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HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.07 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq159b-il-1000000.txt
Download as CSV file: xf-hq159b-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 B 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  -0.5386   0.08031   0.07873  -0.0245   1.0000   0.0099
  -9.250  -0.5463   0.07351   0.07195  -0.0288   1.0000   0.0099
  -9.000  -0.7299   0.03151   0.02898  -0.0460   1.0000   0.0057
  -8.750  -0.7335   0.02564   0.02251  -0.0441   1.0000   0.0059
  -8.500  -0.7232   0.02268   0.01918  -0.0424   1.0000   0.0061
  -8.250  -0.7085   0.02077   0.01700  -0.0409   1.0000   0.0063
  -8.000  -0.6926   0.01937   0.01540  -0.0392   1.0000   0.0064
  -7.750  -0.6731   0.01817   0.01402  -0.0382   0.9996   0.0065
  -7.500  -0.6415   0.01656   0.01217  -0.0397   0.9972   0.0067
  -7.250  -0.6113   0.01415   0.00942  -0.0411   0.9942   0.0069
  -7.000  -0.5814   0.01273   0.00780  -0.0421   0.9905   0.0072
  -6.750  -0.5490   0.01190   0.00688  -0.0434   0.9872   0.0076
  -6.500  -0.5149   0.01138   0.00631  -0.0450   0.9846   0.0083
  -6.250  -0.4815   0.01079   0.00565  -0.0464   0.9810   0.0089
  -6.000  -0.4502   0.01030   0.00510  -0.0473   0.9750   0.0097
  -5.750  -0.4179   0.00951   0.00419  -0.0484   0.9698   0.0114
  -5.500  -0.3890   0.00920   0.00387  -0.0487   0.9608   0.0134
  -5.250  -0.3609   0.00880   0.00344  -0.0488   0.9516   0.0177
  -5.000  -0.3335   0.00870   0.00333  -0.0486   0.9414   0.0207
  -4.750  -0.3080   0.00837   0.00298  -0.0481   0.9291   0.0263
  -4.500  -0.2815   0.00827   0.00284  -0.0478   0.9170   0.0290
  -4.250  -0.2555   0.00800   0.00250  -0.0473   0.9050   0.0337
  -4.000  -0.2289   0.00784   0.00231  -0.0470   0.8940   0.0385
  -3.750  -0.2023   0.00766   0.00209  -0.0467   0.8837   0.0460
  -3.500  -0.1754   0.00748   0.00190  -0.0465   0.8736   0.0561
  -3.250  -0.1485   0.00728   0.00173  -0.0463   0.8643   0.0727
  -3.000  -0.1217   0.00706   0.00156  -0.0461   0.8557   0.0996
  -2.750  -0.0957   0.00661   0.00138  -0.0460   0.8459   0.1841
  -2.500  -0.0696   0.00622   0.00122  -0.0459   0.8354   0.2647
  -2.250  -0.0443   0.00565   0.00106  -0.0457   0.8254   0.4001
  -2.000  -0.0179   0.00534   0.00097  -0.0455   0.8155   0.4814
  -1.750   0.0088   0.00510   0.00093  -0.0453   0.8053   0.5548
  -1.500   0.0357   0.00497   0.00091  -0.0451   0.7956   0.6089
  -1.250   0.0632   0.00493   0.00089  -0.0449   0.7861   0.6380
  -0.750   0.1186   0.00488   0.00087  -0.0447   0.7660   0.6781
  -0.500   0.1462   0.00489   0.00086  -0.0445   0.7546   0.6945
  -0.250   0.1737   0.00490   0.00085  -0.0443   0.7424   0.7108
   0.000   0.2014   0.00490   0.00086  -0.0442   0.7315   0.7240
   0.250   0.2292   0.00490   0.00087  -0.0441   0.7223   0.7365
   0.500   0.2569   0.00492   0.00089  -0.0440   0.7131   0.7477
   0.750   0.2849   0.00495   0.00090  -0.0440   0.7031   0.7572
   1.000   0.3126   0.00495   0.00093  -0.0439   0.6929   0.7673
   1.250   0.3403   0.00497   0.00096  -0.0438   0.6816   0.7776
   1.500   0.3678   0.00501   0.00099  -0.0436   0.6677   0.7887
   1.750   0.3949   0.00505   0.00103  -0.0434   0.6490   0.8012
   2.250   0.4470   0.00533   0.00112  -0.0426   0.5673   0.8269
   2.500   0.4721   0.00557   0.00121  -0.0421   0.5115   0.8417
