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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 100,000
Max Cl/Cd: 54.29 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2010-il-100000.txt
Download as CSV file: xf-hq2010-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3545   0.09133   0.08677  -0.0297   1.0000   0.1127
  -9.000  -0.3640   0.08760   0.08311  -0.0320   1.0000   0.1176
  -8.750  -0.3974   0.08374   0.07938  -0.0380   1.0000   0.1193
  -8.500  -0.3637   0.07936   0.07497  -0.0329   1.0000   0.1241
  -8.250  -0.3668   0.07576   0.07142  -0.0336   1.0000   0.1296
  -8.000  -0.4033   0.07180   0.06762  -0.0384   1.0000   0.1328
  -7.750  -0.3854   0.06770   0.06353  -0.0352   1.0000   0.1373
  -7.500  -0.3910   0.06455   0.06046  -0.0345   1.0000   0.1422
  -7.250  -0.4207   0.06130   0.05736  -0.0354   1.0000   0.1447
  -7.000  -0.4686   0.05834   0.05438  -0.0373   1.0000   0.1469
  -6.750  -0.4584   0.05468   0.05085  -0.0335   1.0000   0.1507
  -6.500  -0.5037   0.06100   0.05672  -0.0369   1.0000   0.1523
  -6.250  -0.5154   0.05820   0.05376  -0.0367   1.0000   0.1632
  -6.000  -0.5080   0.05568   0.05133  -0.0338   1.0000   0.1687
  -5.750  -0.5000   0.03917   0.03283  -0.0391   1.0000   0.0672
  -5.500  -0.4843   0.03568   0.02893  -0.0376   1.0000   0.0617
  -5.250  -0.4677   0.03231   0.02512  -0.0365   1.0000   0.0595
  -5.000  -0.4486   0.02965   0.02198  -0.0353   1.0000   0.0603
  -4.750  -0.4278   0.02781   0.01961  -0.0341   1.0000   0.0635
  -4.500  -0.4055   0.02561   0.01695  -0.0330   1.0000   0.0657
  -4.250  -0.3830   0.02355   0.01481  -0.0323   1.0000   0.0700
  -4.000  -0.3606   0.02245   0.01346  -0.0313   1.0000   0.0791
  -3.750  -0.3386   0.02111   0.01211  -0.0304   1.0000   0.0907
  -3.500  -0.3173   0.02000   0.01101  -0.0296   1.0000   0.1071
  -3.250  -0.2967   0.01905   0.01024  -0.0287   1.0000   0.1276
  -3.000  -0.2758   0.01816   0.00951  -0.0278   1.0000   0.1537
  -2.750  -0.2548   0.01700   0.00885  -0.0273   1.0000   0.2250
  -2.500  -0.2396   0.01537   0.00926  -0.0247   0.9982   0.6491
  -2.250  -0.2116   0.01582   0.00977  -0.0237   0.9911   0.7383
  -2.000  -0.1836   0.01621   0.01015  -0.0229   0.9838   0.7932
  -1.750  -0.1590   0.01640   0.01030  -0.0215   0.9760   0.8377
  -1.500  -0.1304   0.01660   0.01048  -0.0206   0.9694   0.8859
  -1.250  -0.0901   0.01670   0.01055  -0.0221   0.9636   0.9427
  -1.000  -0.0064   0.01704   0.01067  -0.0329   0.9621   0.9864
  -0.750   0.0464   0.01723   0.01065  -0.0393   0.9564   1.0000
  -0.500   0.0749   0.01725   0.01055  -0.0411   0.9450   1.0000
  -0.250   0.1109   0.01735   0.01052  -0.0439   0.9345   1.0000
   0.000   0.1588   0.01751   0.01055  -0.0486   0.9273   1.0000
   0.250   0.1883   0.01767   0.01062  -0.0499   0.9167   1.0000
   0.500   0.2249   0.01787   0.01073  -0.0523   0.9079   1.0000
   0.750   0.2724   0.01793   0.01074  -0.0562   0.9001   1.0000
   1.000   0.3130   0.01791   0.01068  -0.0587   0.8884   1.0000
   1.250   0.3603   0.01766   0.01042  -0.0619   0.8763   1.0000
   1.500   0.4034   0.01739   0.01015  -0.0641   0.8647   1.0000
