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HQ 1.5/9 AIRFOIL (hq159-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/9 AIRFOIL (hq159-il)
Reynolds number: 500,000
Max Cl/Cd: 72.05 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq159-il-500000-n5.txt
Download as CSV file: xf-hq159-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5385   0.08581   0.08357  -0.0213   1.0000   0.0046
  -9.500  -0.5455   0.07999   0.07778  -0.0246   1.0000   0.0046
  -9.250  -0.5534   0.07406   0.07189  -0.0284   1.0000   0.0045
  -9.000  -0.5700   0.06553   0.06342  -0.0356   1.0000   0.0044
  -8.750  -0.5908   0.05828   0.05615  -0.0421   1.0000   0.0043
  -8.500  -0.6065   0.05097   0.04867  -0.0450   1.0000   0.0043
  -8.250  -0.6248   0.04177   0.03914  -0.0458   1.0000   0.0041
  -8.000  -0.6501   0.02970   0.02624  -0.0435   1.0000   0.0040
  -7.750  -0.6460   0.02508   0.02107  -0.0413   1.0000   0.0040
  -7.500  -0.6203   0.02136   0.01679  -0.0426   0.9941   0.0042
  -7.250  -0.5925   0.01899   0.01402  -0.0436   0.9885   0.0045
  -7.000  -0.5616   0.01733   0.01204  -0.0448   0.9845   0.0048
  -6.750  -0.5323   0.01616   0.01065  -0.0455   0.9783   0.0051
  -6.500  -0.5018   0.01464   0.00890  -0.0466   0.9730   0.0055
  -6.250  -0.4727   0.01361   0.00775  -0.0473   0.9657   0.0061
  -6.000  -0.4412   0.01297   0.00703  -0.0483   0.9592   0.0067
  -5.750  -0.4116   0.01253   0.00654  -0.0489   0.9504   0.0078
  -5.500  -0.3820   0.01203   0.00593  -0.0494   0.9416   0.0087
  -5.000  -0.3273   0.01076   0.00440  -0.0493   0.9205   0.0108
  -4.750  -0.3004   0.01039   0.00396  -0.0492   0.9104   0.0125
  -4.500  -0.2735   0.01011   0.00360  -0.0489   0.9010   0.0148
  -4.250  -0.2473   0.00973   0.00321  -0.0486   0.8913   0.0224
  -4.000  -0.2207   0.00947   0.00294  -0.0484   0.8821   0.0326
  -3.750  -0.1939   0.00926   0.00268  -0.0481   0.8734   0.0414
  -3.500  -0.1672   0.00906   0.00247  -0.0479   0.8647   0.0530
  -3.250  -0.1406   0.00879   0.00226  -0.0477   0.8562   0.0779
  -3.000  -0.1142   0.00851   0.00206  -0.0476   0.8483   0.1122
  -2.750  -0.0877   0.00819   0.00188  -0.0474   0.8395   0.1604
  -2.500  -0.0615   0.00785   0.00169  -0.0473   0.8310   0.2247
  -2.250  -0.0360   0.00738   0.00151  -0.0471   0.8216   0.3207
  -2.000  -0.0103   0.00695   0.00139  -0.0469   0.8116   0.4231
  -1.750   0.0159   0.00668   0.00131  -0.0466   0.8022   0.4967
  -1.500   0.0421   0.00649   0.00127  -0.0463   0.7936   0.5609
  -1.250   0.0689   0.00638   0.00125  -0.0460   0.7833   0.6041
  -1.000   0.0954   0.00631   0.00124  -0.0456   0.7712   0.6447
  -0.750   0.1222   0.00629   0.00122  -0.0452   0.7577   0.6698
  -0.500   0.1493   0.00628   0.00120  -0.0449   0.7450   0.6876
  -0.250   0.1764   0.00628   0.00119  -0.0447   0.7325   0.7037
   0.000   0.2035   0.00629   0.00119  -0.0444   0.7195   0.7204
   0.250   0.2305   0.00631   0.00119  -0.0441   0.7051   0.7356
   0.500   0.2577   0.00633   0.00120  -0.0439   0.6906   0.7464
   0.750   0.2849   0.00637   0.00121  -0.0437   0.6766   0.7558
   1.000   0.3122   0.00641   0.00123  -0.0435   0.6629   0.7658
   1.250   0.3393   0.00646   0.00127  -0.0433   0.6477   0.7760
   1.500   0.3662   0.00651   0.00131  -0.0430   0.6307   0.7864
   1.750   0.3929   0.00658   0.00136  -0.0427   0.6117   0.7976
   2.000   0.4194   0.00666   0.00142  -0.0424   0.5893   0.8097
   2.250   0.4454   0.00677   0.00148  -0.0420   0.5628   0.8226
