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NACA 65-206 (naca65206-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: NACA 65-206 (naca65206-il)
Reynolds number: 1,000,000
Max Cl/Cd: 67.66 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca65206-il-1000000-n5.txt
Download as CSV file: xf-naca65206-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 65-206                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5364   0.08651   0.08489  -0.0110   1.0000   0.0044
  -8.000  -0.5359   0.08258   0.08098  -0.0132   1.0000   0.0044
  -7.000  -0.5369   0.06043   0.05879  -0.0306   1.0000   0.0018
  -6.750  -0.5277   0.05530   0.05356  -0.0333   1.0000   0.0018
  -6.500  -0.5167   0.05020   0.04833  -0.0352   1.0000   0.0017
  -6.250  -0.5039   0.04510   0.04303  -0.0363   1.0000   0.0017
  -6.000  -0.4896   0.04019   0.03792  -0.0365   1.0000   0.0016
  -5.750  -0.4630   0.03388   0.03130  -0.0389   0.9942   0.0016
  -5.500  -0.4332   0.02697   0.02392  -0.0407   0.9894   0.0016
  -5.250  -0.4045   0.01408   0.00984  -0.0404   0.9836   0.0019
  -5.000  -0.3750   0.01103   0.00624  -0.0410   0.9790   0.0023
  -4.750  -0.3445   0.01035   0.00546  -0.0418   0.9734   0.0027
  -4.500  -0.3138   0.00968   0.00468  -0.0427   0.9674   0.0030
  -4.250  -0.2845   0.00927   0.00422  -0.0432   0.9596   0.0035
  -4.000  -0.2556   0.00900   0.00390  -0.0436   0.9513   0.0042
  -3.750  -0.2280   0.00851   0.00330  -0.0436   0.9420   0.0046
  -3.500  -0.2013   0.00785   0.00255  -0.0434   0.9319   0.0071
  -3.250  -0.1742   0.00768   0.00232  -0.0433   0.9222   0.0092
  -3.000  -0.1470   0.00782   0.00248  -0.0432   0.9126   0.0102
  -2.500  -0.0934   0.00705   0.00146  -0.0429   0.8926   0.0133
  -2.250  -0.0663   0.00686   0.00120  -0.0428   0.8829   0.0157
  -2.000  -0.0390   0.00673   0.00103  -0.0426   0.8734   0.0199
  -1.750  -0.0117   0.00664   0.00088  -0.0426   0.8635   0.0230
  -1.500   0.0157   0.00653   0.00076  -0.0425   0.8538   0.0340
  -1.250   0.0429   0.00632   0.00066  -0.0425   0.8445   0.0817
  -1.000   0.0692   0.00553   0.00053  -0.0429   0.8345   0.3162
  -0.750   0.0945   0.00454   0.00045  -0.0431   0.8242   0.6174
  -0.500   0.1208   0.00428   0.00047  -0.0428   0.8139   0.7153
  -0.250   0.1471   0.00415   0.00050  -0.0425   0.8035   0.7733
   0.000   0.1740   0.00413   0.00052  -0.0423   0.7927   0.7987
   0.250   0.2012   0.00415   0.00053  -0.0421   0.7795   0.8117
   0.500   0.2277   0.00422   0.00054  -0.0418   0.7524   0.8236
   0.750   0.2538   0.00435   0.00055  -0.0414   0.7144   0.8353
   1.000   0.2797   0.00450   0.00059  -0.0410   0.6709   0.8465
   1.250   0.3019   0.00519   0.00068  -0.0401   0.5032   0.8578
   1.500   0.3229   0.00637   0.00096  -0.0394   0.2513   0.8694
   1.750   0.3466   0.00709   0.00121  -0.0390   0.0998   0.8812
   2.000   0.3719   0.00745   0.00139  -0.0386   0.0379   0.8933
   2.250   0.3979   0.00760   0.00153  -0.0383   0.0260   0.9057
   2.500   0.4238   0.00773   0.00169  -0.0379   0.0214   0.9180
   2.750   0.4492   0.00795   0.00194  -0.0374   0.0159   0.9305
   3.000   0.4740   0.00823   0.00238  -0.0367   0.0144   0.9441
   3.250   0.4993   0.00849   0.00273  -0.0362   0.0138   0.9598
   3.500   0.5292   0.00862   0.00288  -0.0367   0.0133   0.9792
   3.750   0.5591   0.00873   0.00298  -0.0374   0.0118   1.0000
   4.000   0.5861   0.00895   0.00322  -0.0374   0.0095   1.0000
   4.250   0.6126   0.00931   0.00356  -0.0373   0.0066   1.0000
   4.500   0.6390   0.00966   0.00400  -0.0372   0.0057   1.0000
   4.750   0.6657   0.00993   0.00430  -0.0371   0.0047   1.0000
   5.000   0.6922   0.01023   0.00456  -0.0371   0.0034   1.0000
   5.250   0.7161   0.01124   0.00574  -0.0364   0.0025   1.0000
   5.500   0.7404   0.01218   0.00684  -0.0358   0.0023   1.0000
   5.750   0.7637   0.01365   0.00853  -0.0349   0.0021   1.0000
   6.000   0.7862   0.01590   0.01111  -0.0338   0.0021   1.0000
   6.250   0.8039   0.02203   0.01799  -0.0313   0.0021   1.0000
   6.500   0.8165   0.03053   0.02720  -0.0280   0.0021   1.0000
   6.750   0.8312   0.03610   0.03316  -0.0260   0.0020   1.0000
   7.000   0.8449   0.04122   0.03858  -0.0245   0.0018   1.0000
   7.250   0.8557   0.04661   0.04425  -0.0232   0.0017   1.0000
   7.500   0.8629   0.05230   0.05020  -0.0222   0.0017   1.0000
   7.750   0.8677   0.05777   0.05586  -0.0217   0.0016   1.0000
   8.000   0.8685   0.06338   0.06165  -0.0217   0.0016   1.0000
   8.250   0.8650   0.06899   0.06739  -0.0222   0.0016   1.0000
   8.500   0.8589   0.07425   0.07275  -0.0233   0.0016   1.0000
   8.750   0.8447   0.07897   0.07754  -0.0242   0.0016   1.0000
   9.000   0.8283   0.08432   0.08292  -0.0280   0.0016   1.0000
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