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NACA 0006 (naca0006-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: NACA 0006 (naca0006-il)
Reynolds number: 200,000
Max Cl/Cd: 34.02 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-naca0006-il-200000-n5.txt
Download as CSV file: xf-naca0006-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.7134   0.09053   0.08719   0.0174   1.0000   0.0101
  -8.750  -0.7180   0.08461   0.08131   0.0134   1.0000   0.0099
  -8.500  -0.7235   0.07795   0.07469   0.0071   1.0000   0.0098
  -8.250  -0.7278   0.07039   0.06708  -0.0002   1.0000   0.0097
  -8.000  -0.7294   0.06324   0.05979  -0.0048   1.0000   0.0095
  -7.750  -0.7287   0.05643   0.05277  -0.0077   1.0000   0.0094
  -7.500  -0.7252   0.04986   0.04590  -0.0092   1.0000   0.0093
  -7.250  -0.7184   0.04356   0.03920  -0.0098   1.0000   0.0092
  -7.000  -0.7082   0.03775   0.03290  -0.0095   1.0000   0.0093
  -6.750  -0.6942   0.03274   0.02732  -0.0088   1.0000   0.0094
  -6.500  -0.6764   0.02879   0.02281  -0.0079   1.0000   0.0097
  -6.250  -0.6563   0.02554   0.01899  -0.0070   1.0000   0.0107
  -6.000  -0.6356   0.02250   0.01550  -0.0062   1.0000   0.0118
  -5.750  -0.6121   0.02049   0.01316  -0.0054   1.0000   0.0126
  -5.500  -0.5878   0.01884   0.01126  -0.0046   1.0000   0.0137
  -5.250  -0.5633   0.01747   0.00970  -0.0039   1.0000   0.0155
  -5.000  -0.5382   0.01653   0.00854  -0.0033   1.0000   0.0184
  -4.750  -0.5146   0.01515   0.00706  -0.0025   1.0000   0.0209
  -4.500  -0.4895   0.01446   0.00630  -0.0020   1.0000   0.0267
  -4.250  -0.4647   0.01366   0.00541  -0.0015   1.0000   0.0330
  -4.000  -0.4395   0.01309   0.00477  -0.0010   1.0000   0.0418
  -3.750  -0.4140   0.01260   0.00421  -0.0007   1.0000   0.0514
  -3.500  -0.3886   0.01208   0.00367  -0.0002   1.0000   0.0609
  -3.250  -0.3631   0.01161   0.00322   0.0002   1.0000   0.0784
  -3.000  -0.3386   0.01091   0.00281   0.0005   1.0000   0.1392
  -2.750  -0.3143   0.01023   0.00246   0.0009   1.0000   0.2336
  -2.500  -0.2902   0.00963   0.00222   0.0013   1.0000   0.3308
  -2.250  -0.2663   0.00907   0.00203   0.0019   1.0000   0.4305
  -2.000  -0.2434   0.00849   0.00190   0.0028   1.0000   0.5445
  -1.750  -0.2215   0.00796   0.00182   0.0041   1.0000   0.6593
  -1.500  -0.2012   0.00750   0.00186   0.0063   1.0000   0.7809
  -1.250  -0.1752   0.00733   0.00196   0.0078   1.0000   0.8894
  -1.000  -0.1343   0.00733   0.00196   0.0055   1.0000   0.9482
  -0.750  -0.0933   0.00733   0.00192   0.0027   1.0000   0.9757
  -0.500  -0.0509   0.00732   0.00186  -0.0005   1.0000   0.9942
  -0.250  -0.0206   0.00729   0.00181  -0.0013   1.0000   1.0000
   0.000   0.0000   0.00728   0.00180   0.0000   1.0000   1.0000
   0.250   0.0206   0.00729   0.00181   0.0013   1.0000   1.0000
   0.500   0.0508   0.00732   0.00186   0.0006   0.9942   1.0000
   0.750   0.0933   0.00733   0.00192  -0.0027   0.9757   1.0000
   1.000   0.1343   0.00733   0.00196  -0.0055   0.9482   1.0000
   1.250   0.1752   0.00733   0.00196  -0.0078   0.8897   1.0000
   1.500   0.2011   0.00750   0.00186  -0.0063   0.7812   1.0000
   1.750   0.2214   0.00796   0.00182  -0.0041   0.6594   1.0000
   2.000   0.2433   0.00849   0.00190  -0.0027   0.5446   1.0000
   2.250   0.2662   0.00907   0.00203  -0.0019   0.4310   1.0000
   2.500   0.2901   0.00963   0.00222  -0.0013   0.3310   1.0000
   3.000   0.3385   0.01091   0.00281  -0.0005   0.1395   1.0000
   3.250   0.3630   0.01161   0.00322  -0.0002   0.0784   1.0000
   3.500   0.3885   0.01208   0.00367   0.0003   0.0609   1.0000
   3.750   0.4140   0.01260   0.00421   0.0007   0.0514   1.0000
   4.000   0.4394   0.01309   0.00476   0.0011   0.0418   1.0000
   4.250   0.4647   0.01366   0.00541   0.0015   0.0330   1.0000
   4.500   0.4895   0.01446   0.00629   0.0020   0.0266   1.0000
   4.750   0.5146   0.01515   0.00706   0.0025   0.0209   1.0000
   5.000   0.5382   0.01653   0.00854   0.0033   0.0184   1.0000
   5.250   0.5633   0.01747   0.00970   0.0039   0.0155   1.0000
   5.500   0.5879   0.01884   0.01126   0.0046   0.0137   1.0000
   5.750   0.6121   0.02049   0.01316   0.0054   0.0126   1.0000
   6.000   0.6356   0.02251   0.01550   0.0062   0.0118   1.0000
   6.250   0.6562   0.02559   0.01905   0.0070   0.0106   1.0000
   6.500   0.6764   0.02881   0.02283   0.0079   0.0097   1.0000
   6.750   0.6943   0.03274   0.02733   0.0088   0.0094   1.0000
   7.000   0.7083   0.03777   0.03292   0.0095   0.0093   1.0000
   7.250   0.7185   0.04358   0.03923   0.0097   0.0092   1.0000
   7.500   0.7253   0.04988   0.04592   0.0092   0.0093   1.0000
   7.750   0.7289   0.05646   0.05280   0.0076   0.0094   1.0000
   8.000   0.7296   0.06328   0.05983   0.0047   0.0095   1.0000
   8.250   0.7280   0.07045   0.06713   0.0001   0.0097   1.0000
   8.500   0.7239   0.07801   0.07475  -0.0072   0.0098   1.0000
   8.750   0.7185   0.08469   0.08138  -0.0135   0.0099   1.0000
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