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HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/9 AIRFOIL (hq159-il)
Reynolds number: 50,000
Max Cl/Cd: 35.66 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq159-il-50000-n5.txt
Download as CSV file: xf-hq159-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5057   0.09619   0.08928  -0.0222   1.0000   0.0430
  -9.000  -0.5072   0.09156   0.08473  -0.0247   1.0000   0.0428
  -8.750  -0.5100   0.08674   0.07999  -0.0277   1.0000   0.0428
  -8.500  -0.5136   0.08179   0.07511  -0.0310   1.0000   0.0420
  -8.250  -0.5212   0.07655   0.06994  -0.0348   1.0000   0.0410
  -8.000  -0.5286   0.07169   0.06509  -0.0377   1.0000   0.0409
  -7.750  -0.5340   0.06692   0.06025  -0.0399   1.0000   0.0400
  -7.500  -0.5373   0.06232   0.05553  -0.0414   1.0000   0.0400
  -7.250  -0.5377   0.05790   0.05090  -0.0422   1.0000   0.0400
  -7.000  -0.5346   0.05364   0.04638  -0.0425   1.0000   0.0399
  -6.750  -0.5285   0.04955   0.04196  -0.0423   1.0000   0.0398
  -6.500  -0.5196   0.04566   0.03767  -0.0417   1.0000   0.0400
  -6.250  -0.5079   0.04206   0.03365  -0.0408   1.0000   0.0404
  -6.000  -0.4936   0.03876   0.02989  -0.0396   1.0000   0.0412
  -5.750  -0.4768   0.03574   0.02638  -0.0384   1.0000   0.0425
  -5.500  -0.4578   0.03310   0.02321  -0.0370   1.0000   0.0452
  -5.250  -0.4392   0.03096   0.02081  -0.0358   1.0000   0.0498
  -5.000  -0.4194   0.02919   0.01874  -0.0345   1.0000   0.0549
  -4.750  -0.3976   0.02732   0.01648  -0.0328   1.0000   0.0596
  -4.500  -0.3786   0.02591   0.01507  -0.0314   1.0000   0.0703
  -4.250  -0.3593   0.02451   0.01361  -0.0297   1.0000   0.0813
  -4.000  -0.3401   0.02338   0.01235  -0.0282   1.0000   0.0999
  -3.750  -0.3210   0.02211   0.01115  -0.0269   1.0000   0.1196
  -3.500  -0.3017   0.02094   0.01014  -0.0260   1.0000   0.1588
  -3.250  -0.2827   0.01939   0.00913  -0.0254   1.0000   0.2499
  -3.000  -0.2710   0.01786   0.00902  -0.0226   1.0000   0.5180
  -2.750  -0.2591   0.01770   0.00914  -0.0185   1.0000   0.6524
  -2.500  -0.2475   0.01768   0.00918  -0.0144   1.0000   0.7304
  -2.250  -0.2371   0.01764   0.00917  -0.0098   1.0000   0.7983
  -2.000  -0.2227   0.01752   0.00907  -0.0058   1.0000   0.8661
  -1.750  -0.1717   0.01751   0.00881  -0.0091   1.0000   0.9422
  -1.500  -0.1120   0.01749   0.00844  -0.0161   1.0000   1.0000
  -1.250  -0.0965   0.01744   0.00817  -0.0158   0.9962   1.0000
  -1.000  -0.0591   0.01760   0.00806  -0.0191   0.9865   1.0000
  -0.750  -0.0224   0.01779   0.00797  -0.0221   0.9768   1.0000
  -0.500   0.0146   0.01801   0.00798  -0.0249   0.9675   1.0000
  -0.250   0.0538   0.01826   0.00806  -0.0281   0.9588   1.0000
   0.000   0.0886   0.01848   0.00811  -0.0302   0.9483   1.0000
   0.250   0.1245   0.01871   0.00823  -0.0325   0.9383   1.0000
   0.500   0.1632   0.01895   0.00839  -0.0352   0.9290   1.0000
