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HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/9 AIRFOIL (hq159-il)
Reynolds number: 100,000
Max Cl/Cd: 49.33 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq159-il-100000-n5.txt
Download as CSV file: xf-hq159-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5110   0.08916   0.08425  -0.0237   1.0000   0.0219
  -9.000  -0.5136   0.08421   0.07937  -0.0264   1.0000   0.0216
  -8.750  -0.5173   0.07907   0.07429  -0.0296   1.0000   0.0213
  -8.500  -0.5230   0.07345   0.06874  -0.0339   1.0000   0.0210
  -8.250  -0.5344   0.06784   0.06315  -0.0384   1.0000   0.0207
  -8.000  -0.5426   0.06258   0.05782  -0.0411   1.0000   0.0205
  -7.750  -0.5468   0.05788   0.05299  -0.0427   1.0000   0.0201
  -7.500  -0.5493   0.05301   0.04792  -0.0435   1.0000   0.0199
  -7.250  -0.5486   0.04832   0.04296  -0.0435   1.0000   0.0198
  -7.000  -0.5446   0.04394   0.03825  -0.0429   1.0000   0.0197
  -6.750  -0.5377   0.03989   0.03381  -0.0419   1.0000   0.0196
  -6.500  -0.5280   0.03609   0.02955  -0.0405   1.0000   0.0198
  -6.250  -0.5154   0.03274   0.02572  -0.0390   1.0000   0.0202
  -6.000  -0.5005   0.02981   0.02233  -0.0373   1.0000   0.0207
  -5.750  -0.4835   0.02744   0.01950  -0.0357   1.0000   0.0218
  -5.500  -0.4656   0.02554   0.01723  -0.0341   1.0000   0.0242
  -5.250  -0.4482   0.02394   0.01551  -0.0328   1.0000   0.0264
  -5.000  -0.4292   0.02243   0.01381  -0.0313   1.0000   0.0281
  -4.750  -0.4099   0.02106   0.01222  -0.0298   1.0000   0.0304
  -4.500  -0.3906   0.01987   0.01084  -0.0282   1.0000   0.0336
  -4.250  -0.3576   0.01876   0.00970  -0.0298   0.9947   0.0424
  -4.000  -0.3247   0.01771   0.00858  -0.0312   0.9886   0.0559
  -3.750  -0.2911   0.01686   0.00774  -0.0328   0.9830   0.0782
  -3.500  -0.2585   0.01605   0.00699  -0.0342   0.9764   0.1080
  -3.250  -0.2252   0.01506   0.00636  -0.0361   0.9710   0.1891
  -3.000  -0.1971   0.01384   0.00595  -0.0371   0.9638   0.3756
  -2.750  -0.1661   0.01321   0.00602  -0.0377   0.9586   0.5667
  -2.500  -0.1377   0.01310   0.00603  -0.0374   0.9506   0.6470
  -2.250  -0.1048   0.01308   0.00600  -0.0379   0.9452   0.7052
  -2.000  -0.0782   0.01307   0.00601  -0.0370   0.9368   0.7512
  -1.750  -0.0463   0.01303   0.00595  -0.0372   0.9312   0.7851
  -1.500  -0.0194   0.01299   0.00587  -0.0366   0.9225   0.8125
  -1.250   0.0126   0.01292   0.00573  -0.0368   0.9166   0.8390
  -1.000   0.0415   0.01285   0.00561  -0.0368   0.9081   0.8589
  -0.750   0.0752   0.01277   0.00547  -0.0377   0.9014   0.8749
  -0.500   0.1084   0.01269   0.00536  -0.0386   0.8933   0.8910
  -0.250   0.1444   0.01263   0.00524  -0.0400   0.8856   0.9074
   0.000   0.1839   0.01256   0.00514  -0.0422   0.8781   0.9244
   0.250   0.2232   0.01251   0.00508  -0.0445   0.8695   0.9435
   0.500   0.2661   0.01243   0.00497  -0.0475   0.8624   0.9615
   0.750   0.3060   0.01237   0.00490  -0.0501   0.8511   0.9839
   1.000   0.3398   0.01230   0.00480  -0.0513   0.8373   1.0000
