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HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il)
Reynolds number: 50,000
Max Cl/Cd: 30.5 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3015-il-50000-n5.txt
Download as CSV file: xf-hq3015-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/15 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3791   0.10405   0.09682  -0.0557   1.0000   0.0693
 -11.000  -0.3907   0.09897   0.09185  -0.0574   1.0000   0.0701
 -10.750  -0.4063   0.09333   0.08631  -0.0594   1.0000   0.0703
 -10.500  -0.4293   0.08657   0.07966  -0.0622   1.0000   0.0703
 -10.250  -0.4614   0.08010   0.07330  -0.0644   1.0000   0.0696
  -9.750  -0.6191   0.06828   0.06137  -0.0614   1.0000   0.0622
  -9.500  -0.6462   0.06589   0.05889  -0.0580   1.0000   0.0622
  -9.250  -0.6631   0.06356   0.05653  -0.0551   1.0000   0.0627
  -9.000  -0.6665   0.06193   0.05493  -0.0529   0.9997   0.0641
  -8.750  -0.6503   0.05914   0.05199  -0.0552   0.9927   0.0670
  -8.500  -0.6430   0.05499   0.04741  -0.0574   0.9846   0.0696
  -8.250  -0.6347   0.05074   0.04249  -0.0590   0.9766   0.0724
  -8.000  -0.6163   0.04762   0.03897  -0.0606   0.9703   0.0760
  -7.750  -0.5959   0.04570   0.03689  -0.0611   0.9640   0.0794
  -7.500  -0.5736   0.04337   0.03411  -0.0622   0.9579   0.0842
  -7.250  -0.5500   0.04105   0.03131  -0.0630   0.9523   0.0882
  -7.000  -0.5264   0.03958   0.02978  -0.0632   0.9462   0.0920
  -6.750  -0.4971   0.03806   0.02792  -0.0644   0.9414   0.0979
  -6.500  -0.4722   0.03662   0.02619  -0.0643   0.9356   0.1021
  -6.250  -0.4457   0.03551   0.02509  -0.0645   0.9300   0.1068
  -6.000  -0.4136   0.03451   0.02381  -0.0656   0.9258   0.1147
  -5.750  -0.3912   0.03366   0.02301  -0.0650   0.9197   0.1208
  -5.500  -0.3639   0.03289   0.02209  -0.0650   0.9141   0.1293
  -5.250  -0.3327   0.03209   0.02132  -0.0661   0.9100   0.1408
  -5.000  -0.3147   0.03147   0.02071  -0.0648   0.9029   0.1515
  -4.750  -0.2884   0.03074   0.02001  -0.0652   0.8974   0.1690
  -4.500  -0.2591   0.02991   0.01928  -0.0661   0.8931   0.1956
  -4.250  -0.2442   0.02921   0.01877  -0.0648   0.8854   0.2288
  -4.000  -0.2174   0.02810   0.01809  -0.0657   0.8805   0.3007
  -3.750  -0.2018   0.02755   0.01841  -0.0637   0.8743   0.4215
  -3.500  -0.1829   0.02780   0.01888  -0.0614   0.8676   0.5190
  -3.250  -0.1537   0.02821   0.01924  -0.0608   0.8631   0.5811
  -3.000  -0.1411   0.02867   0.01962  -0.0576   0.8550   0.6169
  -2.750  -0.1170   0.02912   0.01999  -0.0560   0.8495   0.6532
  -2.500  -0.0974   0.02960   0.02042  -0.0534   0.8435   0.6833
  -2.250  -0.0819   0.02997   0.02072  -0.0505   0.8361   0.7080
  -2.000  -0.0535   0.03018   0.02080  -0.0496   0.8317   0.7298
  -1.750  -0.0413   0.03040   0.02094  -0.0468   0.8233   0.7462
  -1.500  -0.0164   0.03051   0.02092  -0.0458   0.8177   0.7653
  -1.250   0.0038   0.03063   0.02095  -0.0441   0.8114   0.7842
  -1.000   0.0214   0.03072   0.02097  -0.0422   0.8038   0.8007
  -0.750   0.0543   0.03064   0.02077  -0.0427   0.7996   0.8139
  -0.500   0.0667   0.03079   0.02086  -0.0405   0.7903   0.8242
  -0.250   0.0996   0.03070   0.02066  -0.0416   0.7852   0.8341
   0.000   0.1176   0.03084   0.02073  -0.0405   0.7769   0.8445
   0.250   0.1471   0.03082   0.02064  -0.0409   0.7707   0.8543
   0.500   0.1749   0.03086   0.02062  -0.0412   0.7645   0.8653
   0.750   0.1975   0.03100   0.02073  -0.0408   0.7563   0.8771
   1.000   0.2383   0.03085   0.02053  -0.0429   0.7522   0.8876
   1.250   0.2562   0.03124   0.02094  -0.0422   0.7418   0.9018
