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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 200,000
Max Cl/Cd: 68.05 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq209-il-200000-n5.txt
Download as CSV file: xf-hq209-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 AIRFOIL                                
  
 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  -0.4631   0.08563   0.08214  -0.0290   1.0000   0.0097
  -8.750  -0.4674   0.08062   0.07719  -0.0315   1.0000   0.0095
  -8.500  -0.4738   0.07532   0.07196  -0.0345   1.0000   0.0094
  -8.250  -0.4837   0.06985   0.06657  -0.0381   1.0000   0.0093
  -8.000  -0.5030   0.06068   0.05740  -0.0459   1.0000   0.0088
  -7.750  -0.5119   0.05429   0.05089  -0.0483   1.0000   0.0086
  -7.500  -0.5182   0.04859   0.04502  -0.0488   1.0000   0.0085
  -7.250  -0.5203   0.04391   0.04012  -0.0478   1.0000   0.0084
  -7.000  -0.5230   0.03900   0.03488  -0.0468   0.9994   0.0085
  -6.750  -0.4991   0.03379   0.02917  -0.0505   0.9928   0.0089
  -6.500  -0.4693   0.03281   0.02806  -0.0528   0.9878   0.0102
  -6.250  -0.4404   0.02925   0.02401  -0.0550   0.9827   0.0115
  -6.000  -0.4122   0.02512   0.01924  -0.0563   0.9769   0.0118
  -5.750  -0.3803   0.02205   0.01561  -0.0577   0.9732   0.0122
  -5.500  -0.3506   0.01984   0.01299  -0.0582   0.9678   0.0128
  -5.250  -0.3193   0.01825   0.01107  -0.0590   0.9629   0.0136
  -5.000  -0.2876   0.01661   0.00928  -0.0603   0.9591   0.0155
  -4.750  -0.2585   0.01593   0.00852  -0.0607   0.9524   0.0179
  -4.500  -0.2272   0.01488   0.00734  -0.0615   0.9473   0.0198
  -4.250  -0.1971   0.01409   0.00642  -0.0620   0.9413   0.0220
  -4.000  -0.1674   0.01327   0.00553  -0.0626   0.9349   0.0290
  -3.750  -0.1365   0.01276   0.00497  -0.0633   0.9294   0.0444
  -3.500  -0.1079   0.01229   0.00455  -0.0636   0.9223   0.0652
  -3.250  -0.0774   0.01180   0.00415  -0.0643   0.9169   0.0968
  -3.000  -0.0505   0.01126   0.00382  -0.0644   0.9092   0.1563
  -2.500   0.0015   0.00979   0.00331  -0.0646   0.8952   0.4431
  -2.250   0.0279   0.00944   0.00327  -0.0641   0.8889   0.5528
  -2.000   0.0534   0.00930   0.00327  -0.0634   0.8808   0.6170
  -1.750   0.0801   0.00922   0.00324  -0.0629   0.8739   0.6598
  -1.500   0.1059   0.00917   0.00321  -0.0621   0.8658   0.6976
  -1.250   0.1316   0.00913   0.00320  -0.0613   0.8578   0.7287
  -1.000   0.1575   0.00909   0.00317  -0.0605   0.8498   0.7550
  -0.750   0.1830   0.00906   0.00314  -0.0597   0.8406   0.7754
  -0.500   0.2098   0.00903   0.00305  -0.0592   0.8324   0.7880
  -0.250   0.2364   0.00899   0.00299  -0.0587   0.8227   0.7993
   0.000   0.2625   0.00895   0.00293  -0.0581   0.8110   0.8114
   0.250   0.2885   0.00890   0.00286  -0.0575   0.7982   0.8241
   0.500   0.3145   0.00885   0.00279  -0.0568   0.7852   0.8379
   0.750   0.3407   0.00880   0.00274  -0.0562   0.7722   0.8530
   1.000   0.3669   0.00875   0.00269  -0.0556   0.7581   0.8705
   1.250   0.3942   0.00871   0.00265  -0.0552   0.7442   0.8917
   1.500   0.4252   0.00868   0.00265  -0.0556   0.7309   0.9183
   1.750   0.4622   0.00866   0.00264  -0.0574   0.7165   0.9588
   2.000   0.4952   0.00871   0.00264  -0.0586   0.7011   1.0000
   2.250   0.5217   0.00881   0.00271  -0.0583   0.6847   1.0000
