7410   0.01554   0.00886   0.0115   1.0000   0.0370
  -6.000  -0.7217   0.01510   0.00836   0.0130   1.0000   0.0380
  -5.750  -0.7015   0.01483   0.00803   0.0144   1.0000   0.0389
  -5.500  -0.6775   0.01377   0.00693   0.0147   0.9991   0.0409
  -5.250  -0.6450   0.01322   0.00637   0.0134   0.9971   0.0428
  -5.000  -0.6115   0.01283   0.00597   0.0119   0.9953   0.0449
  -4.750  -0.5775   0.01249   0.00559   0.0103   0.9936   0.0472
  -4.500  -0.5456   0.01212   0.00519   0.0093   0.9908   0.0489
  -4.250  -0.5133   0.01162   0.00470   0.0081   0.9882   0.0536
  -4.000  -0.4788   0.01134   0.00441   0.0064   0.9860   0.0591
  -3.750  -0.4443   0.01086   0.00407   0.0047   0.9842   0.0793
  -3.500  -0.4126   0.01029   0.00378   0.0035   0.9817   0.1356
  -3.250  -0.3837   0.00972   0.00353   0.0028   0.9776   0.2087
  -3.000  -0.3529   0.00900   0.00328   0.0016   0.9746   0.3188
  -2.750  -0.3231   0.00803   0.00304   0.0005   0.9723   0.4907
  -2.500  -0.2913   0.00736   0.00291  -0.0007   0.9705   0.6261
  -2.250  -0.2657   0.00703   0.00286  -0.0001   0.9650   0.6993
  -2.000  -0.2338   0.00681   0.00283  -0.0009   0.9616   0.7527
  -1.750  -0.2002   0.00667   0.00280  -0.0019   0.9588   0.7887
  -1.500  -0.1666   0.00657   0.00279  -0.0029   0.9564   0.8212
  -1.250  -0.1404   0.00652   0.00281  -0.0022   0.9501   0.8438
  -1.000  -0.1101   0.00647   0.00279  -0.0024   0.9455   0.8608
  -0.750  -0.0791   0.00644   0.00279  -0.0026   0.9418   0.8791
  -0.500  -0.0548   0.00646   0.00285  -0.0014   0.9343   0.8956
  -0.250  -0.0265   0.00649   0.00290  -0.0010   0.9287   0.9091
   0.000   0.0000   0.00653   0.00296   0.0000   0.9200   0.9201
   0.250   0.0264   0.00649   0.00290   0.0010   0.9090   0.9287
   0.500   0.0547   0.00646   0.00285   0.0014   0.8955   0.9343
   0.750   0.0791   0.00644   0.00279   0.0027   0.8791   0.9418
   1.000   0.1101   0.00647   0.00279   0.0024   0.8608   0.9455
   1.250   0.1404   0.00652   0.00281   0.0022   0.8437   0.9501
   1.500   0.1666   0.00657   0.00279   0.0029   0.8212   0.9564
   1.750   0.2002   0.00667   0.00280   0.0019   0.7888   0.9588
   2.000   0.2338   0.00681   0.00283   0.0009   0.7528   0.9616
   2.250   0.2657   0.00703   0.00286   0.0001   0.6992   0.9650
   2.500   0.2913   0.00735   0.00291   0.0007   0.6268   0.9705
   2.750   0.3231   0.00804   0.00304  -0.0005   0.4903   0.9723
   3.000   0.3529   0.00900   0.00328  -0.0016   0.3187   0.9747
   3.250   0.3837   0.00972   0.00353  -0.0028   0.2087   0.9776
   3.500   0.4126   0.01029   0.00378  -0.0035   0.1356   0.9817
   3.750   0.4443   0.01086   0.00407  -0.0047   0.0793   0.9842
   4.000   0.4788   0.01134   0.00441  -0.0064   0.0591   0.9860
   4.250   0.5133   0.01162   0.00470  -0.0081   0.0536   0.9882
   4.500   0.5456   0.01212   0.00518  -0.0093   0.0490   0.9908
   4.750   0.5775   0.01249   0.00559  -0.0103   0.0472   0.9936
   5.000   0.6115   0.01283   0.00596  -0.0119   0.0449   0.9953
   5.250   0.6451   0.01322   0.00637  -0.0134   0.0428   0.9971
   5.500   0.6774   0.01377   0.00693  -0.0147   0.0409   0.9991
   5.750   0.7014   0.01482   0.00803  -0.0143   0.0389   1.0000
   6.000   0.7215   0.01509   0.00836  -0.0130   0.0380   1.0000
   6.250   0.7409   0.01554   0.00885  -0.0114   0.0370   1.0000
   6.500   0.7599   0.01601   0.00938  -0.0099   0.0358   1.0000
   6.750   0.7788   0.01645   0.00985  -0.0083   0.0344   1.0000
   7.000   0.7972   0.01692   0.01034  -0.0066   0.0331   1.0000
   7.250   0.8141   0.01795   0.01138  -0.0048   0.0318   1.0000
   7.500   0.8311   0.01936   0.01292  -0.0030   0.0306   1.0000
   7.750   0.8494   0.01974   0.01341  -0.0012   0.0297   1.0000
   8.000   0.8673   0.02026   0.01402   0.0006   0.0285   1.0000
   8.250   0.8849   0.02080   0.01464   0.0024   0.0273   1.0000
   8.500   0.9021   0.02140   0.01528   0.0042   0.0264   1.0000
   8.750   0.9188   0.02220   0.01611   0.0059   0.0255   1.0000
   9.000   0.9306   0.02477   0.01889   0.0082   0.0244   1.0000
   9.250   0.9470   0.02521   0.01951   0.0103   0.0237   1.0000
   9.500   0.9624   0.02604   0.02051   0.0123   0.0227   1.0000
   9.750   0.9779   0.02683   0.02142   0.0142   0.0218   1.0000
  10.000   0.9936   0.02757   0.02224   0.0159   0.0211   1.0000
  10.250   1.0091   0.02828   0.02302   0.0176   0.0205   1.0000
  10.500   1.0234   0.02933   0.02412   0.0192   0.0199   1.0000
  10.750   1.0233   0.03283   0.02795   0.0224   0.0193   1.0000
  11.000   1.0298   0.03449   0.02991   0.0250   0.0189   1.0000
  11.250   1.0288   0.03709   0.03287   0.0282   0.0184   1.0000
  11.500   1.0205   0.04011   0.03623   0.0318   0.0180   1.0000
  11.750   1.0043   0.04318   0.03957   0.0360   0.0177   1.0000
  12.000   0.9846   0.04675   0.04340   0.0390   0.0174   1.0000
  12.250   0.9550   0.05185   0.04879   0.0404   0.0174   1.0000
  12.500   0.9101   0.06022   0.05747   0.0378   0.0177   1.0000
  12.750   0.8630   0.07253   0.07003   0.0284   0.0182   1.0000
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