   2.500   0.4708   0.00692   0.00158  -0.0415   0.5284   0.8365
   2.750   0.4951   0.00716   0.00169  -0.0408   0.4803   0.8520
   3.000   0.5188   0.00744   0.00183  -0.0400   0.4290   0.8710
   3.250   0.5420   0.00775   0.00201  -0.0391   0.3734   0.8978
   3.500   0.5711   0.00825   0.00226  -0.0397   0.2963   0.9445
   3.750   0.6065   0.00865   0.00249  -0.0417   0.2547   1.0000
   4.000   0.6325   0.00890   0.00269  -0.0415   0.2357   1.0000
   4.250   0.6584   0.00916   0.00289  -0.0412   0.2171   1.0000
   4.500   0.6838   0.00949   0.00312  -0.0409   0.1893   1.0000
   4.750   0.7082   0.00993   0.00340  -0.0405   0.1497   1.0000
   5.000   0.7318   0.01047   0.00373  -0.0401   0.1075   1.0000
   5.250   0.7557   0.01100   0.00410  -0.0396   0.0750   1.0000
   5.500   0.7799   0.01147   0.00446  -0.0391   0.0552   1.0000
   5.750   0.8050   0.01183   0.00480  -0.0388   0.0453   1.0000
   6.000   0.8300   0.01219   0.00517  -0.0384   0.0373   1.0000
   6.250   0.8545   0.01260   0.00556  -0.0380   0.0286   1.0000
   6.500   0.8791   0.01301   0.00596  -0.0376   0.0227   1.0000
   6.750   0.9031   0.01348   0.00640  -0.0371   0.0154   1.0000
   7.000   0.9262   0.01407   0.00696  -0.0365   0.0075   1.0000
   7.250   0.9493   0.01466   0.00757  -0.0358   0.0052   1.0000
   7.500   0.9725   0.01524   0.00822  -0.0351   0.0045   1.0000
   7.750   0.9955   0.01582   0.00890  -0.0344   0.0042   1.0000
   8.000   1.0180   0.01647   0.00968  -0.0336   0.0040   1.0000
   8.250   1.0398   0.01716   0.01047  -0.0328   0.0037   1.0000
   8.500   1.0610   0.01791   0.01133  -0.0320   0.0034   1.0000
   8.750   1.0814   0.01873   0.01224  -0.0311   0.0030   1.0000
   9.000   1.0999   0.01977   0.01341  -0.0299   0.0027   1.0000
   9.250   1.1162   0.02105   0.01485  -0.0284   0.0026   1.0000
   9.500   1.1309   0.02244   0.01641  -0.0267   0.0025   1.0000
   9.750   1.1489   0.02337   0.01746  -0.0256   0.0024   1.0000
  10.000   1.1631   0.02467   0.01893  -0.0239   0.0024   1.0000
  10.250   1.1773   0.02588   0.02032  -0.0224   0.0023   1.0000
  10.500   1.1890   0.02725   0.02187  -0.0205   0.0022   1.0000
  10.750   1.1985   0.02865   0.02345  -0.0184   0.0021   1.0000
  11.000   1.2017   0.03028   0.02526  -0.0155   0.0021   1.0000
  11.250   1.2035   0.03198   0.02715  -0.0128   0.0021   1.0000
  11.500   1.2033   0.03389   0.02925  -0.0103   0.0020   1.0000
  11.750   1.2002   0.03615   0.03171  -0.0080   0.0020   1.0000
  12.000   1.1957   0.03866   0.03442  -0.0063   0.0019   1.0000
  12.250   1.1889   0.04161   0.03758  -0.0051   0.0019   1.0000
  12.500   1.1795   0.04510   0.04128  -0.0046   0.0018   1.0000
  12.750   1.1682   0.04916   0.04554  -0.0049   0.0019   1.0000
  13.000   1.1557   0.05379   0.05036  -0.0062   0.0018   1.0000
  13.250   1.1413   0.05924   0.05601  -0.0085   0.0018   1.0000
  13.500   1.1244   0.06580   0.06275  -0.0120   0.0019   1.0000
  13.750   1.1070   0.07332   0.07045  -0.0167   0.0019   1.0000
  14.000   1.0853   0.08273   0.08003  -0.0228   0.0018   1.0000
  14.250   1.0639   0.09284   0.09030  -0.0292   0.0019   1.0000
  14.500   1.0404   0.10372   0.10131  -0.0355   0.0019   1.0000
  14.750   1.0174   0.11456   0.11225  -0.0416   0.0020   1.0000
  15.000   0.9910   0.12673   0.12451  -0.0481   0.0021   1.0000
  15.250   0.9620   0.14022   0.13807  -0.0550   0.0022   1.0000
  15.500   0.9255   0.15728   0.15516  -0.0633   0.0023   1.0000
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