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NACA 66-209 (naca66209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: NACA 66-209 (naca66209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.45 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-naca66209-il-1000000.txt
Download as CSV file: xf-naca66209-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NACA 66-209                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5195   0.08378   0.08217  -0.0360   1.0000   0.0090
  -9.250  -0.5243   0.07875   0.07718  -0.0394   1.0000   0.0091
  -9.000  -0.5378   0.07205   0.07050  -0.0458   1.0000   0.0087
  -8.750  -0.5532   0.06818   0.06662  -0.0473   1.0000   0.0092
  -8.500  -0.5709   0.06404   0.06244  -0.0470   0.9988   0.0088
  -8.250  -0.5606   0.05848   0.05676  -0.0519   0.9882   0.0095
  -8.000  -0.5456   0.05223   0.05033  -0.0568   0.9830   0.0099
  -7.750  -0.5193   0.04715   0.04500  -0.0590   0.9760   0.0113
  -6.750  -0.4838   0.01378   0.01050  -0.0506   0.9172   0.0101
  -6.500  -0.4759   0.00892   0.00506  -0.0480   0.9114   0.0096
  -6.250  -0.4575   0.00679   0.00256  -0.0468   0.9063   0.0103
  -6.000  -0.4364   0.00534   0.00077  -0.0457   0.9019   0.0110
  -5.750  -0.4132   0.01582   0.01087  -0.0488   0.9083   0.0115
  -5.500  -0.3929   0.01268   0.00740  -0.0475   0.9034   0.0122
  -5.250  -0.3682   0.01200   0.00665  -0.0471   0.8991   0.0129
  -5.000  -0.3425   0.01156   0.00617  -0.0469   0.8945   0.0137
  -4.750  -0.3163   0.01133   0.00590  -0.0468   0.8903   0.0151
  -4.500  -0.2910   0.01078   0.00527  -0.0464   0.8864   0.0158
  -4.250  -0.2651   0.01036   0.00481  -0.0461   0.8823   0.0165
  -4.000  -0.2388   0.01008   0.00448  -0.0460   0.8781   0.0170
  -3.750  -0.2168   0.00901   0.00328  -0.0450   0.8740   0.0184
  -3.500  -0.1908   0.00867   0.00293  -0.0448   0.8702   0.0206
  -3.250  -0.1641   0.00842   0.00266  -0.0448   0.8664   0.0227
  -3.000  -0.1373   0.00822   0.00242  -0.0447   0.8629   0.0245
  -2.750  -0.1106   0.00796   0.00209  -0.0446   0.8596   0.0269
  -2.500  -0.0839   0.00770   0.00181  -0.0445   0.8564   0.0333
  -2.250  -0.0565   0.00755   0.00165  -0.0445   0.8529   0.0384
  -2.000  -0.0301   0.00721   0.00146  -0.0445   0.8494   0.0852
  -1.750  -0.0092   0.00594   0.00119  -0.0441   0.8460   0.3967
  -1.500   0.0114   0.00483   0.00106  -0.0433   0.8427   0.6918
  -1.250   0.0382   0.00472   0.00110  -0.0431   0.8396   0.7436
  -1.000   0.0655   0.00470   0.00114  -0.0430   0.8366   0.7729
  -0.750   0.0930   0.00472   0.00117  -0.0429   0.8337   0.7916
  -0.500   0.1206   0.00476   0.00122  -0.0428   0.8307   0.8057
  -0.250   0.1483   0.00477   0.00126  -0.0428   0.8271   0.8148
   0.000   0.1759   0.00477   0.00128  -0.0428   0.8223   0.8231
   0.250   0.2033   0.00483   0.00131  -0.0426   0.8176   0.8331
   0.500   0.2309   0.00481   0.00133  -0.0426   0.8122   0.8373
   0.750   0.2583   0.00481   0.00128  -0.0425   0.8021   0.8406
   1.000   0.2855   0.00479   0.00124  -0.0423   0.7891   0.8439
   1.250   0.3133   0.00478   0.00124  -0.0424   0.7786   0.8470
   1.500   0.3404   0.00478   0.00123  -0.0422   0.7643   0.8499
   1.750   0.3672   0.00481   0.00123  -0.0420   0.7453   0.8531
   2.000   0.3934   0.00489   0.00124  -0.0417   0.7132   0.8568
   2.250   0.4143   0.00536   0.00129  -0.0403   0.5962   0.8608
   2.500   0.4267   0.00670   0.00170  -0.0378   0.3602   0.8650
   2.750   0.4426   0.00790   0.00211  -0.0362   0.1538   0.8696
   3.000   0.4636   0.00869   0.00244  -0.0352   0.0417   0.8740
   3.250   0.4886   0.00896   0.00270  -0.0348   0.0319   0.8778
   3.500   0.5145   0.00914   0.00293  -0.0345   0.0282   0.8820
   3.750   0.5399   0.00942   0.00322  -0.0342   0.0235   0.8866
   4.000   0.5633   0.00990   0.00378  -0.0333   0.0202   0.8911
   4.250   0.5882   0.01014   0.00407  -0.0329   0.0191   0.8956
   4.500   0.6130   0.01047   0.00443  -0.0324   0.0179   0.9006
   4.750   0.6370   0.01082   0.00484  -0.0318   0.0167   0.9053
   5.000   0.6605   0.01118   0.00523  -0.0311   0.0153   0.9104
   5.250   0.6799   0.01215   0.00629  -0.0296   0.0141   0.9166
   5.500   0.6976   0.01341   0.00768  -0.0278   0.0136   0.9228
   5.750   0.7214   0.01388   0.00821  -0.0271   0.0133   0.9290
   6.000   0.7438   0.01445   0.00887  -0.0261   0.0130   0.9351
   6.250   0.7665   0.01520   0.00970  -0.0253   0.0126   0.9421
   6.500   0.7885   0.01569   0.01029  -0.0242   0.0117   0.9497
   6.750   0.8105   0.01612   0.01079  -0.0232   0.0110   0.9590
   7.500   0.8900   0.01915   0.01415  -0.0239   0.0095   1.0000
   8.000   0.9255   0.02568   0.02145  -0.0212   0.0086   1.0000
   8.250   0.9449   0.02764   0.02366  -0.0200   0.0080   1.0000
   8.500   0.9533   0.03237   0.02884  -0.0172   0.0074   1.0000
   8.750   0.9417   0.04101   0.03811  -0.0119   0.0076   1.0000
   9.000   0.9332   0.04710   0.04456  -0.0080   0.0078   1.0000
   9.250   0.9229   0.05230   0.05002  -0.0047   0.0081   1.0000
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