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HQ 3.0/15 AIRFOIL (hq3015-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/15 AIRFOIL (hq3015-il)
Reynolds number: 100,000
Max Cl/Cd: 52.8 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3015-il-100000.txt
Download as CSV file: xf-hq3015-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3577   0.10344   0.09880  -0.0430   1.0000   0.1574
  -9.750  -0.4025   0.10229   0.09784  -0.0419   1.0000   0.1601
  -9.500  -0.4470   0.10078   0.09650  -0.0406   1.0000   0.1607
  -9.250  -0.3986   0.09856   0.09419  -0.0346   1.0000   0.1695
  -9.000  -0.4247   0.09689   0.09263  -0.0327   1.0000   0.1732
  -8.750  -0.4667   0.09490   0.09079  -0.0318   1.0000   0.1751
  -8.500  -0.5901   0.07676   0.07275  -0.0408   1.0000   0.1067
  -8.250  -0.5983   0.07500   0.07097  -0.0418   0.9969   0.1198
  -8.000  -0.6707   0.04995   0.04411  -0.0528   0.9844   0.0766
  -7.750  -0.6471   0.04768   0.04172  -0.0544   0.9793   0.0804
  -7.500  -0.6303   0.04397   0.03743  -0.0555   0.9733   0.0837
  -7.250  -0.6068   0.04046   0.03308  -0.0572   0.9683   0.0878
  -7.000  -0.5848   0.03869   0.03145  -0.0575   0.9625   0.0927
  -6.750  -0.5561   0.03677   0.02908  -0.0588   0.9576   0.0979
  -6.500  -0.5275   0.03474   0.02656  -0.0599   0.9531   0.1028
  -6.250  -0.5041   0.03344   0.02523  -0.0599   0.9471   0.1072
  -6.000  -0.4711   0.03230   0.02378  -0.0613   0.9425   0.1131
  -5.750  -0.4386   0.03093   0.02215  -0.0625   0.9384   0.1173
  -5.500  -0.4168   0.03007   0.02132  -0.0619   0.9322   0.1229
  -5.250  -0.3823   0.02928   0.02030  -0.0633   0.9275   0.1298
  -5.000  -0.3484   0.02827   0.01942  -0.0647   0.9235   0.1373
  -4.750  -0.3288   0.02785   0.01886  -0.0635   0.9166   0.1458
  -4.500  -0.2957   0.02711   0.01825  -0.0647   0.9120   0.1604
  -4.250  -0.2670   0.02647   0.01781  -0.0652   0.9072   0.1786
  -4.000  -0.2480   0.02596   0.01750  -0.0642   0.9003   0.2043
  -3.750  -0.2179   0.02469   0.01687  -0.0654   0.8958   0.2903
  -3.500  -0.2064   0.02392   0.01741  -0.0626   0.8895   0.5165
  -3.250  -0.1842   0.02453   0.01809  -0.0608   0.8827   0.5941
  -3.000  -0.1482   0.02522   0.01869  -0.0611   0.8785   0.6400
  -2.750  -0.1404   0.02581   0.01930  -0.0572   0.8697   0.6613
  -2.500  -0.1089   0.02632   0.01973  -0.0569   0.8644   0.6892
  -2.250  -0.0941   0.02688   0.02028  -0.0540   0.8570   0.7081
  -2.000  -0.0709   0.02729   0.02067  -0.0522   0.8505   0.7286
  -1.750  -0.0352   0.02762   0.02092  -0.0524   0.8466   0.7533
  -1.500  -0.0339   0.02807   0.02137  -0.0477   0.8365   0.7695
  -1.250  -0.0044   0.02821   0.02149  -0.0465   0.8319   0.7889
  -1.000   0.0033   0.02852   0.02177  -0.0432   0.8228   0.8033
  -0.750   0.0331   0.02852   0.02170  -0.0430   0.8173   0.8181
  -0.500   0.0490   0.02872   0.02186  -0.0411   0.8096   0.8320
  -0.250   0.0715   0.02871   0.02182  -0.0398   0.8027   0.8465
   0.000   0.1089   0.02849   0.02154  -0.0405   0.7991   0.8615
   0.250   0.1119   0.02880   0.02186  -0.0369   0.7880   0.8740
   0.500   0.1543   0.02853   0.02153  -0.0389   0.7841   0.8844
   0.750   0.1640   0.02888   0.02187  -0.0368   0.7733   0.8967
   1.000   0.2088   0.02857   0.02151  -0.0393   0.7690   0.9064
   1.250   0.2285   0.02882   0.02176  -0.0386   0.7580   0.9192
   1.500   0.2852   0.02816   0.02107  -0.0425   0.7536   0.9289
   1.750   0.3187   0.02828   0.02119  -0.0441   0.7427   0.9425
   2.000   0.3833   0.02748   0.02036  -0.0495   0.7388   0.9510
   2.250   0.4534   0.02655   0.01940  -0.0557   0.7366   0.9575
   2.500   0.4942   0.02686   0.01975  -0.0592   0.7253   0.9708
   2.750   0.5624   0.02586   0.01873  -0.0652   0.7223   0.9768
   3.000   0.6125   0.02575   0.01865  -0.0697   0.7124   0.9885
   3.250   0.6759   0.02469   0.01760  -0.0751   0.7075   0.9964
   3.500   0.6718   0.02485   0.01776  -0.0708   0.6956   1.0000
