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HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il)
Reynolds number: 100,000
Max Cl/Cd: 51.34 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq159b-il-100000.txt
Download as CSV file: xf-hq159b-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4191   0.09993   0.09527  -0.0172   1.0000   0.1039
  -9.500  -0.4370   0.09596   0.09138  -0.0216   1.0000   0.1061
  -9.250  -0.5089   0.09884   0.09393  -0.0169   1.0000   0.0976
  -9.000  -0.5096   0.09538   0.09052  -0.0188   1.0000   0.1038
  -8.750  -0.5252   0.09122   0.08650  -0.0246   1.0000   0.1059
  -8.500  -0.5091   0.08774   0.08299  -0.0214   1.0000   0.1129
  -8.250  -0.5153   0.08398   0.07931  -0.0242   1.0000   0.1174
  -8.000  -0.5347   0.07904   0.07447  -0.0310   1.0000   0.1192
  -7.750  -0.5611   0.07440   0.06968  -0.0388   1.0000   0.1206
  -7.500  -0.5355   0.07111   0.06657  -0.0339   1.0000   0.1324
  -7.250  -0.5328   0.06716   0.06264  -0.0342   1.0000   0.1388
  -7.000  -0.5427   0.06309   0.05840  -0.0378   1.0000   0.1496
  -6.500  -0.5227   0.05694   0.05234  -0.0349   1.0000   0.1698
  -6.250  -0.5178   0.05387   0.04923  -0.0343   1.0000   0.1839
  -6.000  -0.5070   0.03807   0.03095  -0.0385   1.0000   0.0661
  -5.750  -0.4916   0.03402   0.02675  -0.0372   1.0000   0.0635
  -5.500  -0.4755   0.03079   0.02311  -0.0355   1.0000   0.0626
  -5.250  -0.4572   0.02924   0.02091  -0.0335   1.0000   0.0656
  -5.000  -0.4398   0.02594   0.01750  -0.0324   1.0000   0.0694
  -4.750  -0.4196   0.02405   0.01537  -0.0309   1.0000   0.0735
  -4.500  -0.3990   0.02242   0.01343  -0.0295   1.0000   0.0814
  -4.250  -0.3781   0.02098   0.01192  -0.0283   1.0000   0.0888
  -4.000  -0.3573   0.01964   0.01051  -0.0271   1.0000   0.0987
  -3.750  -0.3360   0.01853   0.00932  -0.0257   1.0000   0.1079
  -3.500  -0.3162   0.01747   0.00841  -0.0246   1.0000   0.1235
  -3.250  -0.2959   0.01654   0.00764  -0.0234   1.0000   0.1435
  -3.000  -0.2755   0.01546   0.00694  -0.0225   1.0000   0.2010
  -2.750  -0.2669   0.01334   0.00706  -0.0188   1.0000   0.6483
  -2.500  -0.2561   0.01346   0.00733  -0.0145   1.0000   0.7372
  -2.250  -0.2447   0.01355   0.00745  -0.0107   1.0000   0.7893
  -2.000  -0.2339   0.01359   0.00750  -0.0067   1.0000   0.8346
  -1.750  -0.2229   0.01358   0.00751  -0.0027   1.0000   0.8822
  -1.500  -0.1857   0.01365   0.00754  -0.0035   1.0000   0.9526
  -1.250  -0.1249   0.01379   0.00745  -0.0109   1.0000   1.0000
  -1.000  -0.1079   0.01376   0.00726  -0.0111   0.9979   1.0000
  -0.750  -0.0630   0.01407   0.00736  -0.0159   0.9896   1.0000
  -0.500  -0.0170   0.01446   0.00758  -0.0207   0.9824   1.0000
  -0.250   0.0225   0.01472   0.00771  -0.0241   0.9735   1.0000
   0.000   0.0646   0.01505   0.00792  -0.0278   0.9657   1.0000