   2.500   0.5481   0.00892   0.00277  -0.0580   0.6666   1.0000
   2.750   0.5744   0.00906   0.00285  -0.0576   0.6464   1.0000
   3.000   0.6003   0.00921   0.00295  -0.0572   0.6229   1.0000
   3.250   0.6259   0.00939   0.00306  -0.0567   0.5955   1.0000
   3.500   0.6509   0.00962   0.00322  -0.0561   0.5623   1.0000
   3.750   0.6751   0.00992   0.00337  -0.0554   0.5217   1.0000
   4.000   0.6981   0.01033   0.00357  -0.0545   0.4705   1.0000
   4.250   0.7197   0.01089   0.00384  -0.0535   0.4087   1.0000
   4.500   0.7405   0.01156   0.00418  -0.0525   0.3408   1.0000
   4.750   0.7624   0.01219   0.00459  -0.0517   0.2902   1.0000
   5.000   0.7859   0.01268   0.00498  -0.0511   0.2615   1.0000
   5.250   0.8099   0.01312   0.00538  -0.0506   0.2395   1.0000
   5.500   0.8336   0.01359   0.00580  -0.0501   0.2140   1.0000
   5.750   0.8570   0.01411   0.00623  -0.0495   0.1801   1.0000
   6.000   0.8792   0.01475   0.00674  -0.0489   0.1395   1.0000
   6.250   0.8992   0.01568   0.00737  -0.0480   0.0918   1.0000
   6.500   0.9201   0.01652   0.00804  -0.0472   0.0641   1.0000
   6.750   0.9425   0.01716   0.00869  -0.0465   0.0532   1.0000
   7.000   0.9646   0.01783   0.00936  -0.0458   0.0444   1.0000
   7.250   0.9872   0.01841   0.01001  -0.0451   0.0371   1.0000
   7.500   1.0088   0.01910   0.01075  -0.0444   0.0313   1.0000
   7.750   1.0305   0.01976   0.01150  -0.0436   0.0228   1.0000
   8.000   1.0510   0.02056   0.01235  -0.0427   0.0154   1.0000
   8.250   1.0704   0.02151   0.01340  -0.0415   0.0112   1.0000
   8.500   1.0886   0.02257   0.01455  -0.0403   0.0091   1.0000
   8.750   1.1046   0.02387   0.01599  -0.0387   0.0081   1.0000
   9.000   1.1206   0.02508   0.01739  -0.0372   0.0075   1.0000
   9.250   1.1365   0.02624   0.01870  -0.0357   0.0066   1.0000
   9.500   1.1515   0.02742   0.02003  -0.0343   0.0061   1.0000
   9.750   1.1644   0.02876   0.02149  -0.0327   0.0053   1.0000
  10.000   1.1703   0.03068   0.02359  -0.0302   0.0049   1.0000
  10.250   1.1767   0.03234   0.02546  -0.0277   0.0048   1.0000
  10.500   1.1813   0.03410   0.02748  -0.0252   0.0048   1.0000
  10.750   1.1843   0.03605   0.02965  -0.0229   0.0047   1.0000
  11.000   1.1848   0.03833   0.03217  -0.0206   0.0046   1.0000
  11.250   1.1839   0.04078   0.03486  -0.0187   0.0045   1.0000
  11.500   1.1801   0.04362   0.03795  -0.0170   0.0044   1.0000
  11.750   1.1751   0.04668   0.04125  -0.0158   0.0044   1.0000
  12.000   1.1670   0.05026   0.04509  -0.0151   0.0044   1.0000
  12.250   1.1576   0.05417   0.04924  -0.0150   0.0043   1.0000
  12.500   1.1458   0.05872   0.05403  -0.0158   0.0044   1.0000
  12.750   1.1324   0.06387   0.05941  -0.0174   0.0044   1.0000
  13.000   1.1169   0.06982   0.06559  -0.0201   0.0044   1.0000
  13.250   1.0997   0.07675   0.07273  -0.0239   0.0044   1.0000
  13.500   1.0832   0.08426   0.08043  -0.0285   0.0044   1.0000
  13.750   1.0641   0.09314   0.08948  -0.0342   0.0044   1.0000
  14.000   1.0449   0.10280   0.09930  -0.0404   0.0045   1.0000
  14.250   1.0243   0.11338   0.11001  -0.0468   0.0046   1.0000
  14.500   1.0035   0.12437   0.12110  -0.0532   0.0047   1.0000
  14.750   0.9805   0.13650   0.13330  -0.0598   0.0048   1.0000
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