   1.750   0.4485   0.01708   0.00985  -0.0666   0.8566   1.0000
   2.000   0.4772   0.01710   0.00987  -0.0665   0.8443   1.0000
   2.250   0.5062   0.01708   0.00990  -0.0663   0.8320   1.0000
   2.500   0.5356   0.01702   0.00986  -0.0661   0.8197   1.0000
   2.750   0.5650   0.01690   0.00978  -0.0657   0.8069   1.0000
   3.000   0.5938   0.01675   0.00967  -0.0651   0.7936   1.0000
   3.250   0.6221   0.01656   0.00956  -0.0643   0.7792   1.0000
   3.500   0.6499   0.01635   0.00940  -0.0633   0.7638   1.0000
   3.750   0.6779   0.01608   0.00917  -0.0623   0.7471   1.0000
   4.000   0.7059   0.01578   0.00891  -0.0611   0.7289   1.0000
   4.250   0.7308   0.01558   0.00880  -0.0596   0.7054   1.0000
   4.500   0.7561   0.01536   0.00861  -0.0581   0.6787   1.0000
   4.750   0.7814   0.01516   0.00838  -0.0565   0.6468   1.0000
   5.000   0.8043   0.01509   0.00826  -0.0546   0.6048   1.0000
   5.250   0.8258   0.01521   0.00827  -0.0526   0.5528   1.0000
   5.500   0.8460   0.01559   0.00839  -0.0507   0.4964   1.0000
   5.750   0.8654   0.01616   0.00870  -0.0489   0.4428   1.0000
   6.000   0.8847   0.01690   0.00917  -0.0473   0.3981   1.0000
   6.250   0.9042   0.01767   0.00978  -0.0459   0.3587   1.0000
   6.500   0.9230   0.01846   0.01044  -0.0445   0.3221   1.0000
   6.750   0.9414   0.01932   0.01120  -0.0431   0.2848   1.0000
   7.000   0.9574   0.02038   0.01210  -0.0414   0.2421   1.0000
   7.250   0.9709   0.02163   0.01309  -0.0394   0.1929   1.0000
   7.500   0.9853   0.02299   0.01419  -0.0375   0.1557   1.0000
   7.750   1.0031   0.02445   0.01554  -0.0360   0.1330   1.0000
   8.000   1.0220   0.02590   0.01689  -0.0348   0.1178   1.0000
   8.250   1.0433   0.02748   0.01854  -0.0339   0.1065   1.0000
   8.500   1.0677   0.02948   0.02054  -0.0334   0.0985   1.0000
   8.750   1.0912   0.03130   0.02240  -0.0328   0.0907   1.0000
   9.000   1.1121   0.03340   0.02477  -0.0318   0.0830   1.0000
   9.250   1.1294   0.03544   0.02687  -0.0308   0.0737   1.0000
   9.500   1.1402   0.03683   0.02827  -0.0293   0.0625   1.0000
   9.750   1.1510   0.03864   0.03040  -0.0272   0.0542   1.0000
  10.000   1.1605   0.04252   0.03468  -0.0251   0.0480   1.0000
  10.250   1.1685   0.04497   0.03744  -0.0231   0.0434   1.0000
  10.500   1.1755   0.04952   0.04204  -0.0221   0.0399   1.0000
  10.750   1.1698   0.05189   0.04494  -0.0186   0.0387   1.0000
  11.000   1.1603   0.05498   0.04844  -0.0153   0.0378   1.0000
  11.250   1.1463   0.05832   0.05212  -0.0122   0.0374   1.0000
  11.500   1.1302   0.06198   0.05608  -0.0099   0.0374   1.0000
  11.750   1.1111   0.06604   0.06042  -0.0085   0.0374   1.0000
  12.000   1.0900   0.07061   0.06524  -0.0083   0.0374   1.0000
  12.250   1.0692   0.07568   0.07052  -0.0092   0.0377   1.0000
  12.500   1.0472   0.08145   0.07647  -0.0112   0.0381   1.0000
  12.750   1.0243   0.08798   0.08316  -0.0145   0.0384   1.0000
  13.000   1.0013   0.09543   0.09075  -0.0189   0.0389   1.0000
  13.250   0.9808   0.10348   0.09888  -0.0236   0.0395   1.0000
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