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HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 1,000,000
Max Cl/Cd: 101.02 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2195-il-1000000.txt
Download as CSV file: xf-hq2195-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.1/9.5 AIRFOIL                              
  
 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  -0.5865   0.05469   0.05304  -0.0547   1.0000   0.0116
  -9.250  -0.6191   0.04861   0.04683  -0.0567   1.0000   0.0114
  -9.000  -0.6940   0.02715   0.02405  -0.0586   0.9971   0.0115
  -8.750  -0.6737   0.02112   0.01729  -0.0616   0.9930   0.0121
  -8.500  -0.6438   0.01999   0.01606  -0.0631   0.9896   0.0125
  -8.250  -0.6118   0.01912   0.01508  -0.0647   0.9868   0.0129
  -8.000  -0.5789   0.01825   0.01411  -0.0665   0.9846   0.0134
  -7.750  -0.5465   0.01730   0.01303  -0.0680   0.9820   0.0140
  -7.500  -0.5164   0.01655   0.01215  -0.0689   0.9765   0.0146
  -7.250  -0.4839   0.01567   0.01111  -0.0702   0.9724   0.0151
  -7.000  -0.4523   0.01519   0.01052  -0.0712   0.9666   0.0153
  -6.750  -0.4262   0.01283   0.00793  -0.0716   0.9583   0.0162
  -6.500  -0.3985   0.01222   0.00727  -0.0718   0.9491   0.0168
  -6.250  -0.3711   0.01179   0.00678  -0.0718   0.9396   0.0174
  -6.000  -0.3448   0.01146   0.00640  -0.0715   0.9288   0.0182
  -5.750  -0.3190   0.01098   0.00583  -0.0712   0.9187   0.0187
  -5.500  -0.2930   0.01053   0.00530  -0.0708   0.9094   0.0192
  -5.250  -0.2668   0.01017   0.00486  -0.0705   0.9000   0.0197
  -5.000  -0.2401   0.00990   0.00452  -0.0702   0.8914   0.0200
  -4.750  -0.2154   0.00907   0.00357  -0.0697   0.8827   0.0213
  -4.500  -0.1885   0.00878   0.00326  -0.0696   0.8747   0.0226
  -4.250  -0.1614   0.00857   0.00299  -0.0694   0.8673   0.0238
  -4.000  -0.1340   0.00834   0.00272  -0.0693   0.8604   0.0249
  -3.750  -0.1066   0.00818   0.00250  -0.0691   0.8533   0.0258
  -3.500  -0.0795   0.00784   0.00211  -0.0690   0.8447   0.0291
  -3.250  -0.0523   0.00770   0.00191  -0.0687   0.8353   0.0326
  -3.000  -0.0249   0.00748   0.00171  -0.0686   0.8261   0.0421
  -2.750   0.0024   0.00725   0.00154  -0.0685   0.8183   0.0654
  -2.500   0.0297   0.00700   0.00141  -0.0684   0.8100   0.1036
  -2.250   0.0569   0.00666   0.00127  -0.0685   0.8027   0.1731
  -2.000   0.0829   0.00597   0.00109  -0.0685   0.7955   0.3372
  -1.750   0.1093   0.00549   0.00102  -0.0685   0.7891   0.4777
  -1.500   0.1369   0.00531   0.00098  -0.0685   0.7827   0.5332
  -1.250   0.1644   0.00519   0.00097  -0.0684   0.7771   0.5856
  -1.000   0.1923   0.00510   0.00099  -0.0683   0.7712   0.6237
  -0.750   0.2204   0.00509   0.00099  -0.0682   0.7652   0.6452
  -0.500   0.2483   0.00507   0.00100  -0.0681   0.7595   0.6681
  -0.250   0.2763   0.00505   0.00103  -0.0681   0.7530   0.6917
   0.000   0.3039   0.00506   0.00105  -0.0679   0.7468   0.7116
   0.250   0.3321   0.00504   0.00106  -0.0678   0.7398   0.7236
   0.500   0.3600   0.00507   0.00107  -0.0677   0.7327   0.7331
   0.750   0.3882   0.00505   0.00109  -0.0677   0.7249   0.7420
   1.000   0.4160   0.00509   0.00110  -0.0676   0.7164   0.7509
   1.250   0.4439   0.00509   0.00113  -0.0675   0.7061   0.7600
   1.500   0.4716   0.00510   0.00115  -0.0674   0.6942   0.7693
   1.750   0.4988   0.00516   0.00118  -0.0671   0.6749   0.7795
   2.000   0.5249   0.00525   0.00120  -0.0667   0.6375   0.7904
   2.500   0.5712   0.00608   0.00146  -0.0649   0.4791   0.8152
   2.750   0.5963   0.00636   0.00161  -0.0643   0.4373   0.8297
   3.000   0.6217   0.00657   0.00175  -0.0639   0.4062   0.8453
   3.250   0.6472   0.00675   0.00188  -0.0634   0.3804   0.8621
   3.500   0.6726   0.00691   0.00202  -0.0629   0.3577   0.8804