   3.750   0.7156   0.02377   0.01664  -0.0726   0.6903   1.0000
   4.000   0.7282   0.02380   0.01666  -0.0705   0.6780   1.0000
   4.250   0.7654   0.02314   0.01598  -0.0715   0.6691   1.0000
   4.500   0.8048   0.02238   0.01518  -0.0727   0.6595   1.0000
   4.750   0.8316   0.02215   0.01497  -0.0724   0.6466   1.0000
   5.000   0.8628   0.02179   0.01459  -0.0726   0.6342   1.0000
   5.250   0.8973   0.02129   0.01406  -0.0731   0.6216   1.0000
   5.500   0.9304   0.02087   0.01361  -0.0734   0.6079   1.0000
   5.750   0.9586   0.02063   0.01334  -0.0730   0.5919   1.0000
   6.000   0.9840   0.02050   0.01320  -0.0722   0.5742   1.0000
   6.250   1.0092   0.02040   0.01305  -0.0714   0.5551   1.0000
   6.500   1.0361   0.02030   0.01286  -0.0708   0.5352   1.0000
   6.750   1.0594   0.02040   0.01287  -0.0697   0.5141   1.0000
   7.000   1.0798   0.02065   0.01306  -0.0683   0.4914   1.0000
   7.250   1.1040   0.02091   0.01315  -0.0675   0.4700   1.0000
   7.500   1.1209   0.02143   0.01361  -0.0657   0.4477   1.0000
   7.750   1.1406   0.02195   0.01402  -0.0643   0.4269   1.0000
   8.000   1.1620   0.02255   0.01445  -0.0633   0.4074   1.0000
   8.250   1.1780   0.02325   0.01511  -0.0616   0.3884   1.0000
   8.500   1.1947   0.02397   0.01577  -0.0600   0.3705   1.0000
   8.750   1.2118   0.02473   0.01648  -0.0585   0.3539   1.0000
   9.000   1.2288   0.02552   0.01721  -0.0570   0.3381   1.0000
   9.250   1.2455   0.02634   0.01798  -0.0555   0.3233   1.0000
   9.500   1.2631   0.02722   0.01880  -0.0542   0.3095   1.0000
   9.750   1.2814   0.02813   0.01965  -0.0531   0.2962   1.0000
  10.000   1.3022   0.02908   0.02049  -0.0524   0.2832   1.0000
  10.250   1.3094   0.02997   0.02151  -0.0496   0.2718   1.0000
  10.500   1.3221   0.03098   0.02255  -0.0477   0.2608   1.0000
  10.750   1.3397   0.03197   0.02348  -0.0466   0.2499   1.0000
  11.000   1.3484   0.03292   0.02449  -0.0442   0.2398   1.0000
  11.250   1.3563   0.03402   0.02571  -0.0419   0.2304   1.0000
  11.500   1.3732   0.03502   0.02660  -0.0409   0.2205   1.0000
  11.750   1.3738   0.03618   0.02796  -0.0378   0.2121   1.0000
  12.000   1.3848   0.03735   0.02913  -0.0361   0.2033   1.0000
  12.250   1.3915   0.03851   0.03034  -0.0341   0.1949   1.0000
  12.500   1.3965   0.03998   0.03192  -0.0320   0.1870   1.0000
  12.750   1.4103   0.04111   0.03298  -0.0309   0.1784   1.0000
  13.000   1.4075   0.04296   0.03507  -0.0283   0.1715   1.0000
  13.250   1.4291   0.04412   0.03601  -0.0281   0.1625   1.0000
  13.500   1.4168   0.04632   0.03858  -0.0250   0.1573   1.0000
  13.750   1.4301   0.04766   0.03984  -0.0242   0.1499   1.0000
  14.000   1.4267   0.05003   0.04245  -0.0223   0.1444   1.0000
  14.250   1.4257   0.05210   0.04466  -0.0207   0.1389   1.0000
  14.500   1.4400   0.05382   0.04633  -0.0201   0.1326   1.0000
  14.750   1.4262   0.05684   0.04967  -0.0182   0.1289   1.0000
  15.000   1.4282   0.05891   0.05181  -0.0173   0.1240   1.0000
  15.250   1.4366   0.06102   0.05391  -0.0167   0.1190   1.0000
  15.500   1.4185   0.06478   0.05800  -0.0156   0.1163   1.0000
  15.750   1.4067   0.06822   0.06165  -0.0150   0.1130   1.0000
  16.000   1.4318   0.06879   0.06196  -0.0148   0.1069   1.0000
  16.250   1.4072   0.07355   0.06708  -0.0145   0.1054   1.0000
  16.500   1.3837   0.07882   0.07267  -0.0149   0.1038   1.0000
  16.750   1.3592   0.08459   0.07872  -0.0160   0.1022   1.0000
  17.000   1.3314   0.09132   0.08572  -0.0179   0.1011   1.0000
  17.250   1.2757   0.10314   0.09793  -0.0226   0.1029   1.0000
  17.500   1.1977   0.12083   0.11591  -0.0317   0.1062   1.0000
  17.750   1.2722   0.11016   0.10504  -0.0254   0.0961   1.0000
  18.000   1.2500   0.11780   0.11281  -0.0290   0.0950   1.0000
  18.250   0.9080   0.21517   0.20988  -0.0888   0.1526   1.0000
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