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HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il)
Reynolds number: 50,000
Max Cl/Cd: 35.23 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq159b-il-50000.txt
Download as CSV file: xf-hq159b-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4754   0.09945   0.09265  -0.0013   1.0000   0.3123
  -8.250  -0.4735   0.09652   0.08977  -0.0010   1.0000   0.3289
  -8.000  -0.4805   0.09440   0.08775  -0.0008   1.0000   0.3456
  -7.750  -0.4594   0.09001   0.08335   0.0010   1.0000   0.3707
  -7.500  -0.4485   0.08661   0.07997   0.0025   1.0000   0.3960
  -7.000  -0.4378   0.08046   0.07389   0.0046   1.0000   0.4351
  -6.750  -0.4316   0.07715   0.07063   0.0054   1.0000   0.4505
  -6.500  -0.5369   0.05724   0.05022  -0.0383   1.0000   0.1618
  -6.250  -0.5226   0.05124   0.04403  -0.0387   1.0000   0.1419
  -6.000  -0.5109   0.04605   0.03827  -0.0392   1.0000   0.1292
  -5.750  -0.4967   0.04193   0.03365  -0.0388   1.0000   0.1259
  -5.500  -0.4802   0.03863   0.02992  -0.0379   1.0000   0.1281
  -5.250  -0.4612   0.03534   0.02610  -0.0368   1.0000   0.1283
  -5.000  -0.4404   0.03247   0.02270  -0.0356   1.0000   0.1310
  -4.750  -0.4200   0.03013   0.02011  -0.0344   1.0000   0.1403
  -4.500  -0.3968   0.02795   0.01746  -0.0331   1.0000   0.1470
  -4.250  -0.3748   0.02616   0.01550  -0.0317   1.0000   0.1605
  -4.000  -0.3521   0.02453   0.01377  -0.0303   1.0000   0.1763
  -3.750  -0.3302   0.02293   0.01232  -0.0286   1.0000   0.1974
  -3.500  -0.3090   0.02141   0.01099  -0.0272   1.0000   0.2374
  -3.250  -0.2915   0.01880   0.00959  -0.0256   1.0000   0.3647
  -3.000  -0.3049   0.01795   0.01062  -0.0130   1.0000   0.7441
  -2.750  -0.0690   0.01903   0.01008  -0.0362   1.0000   1.0000
  -2.500  -0.0698   0.01867   0.00967  -0.0335   1.0000   1.0000
  -2.250  -0.0750   0.01838   0.00934  -0.0299   1.0000   1.0000
  -2.000  -0.0845   0.01813   0.00905  -0.0256   1.0000   1.0000
  -1.750  -0.0967   0.01786   0.00875  -0.0209   1.0000   1.0000
  -1.500  -0.1073   0.01758   0.00842  -0.0164   1.0000   1.0000
  -1.250  -0.1080   0.01741   0.00810  -0.0133   1.0000   1.0000
  -1.000  -0.0969   0.01740   0.00789  -0.0120   1.0000   1.0000
  -0.750  -0.0803   0.01748   0.00778  -0.0114   1.0000   1.0000
  -0.500  -0.0616   0.01765   0.00773  -0.0111   1.0000   1.0000
  -0.250  -0.0420   0.01787   0.00777  -0.0109   1.0000   1.0000
   0.000  -0.0219   0.01813   0.00789  -0.0108   1.0000   1.0000
   0.250  -0.0016   0.01844   0.00807  -0.0106   1.0000   1.0000
   0.500   0.0186   0.01879   0.00829  -0.0105   1.0000   1.0000
   0.750   0.0388   0.01918   0.00859  -0.0104   1.0000   1.0000
   1.000   0.0588   0.01961   0.00895  -0.0103   1.0000   1.0000
   1.250   0.0786   0.02009   0.00937  -0.0103   1.0000   1.0000
   1.500   0.0981   0.02062   0.00986  -0.0102   1.0000   1.0000
   1.750   0.1173   0.02119   0.01041  -0.0103   1.0000   1.0000
   2.000   0.1361   0.02183   0.01103  -0.0103   1.0000   1.0000
   2.250   0.1545   0.02252   0.01174  -0.0104   1.0000   1.0000
   2.500   0.1954   0.02370   0.01299  -0.0149   0.9885   1.0000
   2.750   0.2683   0.02524   0.01470  -0.0247   0.9590   1.0000
   3.000   0.3299   0.02629   0.01594  -0.0317   0.9316   1.0000
   3.250   0.3841   0.02708   0.01698  -0.0370   0.9059   1.0000
   3.500   0.4383   0.02764   0.01781  -0.0417   0.8798   1.0000
   3.750   0.4940   0.02794   0.01842  -0.0461   0.8524   1.0000
   4.000   0.5517   0.02785   0.01875  -0.0499   0.8226   1.0000
   4.250   0.6050   0.02734   0.01863  -0.0518   0.7908   1.0000
   4.500   0.6564   0.02630   0.01802  -0.0521   0.7565   1.0000
   4.750   0.6959   0.02493   0.01695  -0.0495   0.7138   1.0000
   5.000   0.7262   0.02363   0.01581  -0.0453   0.6629   1.0000
   5.250   0.7520   0.02277   0.01497  -0.0413   0.6068   1.0000
   5.500   0.7739   0.02236   0.01448  -0.0373   0.5427   1.0000
   5.750   0.7882   0.02237   0.01402  -0.0326   0.4599   1.0000
   6.000   0.7967   0.02336   0.01441  -0.0285   0.3634   1.0000
   6.250   0.8042   0.02594   0.01599  -0.0249   0.2496   1.0000
   6.500   0.8235   0.02881   0.01827  -0.0230   0.1811   1.0000
   6.750   0.8467   0.03085   0.02022  -0.0218   0.1508   1.0000
   7.000   0.8755   0.03348   0.02300  -0.0211   0.1356   1.0000
   7.250   0.9018   0.03632   0.02595  -0.0205   0.1249   1.0000
   7.500   0.9248   0.03905   0.02881  -0.0197   0.1143   1.0000
   7.750   0.9445   0.04285   0.03321  -0.0183   0.1112   1.0000
   8.000   0.9585   0.04676   0.03777  -0.0166   0.1084   1.0000
   8.250   0.9714   0.05026   0.04164  -0.0153   0.1036   1.0000
   8.500   0.9881   0.05482   0.04617  -0.0147   0.1002   1.0000
   8.750   0.9826   0.05928   0.05157  -0.0123   0.1025   1.0000
   9.000   0.9687   0.06500   0.05791  -0.0109   0.1058   1.0000
   9.250   0.9551   0.07051   0.06376  -0.0101   0.1085   1.0000
   9.500   0.9443   0.07583   0.06926  -0.0098   0.1109   1.0000
   9.750   0.9570   0.08175   0.07521  -0.0098   0.1136   1.0000
  10.000   0.8786   0.08786   0.08154  -0.0134   0.1179   1.0000
  10.250   0.8514   0.09646   0.09010  -0.0191   0.1238   1.0000
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