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HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/9 AIRFOIL (hq159-il)
Reynolds number: 1,000,000
Max Cl/Cd: 79.17 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq159-il-1000000-n5.txt
Download as CSV file: xf-hq159-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.7653   0.03198   0.02957  -0.0472   1.0000   0.0024
  -9.250  -0.7653   0.02734   0.02450  -0.0458   1.0000   0.0024
  -9.000  -0.7590   0.02376   0.02050  -0.0442   1.0000   0.0024
  -8.750  -0.7450   0.02098   0.01734  -0.0432   0.9990   0.0025
  -8.500  -0.7194   0.01878   0.01482  -0.0441   0.9932   0.0025
  -8.250  -0.6915   0.01707   0.01284  -0.0451   0.9884   0.0026
  -8.000  -0.6617   0.01568   0.01123  -0.0462   0.9839   0.0026
  -7.750  -0.6324   0.01464   0.01002  -0.0471   0.9775   0.0027
  -7.500  -0.6010   0.01380   0.00904  -0.0483   0.9716   0.0027
  -7.250  -0.5737   0.01236   0.00739  -0.0487   0.9614   0.0032
  -7.000  -0.5448   0.01189   0.00684  -0.0492   0.9508   0.0035
  -6.750  -0.5174   0.01145   0.00631  -0.0493   0.9380   0.0037
  -6.500  -0.4913   0.01104   0.00581  -0.0490   0.9243   0.0041
  -6.250  -0.4657   0.01064   0.00531  -0.0486   0.9114   0.0045
  -6.000  -0.4400   0.01030   0.00487  -0.0482   0.9000   0.0048
  -5.750  -0.4140   0.01002   0.00450  -0.0479   0.8894   0.0051
  -5.500  -0.3881   0.00960   0.00398  -0.0475   0.8793   0.0056
  -5.250  -0.3620   0.00926   0.00357  -0.0473   0.8701   0.0067
  -5.000  -0.3355   0.00902   0.00326  -0.0470   0.8616   0.0076
  -4.750  -0.3086   0.00880   0.00297  -0.0468   0.8531   0.0083
  -4.500  -0.2817   0.00859   0.00270  -0.0467   0.8455   0.0088
  -4.250  -0.2547   0.00836   0.00240  -0.0465   0.8373   0.0109
  -4.000  -0.2277   0.00812   0.00218  -0.0463   0.8297   0.0171
  -3.750  -0.2006   0.00792   0.00197  -0.0462   0.8217   0.0268
  -3.500  -0.1732   0.00776   0.00181  -0.0461   0.8136   0.0344
  -3.250  -0.1459   0.00762   0.00166  -0.0460   0.8049   0.0428
  -3.000  -0.1188   0.00747   0.00151  -0.0459   0.7945   0.0565
  -2.750  -0.0914   0.00733   0.00138  -0.0458   0.7839   0.0720
  -2.500  -0.0644   0.00710   0.00124  -0.0457   0.7747   0.1075
  -2.000  -0.0104   0.00661   0.00100  -0.0456   0.7555   0.2074
  -1.750   0.0161   0.00632   0.00089  -0.0455   0.7421   0.2764
  -1.500   0.0424   0.00602   0.00078  -0.0454   0.7275   0.3585
  -1.250   0.0690   0.00576   0.00071  -0.0453   0.7146   0.4364
  -1.000   0.0957   0.00554   0.00068  -0.0452   0.7024   0.5088
  -0.750   0.1228   0.00542   0.00066  -0.0450   0.6896   0.5587
  -0.500   0.1497   0.00533   0.00066  -0.0449   0.6759   0.6062
  -0.250   0.1771   0.00533   0.00067  -0.0447   0.6614   0.6311
   0.000   0.2046   0.00535   0.00067  -0.0446   0.6452   0.6493
   0.250   0.2322   0.00537   0.00069  -0.0445   0.6309   0.6653
   0.500   0.2597   0.00541   0.00071  -0.0444   0.6151   0.6796
   0.750   0.2870   0.00545   0.00074  -0.0443   0.5971   0.6963
   1.000   0.3143   0.00552   0.00077  -0.0442   0.5764   0.7096
   1.250   0.3416   0.00561   0.00082  -0.0440   0.5534   0.7186
   1.500   0.3686   0.00573   0.00087  -0.0439   0.5271   0.7271
   1.750   0.3954   0.00590   0.00094  -0.0437   0.4944   0.7364
   2.000   0.4217   0.00611   0.00103  -0.0435   0.4543   0.7455
   2.250   0.4475   0.00639   0.00115  -0.0432   0.4058   0.7550
