Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 2.1/9.5 AIRFOIL (hq2195-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.1/9.5 AIRFOIL (hq2195-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.99 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2195-il-1000000-n5.txt
Download as CSV file: xf-hq2195-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -1.0067   0.04417   0.04189  -0.0659   1.0000   0.0061
 -14.000  -1.0338   0.03770   0.03518  -0.0705   1.0000   0.0061
 -13.750  -1.0466   0.03429   0.03162  -0.0713   1.0000   0.0061
 -13.500  -1.0541   0.03225   0.02947  -0.0698   1.0000   0.0062
 -13.250  -1.0486   0.03062   0.02773  -0.0688   1.0000   0.0063
 -13.000  -1.0392   0.02917   0.02618  -0.0679   1.0000   0.0064
 -12.750  -1.0274   0.02785   0.02475  -0.0670   1.0000   0.0066
 -12.500  -1.0142   0.02659   0.02337  -0.0662   1.0000   0.0067
 -12.250  -0.9991   0.02550   0.02217  -0.0653   1.0000   0.0069
 -12.000  -0.9836   0.02438   0.02093  -0.0644   1.0000   0.0071
 -11.750  -0.9660   0.02351   0.01996  -0.0635   1.0000   0.0073
 -11.500  -0.9487   0.02254   0.01887  -0.0626   1.0000   0.0075
 -11.250  -0.9317   0.02152   0.01772  -0.0615   1.0000   0.0077
 -11.000  -0.9121   0.02065   0.01673  -0.0608   0.9998   0.0079
 -10.750  -0.8834   0.01973   0.01567  -0.0620   0.9972   0.0081
 -10.500  -0.8563   0.01855   0.01437  -0.0630   0.9930   0.0084
 -10.250  -0.8277   0.01792   0.01366  -0.0638   0.9889   0.0087
 -10.000  -0.7970   0.01737   0.01306  -0.0650   0.9855   0.0089
  -9.750  -0.7655   0.01680   0.01242  -0.0663   0.9825   0.0092
  -9.500  -0.7360   0.01626   0.01181  -0.0672   0.9772   0.0095
  -9.250  -0.7047   0.01566   0.01113  -0.0684   0.9723   0.0098
  -9.000  -0.6736   0.01508   0.01045  -0.0695   0.9666   0.0102
  -8.750  -0.6430   0.01460   0.00988  -0.0705   0.9588   0.0106
  -8.500  -0.6134   0.01415   0.00934  -0.0712   0.9498   0.0108
  -8.250  -0.5852   0.01373   0.00881  -0.0715   0.9392   0.0110
  -8.000  -0.5607   0.01286   0.00781  -0.0713   0.9268   0.0115
  -7.750  -0.5351   0.01240   0.00727  -0.0710   0.9155   0.0118
  -7.500  -0.5091   0.01206   0.00687  -0.0708   0.9054   0.0121
  -7.250  -0.4830   0.01179   0.00653  -0.0705   0.8957   0.0125
  -7.000  -0.4568   0.01148   0.00616  -0.0703   0.8862   0.0130
  -6.750  -0.4307   0.01114   0.00573  -0.0701   0.8776   0.0134
  -6.500  -0.4045   0.01080   0.00531  -0.0698   0.8687   0.0137
  -6.250  -0.3780   0.01048   0.00492  -0.0696   0.8606   0.0141
  -6.000  -0.3514   0.01020   0.00456  -0.0694   0.8528   0.0144
  -5.750  -0.3243   0.00997   0.00428  -0.0693   0.8459   0.0146
  -5.500  -0.2980   0.00954   0.00377  -0.0692   0.8389   0.0153
  -5.250  -0.2710   0.00924   0.00343  -0.0691   0.8327   0.0159
  -5.000  -0.2437   0.00900   0.00315  -0.0690   0.8262   0.0163
  -4.750  -0.2164   0.00880   0.00289  -0.0689   0.8203   0.0169
  -4.500  -0.1888   0.00859   0.00266  -0.0688   0.8141   0.0175
  -4.250  -0.1612   0.00842   0.00244  -0.0688   0.8082   0.0182
  -4.000  -0.1334   0.00826   0.00224  -0.0688   0.8032   0.0188
