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HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/9 AIRFOIL (hq109-il)
Reynolds number: 50,000
Max Cl/Cd: 33.15 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq109-il-50000-n5.txt
Download as CSV file: xf-hq109-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/9 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5703   0.10111   0.09417  -0.0155   1.0000   0.0369
  -9.750  -0.5703   0.09625   0.08936  -0.0177   1.0000   0.0367
  -9.500  -0.5728   0.09065   0.08382  -0.0211   1.0000   0.0366
  -9.250  -0.5758   0.08512   0.07833  -0.0246   1.0000   0.0363
  -9.000  -0.5824   0.07970   0.07295  -0.0283   1.0000   0.0361
  -8.750  -0.5918   0.07496   0.06822  -0.0312   1.0000   0.0358
  -8.500  -0.6019   0.07050   0.06373  -0.0331   1.0000   0.0356
  -8.250  -0.6098   0.06587   0.05897  -0.0346   1.0000   0.0356
  -8.000  -0.6153   0.06127   0.05415  -0.0356   1.0000   0.0359
  -7.750  -0.6165   0.05684   0.04940  -0.0360   1.0000   0.0363
  -7.500  -0.6143   0.05268   0.04475  -0.0360   1.0000   0.0371
  -7.250  -0.6067   0.04896   0.04093  -0.0357   1.0000   0.0387
  -7.000  -0.5951   0.04586   0.03761  -0.0351   1.0000   0.0404
  -6.750  -0.5824   0.04230   0.03363  -0.0343   1.0000   0.0412
  -6.500  -0.5671   0.03894   0.02982  -0.0333   1.0000   0.0425
  -6.250  -0.5491   0.03585   0.02624  -0.0322   1.0000   0.0443
  -6.000  -0.5289   0.03311   0.02299  -0.0309   1.0000   0.0473
  -5.750  -0.5092   0.03100   0.02067  -0.0299   1.0000   0.0533
  -5.500  -0.4875   0.02906   0.01845  -0.0286   1.0000   0.0597
  -5.250  -0.4661   0.02715   0.01642  -0.0271   1.0000   0.0668
  -5.000  -0.4459   0.02575   0.01487  -0.0258   1.0000   0.0806
  -4.750  -0.4261   0.02432   0.01337  -0.0242   1.0000   0.0947
  -4.500  -0.4071   0.02310   0.01213  -0.0227   1.0000   0.1170
  -4.250  -0.3884   0.02183   0.01093  -0.0213   1.0000   0.1432
  -4.000  -0.3701   0.02048   0.00989  -0.0204   1.0000   0.1969
  -3.750  -0.3555   0.01884   0.00897  -0.0189   1.0000   0.3044
  -3.500  -0.3450   0.01770   0.00889  -0.0156   1.0000   0.5052
  -3.250  -0.3322   0.01750   0.00891  -0.0117   1.0000   0.6244
  -3.000  -0.3198   0.01748   0.00896  -0.0076   1.0000   0.6996
  -2.750  -0.3079   0.01749   0.00897  -0.0034   1.0000   0.7588
  -2.500  -0.2948   0.01746   0.00888   0.0005   1.0000   0.8073
  -2.250  -0.2773   0.01739   0.00870   0.0033   1.0000   0.8473
  -2.000  -0.2505   0.01736   0.00854   0.0043   1.0000   0.8892
  -1.750  -0.1983   0.01745   0.00834   0.0004   1.0000   0.9337
  -1.500  -0.1438   0.01745   0.00806  -0.0052   1.0000   0.9632
  -1.250  -0.0963   0.01736   0.00775  -0.0102   1.0000   0.9862
  -1.000  -0.0800   0.01724   0.00747  -0.0101   1.0000   1.0000
  -0.750  -0.0676   0.01723   0.00732  -0.0092   0.9957   1.0000
  -0.500  -0.0293   0.01740   0.00733  -0.0126   0.9848   1.0000
  -0.250   0.0083   0.01759   0.00737  -0.0157   0.9737   1.0000
