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NACA 0006 (naca0006-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: NACA 0006 (naca0006-il)
Reynolds number: 100,000
Max Cl/Cd: 27.26 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0006-il-100000-n5.txt
Download as CSV file: xf-naca0006-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 0006                                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.6995   0.10224   0.09745   0.0211   1.0000   0.0229
  -9.000  -0.7022   0.09655   0.09181   0.0176   1.0000   0.0221
  -8.750  -0.7090   0.08879   0.08413   0.0114   1.0000   0.0208
  -8.250  -0.7104   0.07387   0.06910  -0.0025   1.0000   0.0191
  -8.000  -0.7123   0.06820   0.06332  -0.0054   1.0000   0.0190
  -7.750  -0.7120   0.06261   0.05755  -0.0076   1.0000   0.0189
  -7.500  -0.7090   0.05714   0.05184  -0.0091   1.0000   0.0188
  -7.250  -0.7031   0.05182   0.04619  -0.0099   1.0000   0.0187
  -7.000  -0.6940   0.04670   0.04066  -0.0102   1.0000   0.0187
  -6.750  -0.6816   0.04192   0.03538  -0.0101   1.0000   0.0187
  -6.500  -0.6661   0.03759   0.03047  -0.0095   1.0000   0.0189
  -6.250  -0.6476   0.03385   0.02611  -0.0087   1.0000   0.0192
  -6.000  -0.6294   0.03014   0.02202  -0.0082   1.0000   0.0207
  -5.750  -0.6074   0.02824   0.01985  -0.0077   1.0000   0.0233
  -5.500  -0.5836   0.02570   0.01686  -0.0068   1.0000   0.0252
  -5.250  -0.5588   0.02335   0.01410  -0.0059   1.0000   0.0273
  -5.000  -0.5342   0.02158   0.01202  -0.0051   1.0000   0.0316
  -4.750  -0.5101   0.02008   0.01042  -0.0044   1.0000   0.0363
  -4.500  -0.4864   0.01870   0.00895  -0.0036   1.0000   0.0439
  -4.250  -0.4623   0.01759   0.00772  -0.0028   1.0000   0.0529
  -4.000  -0.4381   0.01668   0.00675  -0.0022   1.0000   0.0665
  -3.750  -0.4138   0.01581   0.00576  -0.0015   1.0000   0.0788
  -3.500  -0.3897   0.01491   0.00501  -0.0010   1.0000   0.1077
  -3.250  -0.3665   0.01377   0.00432  -0.0004   1.0000   0.1958
  -3.000  -0.3440   0.01274   0.00387   0.0002   1.0000   0.3396
  -2.750  -0.3214   0.01195   0.00353   0.0012   1.0000   0.4711
  -2.500  -0.3019   0.01107   0.00344   0.0034   1.0000   0.6531
  -2.250  -0.2799   0.01060   0.00354   0.0064   1.0000   0.8245
  -1.750  -0.1919   0.01053   0.00325   0.0014   1.0000   0.9630
  -1.500  -0.1418   0.01045   0.00299  -0.0034   1.0000   0.9909
  -1.250  -0.1078   0.01034   0.00275  -0.0050   1.0000   1.0000
  -1.000  -0.0859   0.01026   0.00258  -0.0042   1.0000   1.0000
  -0.750  -0.0642   0.01020   0.00246  -0.0032   1.0000   1.0000
  -0.500  -0.0427   0.01015   0.00237  -0.0022   1.0000   1.0000
  -0.250  -0.0213   0.01013   0.00231  -0.0011   1.0000   1.0000
   0.000   0.0000   0.01012   0.00230   0.0000   1.0000   1.0000
   0.250   0.0213   0.01013   0.00231   0.0011   1.0000   1.0000
   0.500   0.0427   0.01015   0.00237   0.0022   1.0000   1.0000
   0.750   0.0642   0.01020   0.00246   0.0032   1.0000   1.0000
   1.000   0.0859   0.01026   0.00258   0.0042   1.0000   1.0000
   1.250   0.1078   0.01034   0.00274   0.0050   1.0000   1.0000
   1.500   0.1418   0.01045   0.00299   0.0034   0.9909   1.0000
   1.750   0.1919   0.01053   0.00325  -0.0014   0.9631   1.0000
   2.250   0.2799   0.01060   0.00354  -0.0064   0.8248   1.0000
   2.500   0.3018   0.01107   0.00344  -0.0034   0.6534   1.0000
   2.750   0.3213   0.01195   0.00353  -0.0011   0.4714   1.0000
   3.000   0.3439   0.01274   0.00387  -0.0002   0.3399   1.0000
   3.250   0.3664   0.01377   0.00432   0.0004   0.1960   1.0000
   3.500   0.3896   0.01490   0.00501   0.0010   0.1078   1.0000
   3.750   0.4137   0.01581   0.00576   0.0015   0.0789   1.0000
   4.000   0.4381   0.01668   0.00675   0.0022   0.0665   1.0000
   4.250   0.4622   0.01759   0.00772   0.0028   0.0529   1.0000
   4.500   0.4863   0.01870   0.00895   0.0036   0.0439   1.0000
   4.750   0.5101   0.02008   0.01042   0.0044   0.0363   1.0000
   5.000   0.5342   0.02159   0.01202   0.0051   0.0316   1.0000
   5.250   0.5588   0.02336   0.01410   0.0058   0.0273   1.0000
   5.500   0.5836   0.02570   0.01686   0.0068   0.0252   1.0000
   5.750   0.6075   0.02824   0.01985   0.0077   0.0233   1.0000
   6.000   0.6295   0.03015   0.02203   0.0082   0.0207   1.0000
   6.250   0.6476   0.03386   0.02612   0.0087   0.0192   1.0000
   6.500   0.6662   0.03760   0.03048   0.0095   0.0189   1.0000
   6.750   0.6817   0.04193   0.03539   0.0100   0.0187   1.0000
   7.000   0.6941   0.04672   0.04068   0.0102   0.0187   1.0000
   7.250   0.7032   0.05183   0.04621   0.0099   0.0187   1.0000
   7.500   0.7092   0.05716   0.05186   0.0090   0.0188   1.0000
   7.750   0.7122   0.06264   0.05758   0.0075   0.0189   1.0000
   8.000   0.7125   0.06823   0.06335   0.0053   0.0190   1.0000
   8.250   0.7107   0.07392   0.06915   0.0024   0.0191   1.0000
   8.750   0.6046   0.07599   0.07155  -0.0017   0.0209   1.0000
   9.000   0.5924   0.08296   0.07846  -0.0051   0.0216   1.0000
   9.250   0.5834   0.08901   0.08447  -0.0076   0.0223   1.0000
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