   3.750   0.6967   0.00709   0.00216  -0.0621   0.3295   0.9025
   4.000   0.7201   0.00723   0.00229  -0.0612   0.3021   0.9400
   4.250   0.7536   0.00746   0.00244  -0.0626   0.2739   1.0000
   4.500   0.7793   0.00779   0.00263  -0.0623   0.2393   1.0000
   4.750   0.8041   0.00820   0.00285  -0.0619   0.2005   1.0000
   5.000   0.8281   0.00871   0.00314  -0.0614   0.1558   1.0000
   5.250   0.8519   0.00924   0.00346  -0.0609   0.1174   1.0000
   5.500   0.8766   0.00966   0.00376  -0.0605   0.0931   1.0000
   5.750   0.9018   0.01002   0.00404  -0.0601   0.0773   1.0000
   6.000   0.9270   0.01037   0.00433  -0.0597   0.0657   1.0000
   6.250   0.9522   0.01071   0.00463  -0.0594   0.0565   1.0000
   6.500   0.9772   0.01107   0.00494  -0.0590   0.0461   1.0000
   6.750   1.0014   0.01153   0.00532  -0.0585   0.0339   1.0000
   7.000   1.0254   0.01199   0.00573  -0.0579   0.0277   1.0000
   7.250   1.0500   0.01238   0.00616  -0.0574   0.0254   1.0000
   7.500   1.0744   0.01276   0.00655  -0.0569   0.0234   1.0000
   7.750   1.0975   0.01330   0.00710  -0.0562   0.0213   1.0000
   8.000   1.1205   0.01384   0.00771  -0.0555   0.0202   1.0000
   8.250   1.1444   0.01424   0.00815  -0.0549   0.0195   1.0000
   8.500   1.1678   0.01467   0.00862  -0.0543   0.0185   1.0000
   8.750   1.1906   0.01514   0.00912  -0.0536   0.0176   1.0000
   9.000   1.2117   0.01579   0.00980  -0.0527   0.0166   1.0000
   9.250   1.2281   0.01691   0.01103  -0.0510   0.0155   1.0000
   9.500   1.2508   0.01732   0.01149  -0.0503   0.0152   1.0000
   9.750   1.2726   0.01780   0.01202  -0.0495   0.0147   1.0000
  10.000   1.2936   0.01832   0.01259  -0.0486   0.0140   1.0000
  10.250   1.3142   0.01884   0.01315  -0.0477   0.0133   1.0000
  10.500   1.3334   0.01947   0.01382  -0.0466   0.0128   1.0000
  10.750   1.3478   0.02047   0.01489  -0.0448   0.0122   1.0000
  11.000   1.3569   0.02188   0.01642  -0.0423   0.0116   1.0000
  11.250   1.3738   0.02244   0.01706  -0.0408   0.0113   1.0000
  11.500   1.3869   0.02314   0.01783  -0.0387   0.0110   1.0000
  11.750   1.3997   0.02381   0.01857  -0.0367   0.0107   1.0000
  12.000   1.4110   0.02458   0.01942  -0.0345   0.0103   1.0000
  12.250   1.4224   0.02536   0.02025  -0.0326   0.0100   1.0000
  12.500   1.4340   0.02612   0.02108  -0.0308   0.0096   1.0000
  12.750   1.4441   0.02703   0.02204  -0.0290   0.0093   1.0000
  13.000   1.4474   0.02849   0.02358  -0.0266   0.0090   1.0000
  13.250   1.4393   0.03098   0.02622  -0.0236   0.0087   1.0000
  13.500   1.4393   0.03296   0.02834  -0.0217   0.0085   1.0000
  13.750   1.4488   0.03416   0.02962  -0.0206   0.0084   1.0000
  14.000   1.4501   0.03619   0.03177  -0.0192   0.0083   1.0000
  14.250   1.4538   0.03807   0.03377  -0.0183   0.0081   1.0000
  14.500   1.4539   0.04042   0.03624  -0.0174   0.0080   1.0000
  14.750   1.4548   0.04281   0.03874  -0.0169   0.0078   1.0000
  15.000   1.4534   0.04557   0.04162  -0.0166   0.0076   1.0000
  15.250   1.4508   0.04864   0.04480  -0.0167   0.0075   1.0000
  15.500   1.4444   0.05235   0.04865  -0.0172   0.0074   1.0000
  15.750   1.4358   0.05664   0.05308  -0.0182   0.0073   1.0000
  16.000   1.4297   0.06089   0.05745  -0.0198   0.0072   1.0000
  16.250   1.4227   0.06564   0.06231  -0.0218   0.0071   1.0000
  16.500   1.4150   0.07085   0.06764  -0.0244   0.0070   1.0000
  16.750   1.3971   0.07818   0.07513  -0.0283   0.0070   1.0000
  17.000   1.3810   0.08556   0.08266  -0.0325   0.0070   1.0000
  17.250   1.3628   0.09360   0.09085  -0.0371   0.0069   1.0000
  17.500   1.3382   0.10312   0.10053  -0.0426   0.0070   1.0000
  17.750   1.3182   0.11198   0.10952  -0.0478   0.0069   1.0000
  18.000   1.2911   0.12265   0.12036  -0.0542   0.0070   1.0000
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