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HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il)
Reynolds number: 200,000
Max Cl/Cd: 63.89 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1012-il-200000.txt
Download as CSV file: xf-hq1012-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.6643   0.08042   0.07674  -0.0363   1.0000   0.0290
 -11.750  -0.6919   0.07136   0.06763  -0.0428   1.0000   0.0283
 -11.500  -0.7168   0.06439   0.06054  -0.0477   1.0000   0.0278
 -11.250  -0.7439   0.05835   0.05433  -0.0510   1.0000   0.0276
 -11.000  -0.7660   0.05378   0.04958  -0.0522   1.0000   0.0272
 -10.750  -0.7892   0.04985   0.04544  -0.0516   1.0000   0.0272
 -10.500  -0.8088   0.04662   0.04199  -0.0490   1.0000   0.0271
 -10.250  -0.8206   0.04320   0.03827  -0.0466   1.0000   0.0272
 -10.000  -0.8248   0.04021   0.03493  -0.0443   1.0000   0.0280
  -9.750  -0.8234   0.03764   0.03197  -0.0421   1.0000   0.0288
  -9.500  -0.8173   0.03567   0.02961  -0.0398   1.0000   0.0295
  -9.250  -0.8128   0.03169   0.02523  -0.0377   1.0000   0.0303
  -9.000  -0.7996   0.02937   0.02278  -0.0363   1.0000   0.0314
  -8.750  -0.7843   0.02796   0.02127  -0.0347   1.0000   0.0330
  -8.500  -0.7690   0.02656   0.01971  -0.0330   1.0000   0.0349
  -8.250  -0.7534   0.02564   0.01857  -0.0310   1.0000   0.0376
  -8.000  -0.7400   0.02372   0.01657  -0.0291   1.0000   0.0405
  -7.750  -0.7264   0.02290   0.01574  -0.0270   1.0000   0.0437
  -7.500  -0.7143   0.02209   0.01477  -0.0244   1.0000   0.0471
  -7.250  -0.7051   0.02090   0.01355  -0.0216   1.0000   0.0513
  -7.000  -0.6950   0.02041   0.01305  -0.0190   1.0000   0.0560
  -6.750  -0.6831   0.01990   0.01239  -0.0165   1.0000   0.0606
  -6.500  -0.6495   0.01883   0.01138  -0.0185   0.9958   0.0694
  -6.250  -0.6132   0.01787   0.01040  -0.0209   0.9905   0.0783
  -6.000  -0.5758   0.01708   0.00957  -0.0233   0.9851   0.0887
  -5.750  -0.5385   0.01644   0.00889  -0.0257   0.9798   0.0998
  -5.500  -0.5040   0.01555   0.00808  -0.0277   0.9735   0.1150
  -5.250  -0.4656   0.01465   0.00731  -0.0304   0.9694   0.1410
  -5.000  -0.4356   0.01372   0.00672  -0.0316   0.9614   0.1924
  -4.750  -0.3995   0.01274   0.00616  -0.0342   0.9569   0.2813
  -4.500  -0.3702   0.01190   0.00581  -0.0352   0.9497   0.3851
  -4.250  -0.3384   0.01137   0.00567  -0.0362   0.9435   0.4875
  -4.000  -0.3062   0.01119   0.00566  -0.0369   0.9373   0.5529
  -3.750  -0.2753   0.01116   0.00567  -0.0372   0.9300   0.5933
  -3.500  -0.2419   0.01116   0.00565  -0.0380   0.9246   0.6241
  -3.250  -0.2145   0.01121   0.00569  -0.0375   0.9160   0.6475
  -3.000  -0.1831   0.01126   0.00570  -0.0378   0.9105   0.6697
  -2.750  -0.1579   0.01135   0.00576  -0.0369   0.9014   0.6885
  -2.500  -0.1292   0.01142   0.00582  -0.0364   0.8953   0.7054
  -2.250  -0.1045   0.01152   0.00591  -0.0354   0.8863   0.7209
  -2.000  -0.0773   0.01156   0.00589  -0.0348   0.8796   0.7341
  -1.750  -0.0517   0.01159   0.00591  -0.0340   0.8710   0.7450
  -1.500  -0.0251   0.01160   0.00590  -0.0334   0.8640   0.7548
  -1.250   0.0005   0.01161   0.00588  -0.0327   0.8557   0.7653
  -1.000   0.0264   0.01165   0.00588  -0.0319   0.8487   0.7773
  -0.750   0.0515   0.01168   0.00593  -0.0309   0.8408   0.7879
  -0.500   0.0768   0.01171   0.00595  -0.0300   0.8335   0.7991
  -0.250   0.1017   0.01169   0.00592  -0.0290   0.8248   0.8105
   0.000   0.1264   0.01166   0.00588  -0.0280   0.8151   0.8212
   0.250   0.1525   0.01156   0.00575  -0.0271   0.8067   0.8290
   0.500   0.1774   0.01149   0.00568  -0.0263   0.7960   0.8383
   0.750   0.2028   0.01142   0.00562  -0.0254   0.7866   0.8468
   1.000   0.2289   0.01132   0.00549  -0.0246   0.7777   0.8556
   1.250   0.2537   0.01125   0.00544  -0.0238   0.7668   0.8658