   0.000   0.0451   0.01778   0.00743  -0.0185   0.9625   1.0000
   0.250   0.0823   0.01799   0.00755  -0.0212   0.9515   1.0000
   0.500   0.1206   0.01820   0.00770  -0.0240   0.9410   1.0000
   0.750   0.1614   0.01840   0.00789  -0.0271   0.9310   1.0000
   1.000   0.1981   0.01859   0.00806  -0.0294   0.9192   1.0000
   1.250   0.2349   0.01878   0.00827  -0.0315   0.9074   1.0000
   1.500   0.2700   0.01897   0.00850  -0.0332   0.8955   1.0000
   1.750   0.3042   0.01916   0.00878  -0.0347   0.8834   1.0000
   2.000   0.3401   0.01924   0.00894  -0.0360   0.8676   1.0000
   2.250   0.3784   0.01916   0.00895  -0.0371   0.8490   1.0000
   2.500   0.4072   0.01915   0.00908  -0.0367   0.8272   1.0000
   2.750   0.4374   0.01916   0.00919  -0.0364   0.8087   1.0000
   3.000   0.4637   0.01924   0.00939  -0.0356   0.7892   1.0000
   3.250   0.4900   0.01929   0.00957  -0.0346   0.7689   1.0000
   3.500   0.5155   0.01933   0.00975  -0.0334   0.7465   1.0000
   3.750   0.5410   0.01932   0.00994  -0.0321   0.7220   1.0000
   4.000   0.5649   0.01933   0.01010  -0.0304   0.6928   1.0000
   4.250   0.5885   0.01932   0.01021  -0.0286   0.6583   1.0000
   4.500   0.6114   0.01933   0.01030  -0.0266   0.6155   1.0000
   4.750   0.6331   0.01943   0.01040  -0.0244   0.5616   1.0000
   5.000   0.6537   0.01972   0.01060  -0.0222   0.4941   1.0000
   5.250   0.6724   0.02034   0.01091  -0.0200   0.4183   1.0000
   5.500   0.6901   0.02128   0.01154  -0.0182   0.3461   1.0000
   5.750   0.7071   0.02245   0.01239  -0.0166   0.2860   1.0000
   6.000   0.7245   0.02374   0.01348  -0.0153   0.2326   1.0000
   6.250   0.7420   0.02510   0.01467  -0.0142   0.1839   1.0000
   6.500   0.7597   0.02658   0.01596  -0.0130   0.1467   1.0000
   6.750   0.7781   0.02812   0.01753  -0.0119   0.1160   1.0000
   7.000   0.7970   0.02984   0.01921  -0.0108   0.0951   1.0000
   7.250   0.8166   0.03168   0.02110  -0.0097   0.0782   1.0000
   7.500   0.8374   0.03383   0.02330  -0.0087   0.0669   1.0000
   7.750   0.8562   0.03580   0.02544  -0.0077   0.0558   1.0000
   8.000   0.8789   0.03879   0.02887  -0.0066   0.0499   1.0000
   8.250   0.8946   0.04105   0.03123  -0.0057   0.0436   1.0000
   8.500   0.9094   0.04429   0.03500  -0.0044   0.0395   1.0000
   8.750   0.9207   0.04801   0.03924  -0.0030   0.0375   1.0000
   9.000   0.9274   0.05162   0.04327  -0.0016   0.0357   1.0000
   9.250   0.9310   0.05492   0.04688  -0.0003   0.0340   1.0000
   9.500   0.9331   0.05787   0.04995   0.0007   0.0321   1.0000
   9.750   0.9280   0.06184   0.05410   0.0017   0.0313   1.0000
  10.000   0.9138   0.06567   0.05827   0.0031   0.0309   1.0000
  10.250   0.8986   0.06967   0.06249   0.0037   0.0309   1.0000
  10.500   0.8810   0.07430   0.06731   0.0027   0.0309   1.0000
  10.750   0.8654   0.07943   0.07257   0.0006   0.0311   1.0000
  11.000   0.8497   0.08522   0.07845  -0.0026   0.0313   1.0000
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