   2.750   0.4980   0.00708   0.00146  -0.0425   0.2927   0.7763
   3.000   0.5235   0.00739   0.00163  -0.0422   0.2508   0.7878
   3.250   0.5499   0.00756   0.00177  -0.0420   0.2301   0.7998
   3.500   0.5764   0.00770   0.00191  -0.0418   0.2152   0.8123
   3.750   0.6028   0.00784   0.00205  -0.0415   0.1997   0.8256
   4.000   0.6282   0.00809   0.00223  -0.0411   0.1686   0.8402
   4.250   0.6528   0.00839   0.00243  -0.0406   0.1346   0.8578
   4.500   0.6753   0.00881   0.00272  -0.0398   0.0871   0.8838
   4.750   0.7017   0.00900   0.00298  -0.0395   0.0650   0.9490
   5.000   0.7366   0.00932   0.00324  -0.0413   0.0491   1.0000
   5.250   0.7621   0.00964   0.00349  -0.0410   0.0371   1.0000
   5.500   0.7877   0.00995   0.00375  -0.0408   0.0275   1.0000
   5.750   0.8131   0.01027   0.00403  -0.0404   0.0199   1.0000
   6.000   0.8384   0.01061   0.00435  -0.0401   0.0145   1.0000
   6.250   0.8628   0.01106   0.00475  -0.0396   0.0056   1.0000
   6.500   0.8877   0.01145   0.00514  -0.0392   0.0040   1.0000
   6.750   0.9126   0.01184   0.00556  -0.0388   0.0032   1.0000
   7.000   0.9373   0.01225   0.00603  -0.0383   0.0028   1.0000
   7.250   0.9617   0.01269   0.00653  -0.0378   0.0025   1.0000
   7.500   0.9862   0.01308   0.00697  -0.0374   0.0023   1.0000
   7.750   1.0104   0.01351   0.00747  -0.0369   0.0022   1.0000
   8.000   1.0341   0.01400   0.00802  -0.0363   0.0021   1.0000
   8.250   1.0573   0.01453   0.00862  -0.0357   0.0020   1.0000
   8.500   1.0801   0.01511   0.00928  -0.0350   0.0019   1.0000
   8.750   1.1027   0.01568   0.00992  -0.0343   0.0018   1.0000
   9.000   1.1246   0.01633   0.01064  -0.0335   0.0017   1.0000
   9.250   1.1460   0.01700   0.01139  -0.0327   0.0016   1.0000
   9.500   1.1668   0.01772   0.01220  -0.0318   0.0015   1.0000
   9.750   1.1874   0.01842   0.01297  -0.0310   0.0014   1.0000
  10.000   1.2062   0.01931   0.01399  -0.0298   0.0014   1.0000
  10.250   1.2245   0.02020   0.01498  -0.0287   0.0013   1.0000
  10.500   1.2400   0.02136   0.01626  -0.0272   0.0012   1.0000
  10.750   1.2429   0.02377   0.01896  -0.0241   0.0010   1.0000
  11.000   1.2546   0.02507   0.02040  -0.0222   0.0010   1.0000
  11.250   1.2674   0.02611   0.02156  -0.0205   0.0010   1.0000
  11.500   1.2769   0.02710   0.02266  -0.0182   0.0010   1.0000
  11.750   1.2784   0.02854   0.02425  -0.0150   0.0010   1.0000
  12.000   1.2817   0.02990   0.02573  -0.0124   0.0010   1.0000
  12.250   1.2810   0.03165   0.02764  -0.0099   0.0010   1.0000
  12.500   1.2811   0.03346   0.02959  -0.0078   0.0009   1.0000
  12.750   1.2750   0.03597   0.03227  -0.0060   0.0010   1.0000
  13.000   1.2703   0.03857   0.03503  -0.0048   0.0009   1.0000
  13.250   1.2646   0.04152   0.03813  -0.0041   0.0009   1.0000
  13.500   1.2514   0.04560   0.04238  -0.0043   0.0009   1.0000
  13.750   1.2426   0.04960   0.04654  -0.0051   0.0009   1.0000
  14.000   1.2273   0.05495   0.05207  -0.0071   0.0009   1.0000
  14.250   1.2110   0.06112   0.05840  -0.0102   0.0009   1.0000
  14.500   1.1889   0.06924   0.06670  -0.0150   0.0009   1.0000
  14.750   1.1707   0.07751   0.07510  -0.0202   0.0009   1.0000
  15.000   1.1421   0.08894   0.08672  -0.0273   0.0009   1.0000
  15.250   1.1127   0.10080   0.09872  -0.0342   0.0010   1.0000
  15.500   1.0775   0.11410   0.11214  -0.0415   0.0010   1.0000
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