   1.250   0.3635   0.01227   0.00472  -0.0503   0.8212   1.0000
   1.500   0.3863   0.01229   0.00468  -0.0491   0.8034   1.0000
   1.750   0.4105   0.01232   0.00468  -0.0483   0.7873   1.0000
   2.000   0.4356   0.01238   0.00473  -0.0476   0.7728   1.0000
   2.250   0.4609   0.01244   0.00479  -0.0470   0.7580   1.0000
   2.500   0.4864   0.01251   0.00490  -0.0463   0.7423   1.0000
   2.750   0.5120   0.01258   0.00498  -0.0456   0.7256   1.0000
   3.000   0.5372   0.01268   0.00510  -0.0449   0.7064   1.0000
   3.250   0.5625   0.01277   0.00521  -0.0441   0.6855   1.0000
   3.500   0.5875   0.01288   0.00539  -0.0433   0.6614   1.0000
   3.750   0.6123   0.01301   0.00552  -0.0424   0.6328   1.0000
   4.000   0.6364   0.01318   0.00566  -0.0414   0.5960   1.0000
   4.250   0.6597   0.01343   0.00579  -0.0401   0.5477   1.0000
   4.500   0.6817   0.01382   0.00596  -0.0388   0.4869   1.0000
   4.750   0.7024   0.01441   0.00630  -0.0374   0.4195   1.0000
   5.000   0.7227   0.01512   0.00672  -0.0362   0.3547   1.0000
   5.250   0.7432   0.01588   0.00722  -0.0351   0.2997   1.0000
   5.500   0.7640   0.01665   0.00780  -0.0342   0.2562   1.0000
   5.750   0.7859   0.01735   0.00843  -0.0334   0.2170   1.0000
   6.000   0.8074   0.01810   0.00909  -0.0326   0.1754   1.0000
   6.250   0.8276   0.01905   0.00989  -0.0317   0.1298   1.0000
   6.500   0.8474   0.02010   0.01081  -0.0307   0.1012   1.0000
   6.750   0.8671   0.02118   0.01186  -0.0296   0.0840   1.0000
   7.000   0.8869   0.02224   0.01293  -0.0286   0.0709   1.0000
   7.250   0.9061   0.02339   0.01418  -0.0274   0.0622   1.0000
   7.500   0.9237   0.02474   0.01555  -0.0262   0.0546   1.0000
   7.750   0.9436   0.02572   0.01666  -0.0253   0.0443   1.0000
   8.000   0.9634   0.02670   0.01777  -0.0245   0.0338   1.0000
   8.250   0.9795   0.02833   0.01965  -0.0230   0.0269   1.0000
   8.500   0.9937   0.03015   0.02157  -0.0215   0.0222   1.0000
   8.750   1.0079   0.03240   0.02405  -0.0198   0.0197   1.0000
   9.000   1.0236   0.03426   0.02617  -0.0184   0.0169   1.0000
   9.250   1.0369   0.03582   0.02789  -0.0171   0.0149   1.0000
   9.500   1.0461   0.03812   0.03037  -0.0156   0.0137   1.0000
   9.750   1.0529   0.04121   0.03375  -0.0137   0.0132   1.0000
  10.000   1.0580   0.04417   0.03710  -0.0118   0.0128   1.0000
  10.250   1.0568   0.04723   0.04052  -0.0094   0.0126   1.0000
  10.500   1.0502   0.05049   0.04411  -0.0070   0.0124   1.0000
  10.750   1.0400   0.05395   0.04788  -0.0052   0.0123   1.0000
  11.000   1.0264   0.05788   0.05210  -0.0043   0.0122   1.0000
  11.250   1.0110   0.06226   0.05674  -0.0045   0.0122   1.0000
  11.500   0.9940   0.06727   0.06198  -0.0059   0.0123   1.0000
  11.750   0.9756   0.07313   0.06804  -0.0088   0.0123   1.0000
  12.000   0.9567   0.07989   0.07498  -0.0129   0.0124   1.0000
  12.250   0.9371   0.08789   0.08312  -0.0185   0.0126   1.0000
  12.500   0.9170   0.09726   0.09261  -0.0251   0.0128   1.0000
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