   1.500   0.2793   0.01118   0.00540  -0.0230   0.7579   0.8747
   1.750   0.3052   0.01111   0.00533  -0.0222   0.7490   0.8848
   2.000   0.3303   0.01106   0.00532  -0.0215   0.7386   0.8961
   2.250   0.3572   0.01099   0.00527  -0.0209   0.7292   0.9061
   2.500   0.3852   0.01092   0.00522  -0.0205   0.7187   0.9167
   2.750   0.4142   0.01088   0.00522  -0.0205   0.7066   0.9282
   3.000   0.4451   0.01084   0.00522  -0.0209   0.6940   0.9403
   3.250   0.4814   0.01079   0.00519  -0.0223   0.6794   0.9499
   3.500   0.5189   0.01074   0.00516  -0.0241   0.6626   0.9596
   3.750   0.5568   0.01070   0.00509  -0.0260   0.6434   0.9699
   4.000   0.5983   0.01066   0.00509  -0.0288   0.6178   0.9781
   4.250   0.6393   0.01066   0.00506  -0.0315   0.5863   0.9871
   4.500   0.6797   0.01073   0.00503  -0.0342   0.5429   0.9977
   4.750   0.6951   0.01088   0.00505  -0.0324   0.5025   1.0000
   5.000   0.7062   0.01118   0.00513  -0.0296   0.4587   1.0000
   5.250   0.7212   0.01164   0.00536  -0.0275   0.4109   1.0000
   5.500   0.7387   0.01219   0.00567  -0.0259   0.3668   1.0000
   5.750   0.7578   0.01274   0.00603  -0.0246   0.3313   1.0000
   6.000   0.7777   0.01330   0.00644  -0.0234   0.3023   1.0000
   6.250   0.7978   0.01388   0.00690  -0.0223   0.2772   1.0000
   6.500   0.8188   0.01442   0.00737  -0.0213   0.2534   1.0000
   6.750   0.8392   0.01499   0.00785  -0.0203   0.2300   1.0000
   7.000   0.8598   0.01553   0.00834  -0.0193   0.2046   1.0000
   7.250   0.8797   0.01613   0.00886  -0.0182   0.1774   1.0000
   7.500   0.8987   0.01683   0.00947  -0.0170   0.1522   1.0000
   7.750   0.9157   0.01770   0.01018  -0.0156   0.1329   1.0000
   8.000   0.9334   0.01854   0.01096  -0.0142   0.1174   1.0000
   8.250   0.9502   0.01946   0.01181  -0.0128   0.1050   1.0000
   8.500   0.9688   0.02020   0.01259  -0.0116   0.0947   1.0000
   8.750   0.9860   0.02111   0.01355  -0.0102   0.0860   1.0000
   9.000   1.0011   0.02224   0.01462  -0.0086   0.0782   1.0000
   9.250   1.0186   0.02297   0.01545  -0.0073   0.0710   1.0000
   9.500   1.0329   0.02419   0.01668  -0.0057   0.0646   1.0000
   9.750   1.0473   0.02495   0.01750  -0.0041   0.0581   1.0000
  10.000   1.0588   0.02623   0.01883  -0.0021   0.0524   1.0000
  10.250   1.0697   0.02701   0.01968  -0.0001   0.0472   1.0000
  10.500   1.0790   0.02855   0.02126   0.0019   0.0427   1.0000
  10.750   1.0895   0.02963   0.02248   0.0038   0.0388   1.0000
  11.000   1.0974   0.03115   0.02398   0.0055   0.0356   1.0000
  11.250   1.1060   0.03292   0.02593   0.0073   0.0325   1.0000
  11.500   1.1131   0.03423   0.02736   0.0089   0.0300   1.0000
  11.750   1.1185   0.03581   0.02893   0.0103   0.0278   1.0000
  12.000   1.1245   0.03845   0.03172   0.0117   0.0263   1.0000
  12.250   1.1285   0.04058   0.03410   0.0132   0.0251   1.0000
  12.500   1.1313   0.04292   0.03664   0.0144   0.0241   1.0000
  12.750   1.1325   0.04549   0.03942   0.0154   0.0236   1.0000
  13.000   1.1312   0.04803   0.04213   0.0161   0.0226   1.0000
  13.250   1.1289   0.05092   0.04517   0.0166   0.0220   1.0000
  13.500   1.1248   0.05411   0.04854   0.0168   0.0217   1.0000
  13.750   1.1188   0.05765   0.05224   0.0167   0.0215   1.0000
  14.000   1.1091   0.06181   0.05659   0.0161   0.0212   1.0000
  14.250   1.0963   0.06650   0.06150   0.0149   0.0212   1.0000
  14.500   1.0817   0.07166   0.06684   0.0131   0.0210   1.0000
  14.750   1.0637   0.07762   0.07300   0.0105   0.0209   1.0000
  15.000   1.0432   0.08438   0.08000   0.0067   0.0211   1.0000
  15.250   1.0143   0.09347   0.08939   0.0009   0.0214   1.0000
  15.500   0.9078   0.12333   0.11984  -0.0196   0.0244   1.0000
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