   0.750   0.2006   0.01916   0.00856  -0.0376   0.9189   1.0000
   1.000   0.2355   0.01939   0.00875  -0.0394   0.9080   1.0000
   1.250   0.2718   0.01960   0.00896  -0.0414   0.8975   1.0000
   1.500   0.3086   0.01980   0.00917  -0.0434   0.8872   1.0000
   1.750   0.3458   0.01995   0.00939  -0.0452   0.8763   1.0000
   2.000   0.3800   0.02002   0.00951  -0.0461   0.8613   1.0000
   2.250   0.4119   0.02002   0.00957  -0.0464   0.8425   1.0000
   2.500   0.4457   0.01992   0.00956  -0.0466   0.8240   1.0000
   2.750   0.4782   0.01986   0.00964  -0.0467   0.8071   1.0000
   3.000   0.5042   0.01996   0.00984  -0.0460   0.7883   1.0000
   3.250   0.5323   0.01998   0.00998  -0.0454   0.7699   1.0000
   3.500   0.5608   0.01996   0.01008  -0.0447   0.7508   1.0000
   3.750   0.5861   0.02000   0.01033  -0.0435   0.7282   1.0000
   4.000   0.6117   0.02000   0.01048  -0.0423   0.7035   1.0000
   4.250   0.6370   0.02000   0.01061  -0.0409   0.6756   1.0000
   4.500   0.6622   0.01998   0.01071  -0.0394   0.6431   1.0000
   4.750   0.6857   0.02003   0.01084  -0.0376   0.6025   1.0000
   5.000   0.7082   0.02015   0.01103  -0.0357   0.5520   1.0000
   5.250   0.7293   0.02045   0.01118  -0.0335   0.4912   1.0000
   5.500   0.7484   0.02107   0.01153  -0.0315   0.4252   1.0000
   5.750   0.7658   0.02196   0.01213  -0.0296   0.3613   1.0000
   6.000   0.7825   0.02303   0.01294  -0.0280   0.3040   1.0000
   6.250   0.7988   0.02426   0.01393  -0.0265   0.2527   1.0000
   6.500   0.8152   0.02556   0.01518  -0.0252   0.2032   1.0000
   6.750   0.8324   0.02697   0.01647  -0.0239   0.1639   1.0000
   7.000   0.8499   0.02850   0.01789  -0.0227   0.1354   1.0000
   7.250   0.8682   0.03003   0.01939  -0.0216   0.1128   1.0000
   7.500   0.8887   0.03177   0.02121  -0.0205   0.0996   1.0000
   7.750   0.9088   0.03353   0.02307  -0.0196   0.0868   1.0000
   8.000   0.9288   0.03544   0.02513  -0.0186   0.0758   1.0000
   8.250   0.9508   0.03787   0.02762  -0.0178   0.0683   1.0000
   8.500   0.9682   0.04027   0.03042  -0.0165   0.0584   1.0000
   8.750   0.9842   0.04332   0.03386  -0.0153   0.0517   1.0000
   9.000   0.9945   0.04556   0.03629  -0.0140   0.0444   1.0000
   9.250   1.0016   0.04882   0.04003  -0.0124   0.0394   1.0000
   9.500   1.0064   0.05187   0.04346  -0.0108   0.0356   1.0000
   9.750   1.0095   0.05458   0.04635  -0.0094   0.0331   1.0000
  10.000   1.0084   0.05812   0.04999  -0.0081   0.0314   1.0000
  10.250   0.9990   0.06188   0.05415  -0.0062   0.0311   1.0000
  10.500   0.9852   0.06585   0.05844  -0.0048   0.0308   1.0000
  10.750   0.9699   0.07013   0.06296  -0.0046   0.0308   1.0000
  11.000   0.9519   0.07504   0.06810  -0.0056   0.0308   1.0000
  11.250   0.9341   0.08050   0.07374  -0.0079   0.0309   1.0000
  11.500   0.9168   0.08659   0.07996  -0.0112   0.0311   1.0000
  11.750   0.8993   0.09358   0.08704  -0.0156   0.0313   1.0000
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