   2.750   0.4965   0.00587   0.00134  -0.0415   0.4548   0.8592
   3.000   0.5206   0.00612   0.00149  -0.0408   0.4049   0.8821
   3.250   0.5426   0.00645   0.00166  -0.0396   0.3336   0.9188
   3.500   0.5756   0.00681   0.00185  -0.0410   0.2756   0.9738
   3.750   0.6068   0.00715   0.00203  -0.0420   0.2386   1.0000
   4.000   0.6332   0.00739   0.00220  -0.0418   0.2172   1.0000
   4.250   0.6593   0.00766   0.00238  -0.0416   0.1939   1.0000
   4.500   0.6845   0.00805   0.00259  -0.0413   0.1493   1.0000
   4.750   0.7075   0.00875   0.00297  -0.0407   0.0862   1.0000
   5.000   0.7308   0.00943   0.00337  -0.0401   0.0376   1.0000
   5.250   0.7562   0.00981   0.00372  -0.0398   0.0303   1.0000
   5.500   0.7821   0.01013   0.00408  -0.0394   0.0272   1.0000
   5.750   0.8081   0.01042   0.00440  -0.0392   0.0256   1.0000
   6.000   0.8337   0.01075   0.00476  -0.0388   0.0238   1.0000
   6.250   0.8585   0.01119   0.00523  -0.0384   0.0214   1.0000
   6.500   0.8821   0.01182   0.00595  -0.0377   0.0191   1.0000
   6.750   0.9084   0.01200   0.00613  -0.0376   0.0180   1.0000
   7.000   0.9338   0.01231   0.00647  -0.0373   0.0163   1.0000
   7.250   0.9584   0.01272   0.00687  -0.0369   0.0143   1.0000
   7.500   0.9807   0.01345   0.00768  -0.0360   0.0125   1.0000
   7.750   1.0062   0.01371   0.00796  -0.0358   0.0113   1.0000
   8.000   1.0315   0.01396   0.00819  -0.0355   0.0100   1.0000
   8.250   1.0512   0.01499   0.00931  -0.0343   0.0086   1.0000
   8.500   1.0753   0.01540   0.00977  -0.0338   0.0082   1.0000
   8.750   1.0981   0.01595   0.01038  -0.0332   0.0076   1.0000
   9.000   1.1205   0.01654   0.01102  -0.0325   0.0071   1.0000
   9.250   1.1429   0.01709   0.01162  -0.0318   0.0066   1.0000
   9.500   1.1623   0.01799   0.01260  -0.0307   0.0062   1.0000
   9.750   1.1735   0.01992   0.01474  -0.0285   0.0057   1.0000
  10.000   1.1906   0.02106   0.01601  -0.0271   0.0056   1.0000
  10.250   1.2088   0.02196   0.01702  -0.0260   0.0054   1.0000
  10.500   1.2253   0.02302   0.01821  -0.0246   0.0052   1.0000
  10.750   1.2391   0.02434   0.01968  -0.0229   0.0050   1.0000
  11.000   1.2520   0.02562   0.02110  -0.0212   0.0048   1.0000
  11.250   1.2641   0.02680   0.02241  -0.0194   0.0046   1.0000
  11.500   1.2720   0.02803   0.02377  -0.0170   0.0044   1.0000
  11.750   1.2789   0.02903   0.02488  -0.0145   0.0043   1.0000
  12.000   1.2863   0.02996   0.02589  -0.0123   0.0042   1.0000
  12.250   1.2853   0.03172   0.02780  -0.0096   0.0041   1.0000
  12.500   1.2854   0.03347   0.02967  -0.0074   0.0040   1.0000
  12.750   1.2810   0.03577   0.03212  -0.0055   0.0039   1.0000
  13.000   1.2750   0.03844   0.03497  -0.0040   0.0039   1.0000
  13.250   1.2663   0.04162   0.03832  -0.0032   0.0039   1.0000
  13.500   1.2548   0.04541   0.04228  -0.0030   0.0039   1.0000
  13.750   1.2407   0.04991   0.04695  -0.0038   0.0038   1.0000
  14.000   1.2253   0.05511   0.05233  -0.0055   0.0038   1.0000
  14.250   1.2056   0.06158   0.05900  -0.0085   0.0038   1.0000
  14.500   1.1882   0.06852   0.06609  -0.0126   0.0038   1.0000
  14.750   1.1654   0.07734   0.07511  -0.0181   0.0039   1.0000
  15.000   1.1361   0.08855   0.08652  -0.0253   0.0039   1.0000
  15.250   1.1157   0.09843   0.09652  -0.0314   0.0039   1.0000
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