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NACA 0010-64 (naca001064-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0010-64 (naca001064-il)
Reynolds number: 200,000
Max Cl/Cd: 38.68 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca001064-il-200000-n5.txt
Download as CSV file: xf-naca001064-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.8682   0.07191   0.06803  -0.0302   1.0000   0.0184
 -12.500  -0.8976   0.06310   0.05903  -0.0366   1.0000   0.0182
 -12.250  -0.9261   0.05644   0.05213  -0.0394   1.0000   0.0181
 -12.000  -0.9523   0.05117   0.04656  -0.0394   1.0000   0.0182
 -11.750  -0.9756   0.04680   0.04185  -0.0373   1.0000   0.0184
 -11.500  -0.9943   0.04317   0.03782  -0.0338   1.0000   0.0188
 -11.250  -1.0037   0.04041   0.03476  -0.0302   1.0000   0.0191
 -11.000  -0.9988   0.03886   0.03310  -0.0280   1.0000   0.0196
 -10.750  -0.9902   0.03762   0.03176  -0.0261   1.0000   0.0201
 -10.500  -0.9807   0.03630   0.03030  -0.0242   1.0000   0.0208
 -10.250  -0.9705   0.03493   0.02873  -0.0222   1.0000   0.0217
 -10.000  -0.9602   0.03332   0.02684  -0.0201   1.0000   0.0229
  -9.750  -0.9490   0.03159   0.02477  -0.0179   1.0000   0.0243
  -9.500  -0.9358   0.03012   0.02296  -0.0158   1.0000   0.0253
  -9.250  -0.9225   0.02843   0.02113  -0.0141   1.0000   0.0264
  -9.000  -0.9062   0.02762   0.02027  -0.0125   1.0000   0.0276
  -8.750  -0.8896   0.02684   0.01938  -0.0108   1.0000   0.0290
  -8.500  -0.8727   0.02588   0.01824  -0.0091   1.0000   0.0306
  -8.250  -0.8550   0.02488   0.01702  -0.0075   1.0000   0.0320
  -8.000  -0.8367   0.02410   0.01606  -0.0059   1.0000   0.0332
  -7.750  -0.8197   0.02276   0.01465  -0.0043   1.0000   0.0349
  -7.500  -0.8016   0.02202   0.01387  -0.0028   1.0000   0.0363
  -7.250  -0.7830   0.02132   0.01309  -0.0012   1.0000   0.0378
  -7.000  -0.7642   0.02067   0.01236   0.0004   1.0000   0.0395
  -6.750  -0.7453   0.02002   0.01160   0.0019   1.0000   0.0410
  -6.500  -0.7264   0.01938   0.01084   0.0035   1.0000   0.0420
  -6.250  -0.7084   0.01863   0.01005   0.0052   1.0000   0.0432
  -6.000  -0.6910   0.01791   0.00933   0.0070   1.0000   0.0451
  -5.750  -0.6725   0.01740   0.00879   0.0086   1.0000   0.0469
  -5.500  -0.6537   0.01691   0.00826   0.0102   1.0000   0.0485
  -5.250  -0.6347   0.01645   0.00774   0.0117   1.0000   0.0501
  -5.000  -0.6154   0.01603   0.00727   0.0132   1.0000   0.0519
  -4.750  -0.5866   0.01557   0.00676   0.0127   0.9979   0.0543
  -4.500  -0.5551   0.01509   0.00630   0.0115   0.9951   0.0592
  -4.250  -0.5235   0.01472   0.00590   0.0104   0.9921   0.0664
  -4.000  -0.4923   0.01429   0.00551   0.0094   0.9887   0.0790
  -3.750  -0.4603   0.01384   0.00517   0.0081   0.9858   0.1005
  -3.500  -0.4300   0.01339   0.00487   0.0071   0.9822   0.1347
  -3.250  -0.4000   0.01291   0.00461   0.0062   0.9782   0.1842
  -3.000  -0.3687   0.01236   0.00436   0.0049   0.9750   0.2518
  -2.750  -0.3427   0.01157   0.00409   0.0047   0.9704   0.3688
  -2.500  -0.3203   0.01052   0.00393   0.0053   0.9655   0.5595
  -2.250  -0.2922   0.01001   0.00401   0.0055   0.9625   0.6917
  -2.000  -0.2640   0.00987   0.00409   0.0059   0.9578   0.7561
  -1.750  -0.2328   0.00983   0.00414   0.0055   0.9533   0.7911
  -1.250  -0.1649   0.00993   0.00435   0.0038   0.9470   0.8553
  -1.000  -0.1359   0.01006   0.00451   0.0042   0.9408   0.8786
  -0.750  -0.1016   0.01018   0.00464   0.0033   0.9365   0.8964