   1.500   0.3007   0.03113   0.02079  -0.0450   0.7373   0.9137
   1.750   0.3297   0.03153   0.02122  -0.0464   0.7274   0.9298
   2.000   0.3794   0.03139   0.02106  -0.0503   0.7222   0.9445
   2.500   0.4682   0.03125   0.02092  -0.0570   0.7059   0.9994
   2.750   0.4767   0.03151   0.02113  -0.0548   0.6935   1.0000
   3.250   0.5335   0.03133   0.02086  -0.0553   0.6756   1.0000
   3.500   0.5513   0.03168   0.02118  -0.0543   0.6638   1.0000
   3.750   0.5938   0.03118   0.02066  -0.0561   0.6581   1.0000
   4.000   0.6087   0.03165   0.02113  -0.0547   0.6453   1.0000
   4.500   0.6703   0.03140   0.02087  -0.0551   0.6269   1.0000
   4.750   0.6866   0.03181   0.02131  -0.0537   0.6138   1.0000
   5.000   0.7072   0.03205   0.02156  -0.0527   0.6012   1.0000
   5.250   0.7359   0.03189   0.02143  -0.0524   0.5904   1.0000
   5.500   0.7708   0.03140   0.02098  -0.0527   0.5801   1.0000
   5.750   0.7904   0.03159   0.02120  -0.0514   0.5659   1.0000
   6.000   0.8118   0.03169   0.02133  -0.0503   0.5516   1.0000
   6.250   0.8344   0.03174   0.02142  -0.0492   0.5371   1.0000
   6.500   0.8578   0.03177   0.02148  -0.0482   0.5222   1.0000
   6.750   0.8814   0.03181   0.02153  -0.0473   0.5069   1.0000
   7.000   0.9051   0.03188   0.02163  -0.0464   0.4911   1.0000
   7.250   0.9285   0.03199   0.02174  -0.0454   0.4750   1.0000
   7.500   0.9516   0.03217   0.02191  -0.0445   0.4585   1.0000
   7.750   0.9740   0.03242   0.02215  -0.0435   0.4419   1.0000
   8.000   0.9953   0.03280   0.02250  -0.0425   0.4254   1.0000
   8.250   1.0152   0.03329   0.02295  -0.0414   0.4089   1.0000
   8.500   1.0333   0.03392   0.02356  -0.0401   0.3929   1.0000
   8.750   1.0498   0.03468   0.02433  -0.0389   0.3775   1.0000
   9.000   1.0648   0.03555   0.02519  -0.0375   0.3624   1.0000
   9.250   1.0790   0.03651   0.02617  -0.0362   0.3481   1.0000
   9.500   1.0930   0.03754   0.02722  -0.0349   0.3347   1.0000
   9.750   1.1071   0.03859   0.02830  -0.0337   0.3217   1.0000
  10.000   1.1226   0.03960   0.02932  -0.0326   0.3095   1.0000
  10.250   1.1414   0.04047   0.03015  -0.0317   0.2980   1.0000
  10.500   1.1509   0.04188   0.03167  -0.0304   0.2865   1.0000
  10.750   1.1618   0.04329   0.03315  -0.0292   0.2757   1.0000
  11.000   1.1785   0.04436   0.03425  -0.0283   0.2655   1.0000
  11.250   1.1866   0.04593   0.03593  -0.0271   0.2554   1.0000
  11.500   1.1941   0.04763   0.03774  -0.0259   0.2459   1.0000
  11.750   1.2114   0.04864   0.03870  -0.0251   0.2367   1.0000
  12.000   1.2081   0.05111   0.04144  -0.0237   0.2280   1.0000
  12.250   1.2194   0.05254   0.04288  -0.0228   0.2197   1.0000
  12.500   1.2184   0.05501   0.04557  -0.0217   0.2118   1.0000
  12.750   1.2262   0.05676   0.04736  -0.0209   0.2041   1.0000
  13.000   1.2228   0.05953   0.05033  -0.0201   0.1967   1.0000
  13.250   1.2307   0.06137   0.05220  -0.0194   0.1897   1.0000
  13.500   1.2217   0.06493   0.05600  -0.0189   0.1833   1.0000
  13.750   1.2336   0.06629   0.05732  -0.0183   0.1763   1.0000
  14.000   1.2142   0.07130   0.06264  -0.0185   0.1709   1.0000
  14.250   1.2184   0.07363   0.06504  -0.0183   0.1648   1.0000
  14.500   1.2087   0.07785   0.06941  -0.0187   0.1597   1.0000
  14.750   1.1826   0.08457   0.07640  -0.0204   0.1554   1.0000
  15.000   1.2015   0.08490   0.07670  -0.0196   0.1491   1.0000
  15.250   1.1659   0.09362   0.08570  -0.0226   0.1459   1.0000
  15.500   1.0573   0.11755   0.10991  -0.0346   0.1433   1.0000
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