  -3.750  -0.1056   0.00810   0.00204  -0.0687   0.7973   0.0198
  -3.500  -0.0781   0.00794   0.00186  -0.0686   0.7890   0.0219
  -3.250  -0.0507   0.00782   0.00170  -0.0685   0.7780   0.0240
  -3.000  -0.0230   0.00771   0.00156  -0.0684   0.7679   0.0277
  -2.750   0.0047   0.00759   0.00144  -0.0684   0.7597   0.0342
  -2.500   0.0324   0.00747   0.00133  -0.0683   0.7507   0.0448
  -2.250   0.0602   0.00734   0.00123  -0.0683   0.7430   0.0587
  -2.000   0.0880   0.00721   0.00114  -0.0683   0.7355   0.0789
  -1.750   0.1158   0.00702   0.00106  -0.0683   0.7286   0.1158
  -1.500   0.1434   0.00678   0.00097  -0.0684   0.7213   0.1739
  -1.250   0.1703   0.00628   0.00085  -0.0686   0.7155   0.3061
  -1.000   0.1970   0.00574   0.00080  -0.0687   0.7089   0.4623
  -0.750   0.2248   0.00564   0.00078  -0.0686   0.7024   0.5017
  -0.500   0.2526   0.00551   0.00077  -0.0686   0.6950   0.5486
  -0.250   0.2801   0.00540   0.00080  -0.0685   0.6869   0.6039
   0.000   0.3078   0.00535   0.00084  -0.0685   0.6776   0.6451
   0.250   0.3358   0.00535   0.00085  -0.0684   0.6663   0.6623
   0.500   0.3636   0.00539   0.00087  -0.0683   0.6517   0.6725
   0.750   0.3910   0.00546   0.00089  -0.0681   0.6302   0.6808
   1.000   0.4176   0.00562   0.00092  -0.0678   0.5897   0.6888
   1.250   0.4427   0.00594   0.00100  -0.0673   0.5295   0.6959
   1.500   0.4682   0.00624   0.00112  -0.0669   0.4806   0.7031
   1.750   0.4937   0.00656   0.00125  -0.0665   0.4295   0.7097
   2.000   0.5189   0.00691   0.00139  -0.0661   0.3778   0.7173
   2.250   0.5452   0.00714   0.00150  -0.0659   0.3445   0.7244
   2.500   0.5716   0.00735   0.00162  -0.0656   0.3171   0.7319
   2.750   0.5986   0.00748   0.00172  -0.0655   0.3017   0.7397
   3.000   0.6256   0.00762   0.00184  -0.0653   0.2868   0.7489
   3.250   0.6523   0.00776   0.00196  -0.0651   0.2711   0.7582
   3.500   0.6786   0.00796   0.00210  -0.0649   0.2491   0.7681
   3.750   0.7034   0.00831   0.00230  -0.0644   0.2066   0.7799
   4.000   0.7278   0.00869   0.00254  -0.0639   0.1653   0.7934
   4.250   0.7523   0.00905   0.00279  -0.0634   0.1325   0.8082
   4.500   0.7768   0.00940   0.00304  -0.0629   0.1048   0.8241
   4.750   0.8017   0.00967   0.00328  -0.0624   0.0859   0.8412
   5.000   0.8266   0.00990   0.00351  -0.0618   0.0736   0.8593
   5.250   0.8513   0.01011   0.00374  -0.0613   0.0647   0.8795
   5.500   0.8751   0.01029   0.00396  -0.0605   0.0575   0.9048
   5.750   0.9047   0.01040   0.00418  -0.0609   0.0517   0.9728
   6.000   0.9305   0.01071   0.00445  -0.0607   0.0438   1.0000
   6.250   0.9559   0.01103   0.00472  -0.0603   0.0361   1.0000
   6.500   0.9809   0.01138   0.00503  -0.0600   0.0291   1.0000
   6.750   1.0060   0.01172   0.00534  -0.0596   0.0246   1.0000
   7.000   1.0308   0.01207   0.00569  -0.0592   0.0220   1.0000
   7.250   1.0556   0.01242   0.00604  -0.0587   0.0200   1.0000
   7.500   1.0805   0.01273   0.00638  -0.0583   0.0191   1.0000
   7.750   1.1051   0.01308   0.00675  -0.0579   0.0183   1.0000