  -0.500  -0.0651   0.01022   0.00466   0.0017   0.9331   0.9062
  -0.250  -0.0352   0.01024   0.00468   0.0014   0.9257   0.9145
   0.000   0.0000   0.01024   0.00467   0.0000   0.9204   0.9204
   0.250   0.0352   0.01024   0.00468  -0.0014   0.9144   0.9257
   0.500   0.0651   0.01022   0.00466  -0.0017   0.9062   0.9331
   0.750   0.1016   0.01018   0.00464  -0.0033   0.8964   0.9365
   1.000   0.1359   0.01006   0.00451  -0.0042   0.8786   0.9408
   1.250   0.1649   0.00993   0.00435  -0.0038   0.8553   0.9470
   1.750   0.2328   0.00983   0.00414  -0.0055   0.7910   0.9533
   2.000   0.2640   0.00987   0.00409  -0.0059   0.7561   0.9578
   2.250   0.2922   0.01001   0.00401  -0.0055   0.6913   0.9625
   2.500   0.3202   0.01053   0.00393  -0.0053   0.5584   0.9655
   2.750   0.3427   0.01157   0.00409  -0.0047   0.3690   0.9705
   3.000   0.3687   0.01236   0.00436  -0.0050   0.2519   0.9751
   3.250   0.4000   0.01291   0.00461  -0.0062   0.1843   0.9782
   3.500   0.4300   0.01339   0.00487  -0.0071   0.1347   0.9822
   3.750   0.4603   0.01383   0.00517  -0.0081   0.1005   0.9858
   4.000   0.4924   0.01429   0.00551  -0.0094   0.0790   0.9888
   4.250   0.5235   0.01472   0.00589  -0.0104   0.0663   0.9921
   4.500   0.5552   0.01509   0.00630  -0.0115   0.0592   0.9952
   4.750   0.5867   0.01557   0.00676  -0.0127   0.0543   0.9979
   5.000   0.6153   0.01603   0.00727  -0.0132   0.0519   1.0000
   5.250   0.6347   0.01645   0.00774  -0.0117   0.0501   1.0000
   5.500   0.6537   0.01690   0.00826  -0.0102   0.0485   1.0000
   5.750   0.6724   0.01739   0.00879  -0.0086   0.0469   1.0000
   6.000   0.6910   0.01790   0.00932  -0.0070   0.0451   1.0000
   6.250   0.7083   0.01863   0.01004  -0.0052   0.0432   1.0000
   6.500   0.7264   0.01937   0.01084  -0.0035   0.0420   1.0000
   6.750   0.7453   0.02002   0.01160  -0.0019   0.0410   1.0000
   7.000   0.7642   0.02067   0.01236  -0.0003   0.0395   1.0000
   7.250   0.7830   0.02132   0.01309   0.0012   0.0378   1.0000
   7.500   0.8015   0.02202   0.01387   0.0028   0.0363   1.0000
   7.750   0.8197   0.02275   0.01464   0.0043   0.0349   1.0000
   8.000   0.8367   0.02410   0.01605   0.0059   0.0332   1.0000
   8.250   0.8550   0.02488   0.01702   0.0075   0.0320   1.0000
   8.500   0.8727   0.02588   0.01824   0.0091   0.0306   1.0000
   8.750   0.8896   0.02684   0.01937   0.0108   0.0290   1.0000
   9.000   0.9062   0.02763   0.02027   0.0125   0.0276   1.0000
   9.250   0.9225   0.02843   0.02113   0.0140   0.0264   1.0000
   9.500   0.9359   0.03012   0.02296   0.0158   0.0253   1.0000
   9.750   0.9491   0.03159   0.02477   0.0179   0.0243   1.0000
  10.000   0.9603   0.03332   0.02685   0.0201   0.0229   1.0000
  10.250   0.9707   0.03492   0.02872   0.0222   0.0217   1.0000
  10.500   0.9809   0.03631   0.03030   0.0241   0.0207   1.0000
  10.750   0.9903   0.03763   0.03177   0.0261   0.0201   1.0000
  11.000   0.9990   0.03886   0.03311   0.0280   0.0196   1.0000
  11.250   1.0040   0.04041   0.03476   0.0302   0.0191   1.0000
  11.500   0.9946   0.04319   0.03785   0.0338   0.0187   1.0000
  11.750   0.9760   0.04683   0.04188   0.0373   0.0184   1.0000
  12.000   0.9527   0.05121   0.04661   0.0393   0.0182   1.0000
  12.250   0.9261   0.05654   0.05223   0.0393   0.0181   1.0000
  12.500   0.8978   0.06323   0.05917   0.0363   0.0182   1.0000
  12.750   0.8683   0.07213   0.06827   0.0299   0.0184   1.0000
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