   0.250   0.1068   0.01536   0.00815  -0.0314   0.9574   1.0000
   0.500   0.1445   0.01564   0.00836  -0.0341   0.9480   1.0000
   0.750   0.1909   0.01592   0.00861  -0.0383   0.9404   1.0000
   1.000   0.2368   0.01603   0.00872  -0.0420   0.9286   1.0000
   1.250   0.2935   0.01586   0.00858  -0.0471   0.9145   1.0000
   1.500   0.3471   0.01557   0.00836  -0.0513   0.9005   1.0000
   1.750   0.3862   0.01548   0.00831  -0.0531   0.8877   1.0000
   2.000   0.4215   0.01544   0.00832  -0.0541   0.8752   1.0000
   2.250   0.4551   0.01538   0.00836  -0.0547   0.8624   1.0000
   2.500   0.4868   0.01531   0.00836  -0.0548   0.8488   1.0000
   2.750   0.5166   0.01522   0.00836  -0.0544   0.8341   1.0000
   3.000   0.5451   0.01511   0.00832  -0.0536   0.8182   1.0000
   3.250   0.5728   0.01497   0.00830  -0.0525   0.8016   1.0000
   3.500   0.5977   0.01488   0.00830  -0.0510   0.7817   1.0000
   3.750   0.6234   0.01462   0.00811  -0.0492   0.7591   1.0000
   4.000   0.6475   0.01429   0.00780  -0.0469   0.7295   1.0000
   4.250   0.6698   0.01409   0.00767  -0.0445   0.6921   1.0000
   4.500   0.6927   0.01398   0.00756  -0.0424   0.6496   1.0000
   4.750   0.7139   0.01396   0.00740  -0.0400   0.5884   1.0000
   5.000   0.7326   0.01427   0.00736  -0.0375   0.5027   1.0000
   5.250   0.7508   0.01502   0.00770  -0.0355   0.4226   1.0000
   5.500   0.7700   0.01581   0.00823  -0.0340   0.3537   1.0000
   5.750   0.7869   0.01688   0.00891  -0.0323   0.2779   1.0000
   6.000   0.7975   0.01898   0.01008  -0.0300   0.1415   1.0000
   6.250   0.8122   0.02102   0.01172  -0.0279   0.1040   1.0000
   6.500   0.8315   0.02271   0.01331  -0.0265   0.0902   1.0000
   6.750   0.8533   0.02434   0.01497  -0.0254   0.0796   1.0000
   7.000   0.8779   0.02666   0.01716  -0.0248   0.0732   1.0000
   7.250   0.9018   0.02814   0.01889  -0.0239   0.0660   1.0000
   7.500   0.9278   0.03145   0.02212  -0.0237   0.0613   1.0000
   7.750   0.9500   0.03351   0.02472  -0.0223   0.0583   1.0000
   8.000   0.9701   0.03571   0.02726  -0.0211   0.0538   1.0000
   8.250   0.9889   0.03889   0.03081  -0.0198   0.0526   1.0000
   8.500   1.0023   0.04274   0.03526  -0.0179   0.0526   1.0000
   8.750   1.0075   0.04749   0.04073  -0.0155   0.0541   1.0000
   9.000   1.0088   0.05217   0.04594  -0.0133   0.0550   1.0000
   9.250   1.0055   0.05683   0.05104  -0.0113   0.0557   1.0000
   9.500   0.9972   0.06163   0.05620  -0.0094   0.0568   1.0000
   9.750   0.9858   0.06639   0.06123  -0.0080   0.0582   1.0000
  10.000   0.9727   0.07091   0.06590  -0.0066   0.0592   1.0000
  10.250   0.8636   0.06865   0.06416  -0.0018   0.0641   1.0000
  10.500   0.8070   0.07777   0.07349  -0.0067   0.0664   1.0000
  10.750   0.7647   0.08878   0.08457  -0.0140   0.0679   1.0000
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