   8.000   1.1293   0.01346   0.00715  -0.0574   0.0173   1.0000
   8.250   1.1529   0.01388   0.00758  -0.0568   0.0163   1.0000
   8.500   1.1759   0.01436   0.00810  -0.0561   0.0154   1.0000
   8.750   1.1998   0.01472   0.00850  -0.0556   0.0149   1.0000
   9.000   1.2233   0.01510   0.00892  -0.0551   0.0144   1.0000
   9.250   1.2464   0.01551   0.00938  -0.0544   0.0139   1.0000
   9.500   1.2690   0.01594   0.00985  -0.0537   0.0133   1.0000
   9.750   1.2912   0.01640   0.01033  -0.0530   0.0127   1.0000
  10.000   1.3125   0.01693   0.01088  -0.0522   0.0120   1.0000
  10.250   1.3327   0.01753   0.01153  -0.0512   0.0113   1.0000
  10.500   1.3542   0.01797   0.01203  -0.0503   0.0110   1.0000
  10.750   1.3749   0.01845   0.01257  -0.0494   0.0106   1.0000
  11.000   1.3950   0.01895   0.01312  -0.0484   0.0101   1.0000
  11.250   1.4144   0.01948   0.01370  -0.0473   0.0096   1.0000
  11.500   1.4329   0.02005   0.01430  -0.0462   0.0091   1.0000
  11.750   1.4499   0.02070   0.01498  -0.0448   0.0085   1.0000
  12.000   1.4649   0.02132   0.01566  -0.0430   0.0082   1.0000
  12.250   1.4786   0.02192   0.01634  -0.0410   0.0078   1.0000
  12.500   1.4913   0.02257   0.01705  -0.0390   0.0074   1.0000
  12.750   1.5029   0.02330   0.01785  -0.0369   0.0071   1.0000
  13.000   1.5140   0.02409   0.01869  -0.0349   0.0067   1.0000
  13.250   1.5239   0.02499   0.01964  -0.0328   0.0064   1.0000
  13.500   1.5320   0.02605   0.02077  -0.0308   0.0060   1.0000
  13.750   1.5400   0.02714   0.02195  -0.0289   0.0059   1.0000
  14.000   1.5477   0.02830   0.02320  -0.0271   0.0057   1.0000
  14.250   1.5543   0.02961   0.02460  -0.0254   0.0055   1.0000
  14.500   1.5602   0.03102   0.02612  -0.0238   0.0054   1.0000
  14.750   1.5647   0.03261   0.02781  -0.0223   0.0052   1.0000
  15.000   1.5682   0.03438   0.02967  -0.0210   0.0050   1.0000
  15.250   1.5711   0.03627   0.03166  -0.0199   0.0049   1.0000
  15.500   1.5722   0.03844   0.03392  -0.0189   0.0048   1.0000
  15.750   1.5722   0.04082   0.03641  -0.0182   0.0046   1.0000
  16.000   1.5701   0.04354   0.03923  -0.0178   0.0045   1.0000
  16.250   1.5663   0.04661   0.04242  -0.0176   0.0043   1.0000
  16.500   1.5600   0.05017   0.04609  -0.0179   0.0043   1.0000
  16.750   1.5496   0.05450   0.05056  -0.0187   0.0041   1.0000
  17.000   1.5382   0.05933   0.05554  -0.0202   0.0041   1.0000
  17.250   1.5248   0.06490   0.06126  -0.0224   0.0040   1.0000
  17.500   1.5102   0.07117   0.06768  -0.0255   0.0040   1.0000
  17.750   1.4942   0.07810   0.07477  -0.0291   0.0040   1.0000
  18.000   1.4703   0.08687   0.08370  -0.0340   0.0040   1.0000
  18.250   1.4459   0.09606   0.09306  -0.0393   0.0040   1.0000
  18.500   1.4137   0.10706   0.10424  -0.0457   0.0040   1.0000
  18.750   1.3832   0.11806   0.11541  -0.0522   0.0041   1.0000
  19.000   1.3508   0.12981   0.12733  -0.0592   0.0041   1.0000
  19.250   1.3207   0.14150   0.13917  -0.0663   0.0042   1.0000
<< Back to HQ 2.1/9.5 AIRFOIL (hq2195-il)

Polar data table (+)

Polar graphs


<< Back to HQ 2.1/9.5 AIRFOIL (hq2195-il)