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HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il)
Reynolds number: 100,000
Max Cl/Cd: 48.41 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1511-il-100000-n5.txt
Download as CSV file: xf-hq1511-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/11 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5639   0.08449   0.07940  -0.0336   1.0000   0.0212
 -10.500  -0.5789   0.07560   0.07053  -0.0395   1.0000   0.0209
 -10.250  -0.6015   0.06694   0.06184  -0.0465   1.0000   0.0206
 -10.000  -0.6245   0.06060   0.05540  -0.0510   1.0000   0.0204
  -9.750  -0.6463   0.05600   0.05068  -0.0528   1.0000   0.0203
  -9.500  -0.6648   0.05228   0.04678  -0.0521   1.0000   0.0202
  -9.250  -0.6780   0.04819   0.04240  -0.0511   1.0000   0.0202
  -9.000  -0.6856   0.04419   0.03804  -0.0497   1.0000   0.0204
  -8.750  -0.6871   0.04055   0.03400  -0.0480   1.0000   0.0206
  -8.500  -0.6847   0.03709   0.03007  -0.0460   1.0000   0.0210
  -8.250  -0.6776   0.03416   0.02668  -0.0440   1.0000   0.0214
  -8.000  -0.6669   0.03216   0.02449  -0.0422   1.0000   0.0222
  -7.750  -0.6541   0.03082   0.02304  -0.0405   1.0000   0.0231
  -7.500  -0.6409   0.02962   0.02167  -0.0387   1.0000   0.0248
  -7.250  -0.6276   0.02803   0.01978  -0.0367   1.0000   0.0271
  -7.000  -0.6145   0.02660   0.01822  -0.0347   1.0000   0.0290
  -6.750  -0.6010   0.02559   0.01715  -0.0328   1.0000   0.0313
  -6.500  -0.5825   0.02425   0.01558  -0.0315   0.9987   0.0353
  -6.250  -0.5504   0.02303   0.01429  -0.0331   0.9925   0.0409
  -6.000  -0.5170   0.02239   0.01354  -0.0350   0.9860   0.0507
  -5.750  -0.4840   0.02173   0.01277  -0.0368   0.9799   0.0612
  -5.500  -0.4514   0.02083   0.01174  -0.0381   0.9737   0.0681
  -5.250  -0.4187   0.01992   0.01079  -0.0396   0.9683   0.0754
  -5.000  -0.3873   0.01924   0.00998  -0.0406   0.9616   0.0838
  -4.750  -0.3531   0.01842   0.00918  -0.0425   0.9569   0.0948
  -4.500  -0.3237   0.01773   0.00848  -0.0432   0.9495   0.1103
  -4.000  -0.2640   0.01612   0.00741  -0.0453   0.9367   0.2170
  -3.750  -0.2364   0.01517   0.00699  -0.0460   0.9301   0.3269
  -3.500  -0.2107   0.01453   0.00687  -0.0458   0.9232   0.4605
  -3.250  -0.1837   0.01431   0.00693  -0.0454   0.9163   0.5463
  -3.000  -0.1541   0.01428   0.00699  -0.0453   0.9106   0.6068
  -2.750  -0.1282   0.01435   0.00706  -0.0445   0.9028   0.6519
  -2.500  -0.0981   0.01442   0.00711  -0.0443   0.8978   0.6898
  -2.250  -0.0733   0.01448   0.00713  -0.0433   0.8897   0.7120
  -2.000  -0.0422   0.01444   0.00699  -0.0436   0.8840   0.7263
  -1.750  -0.0157   0.01442   0.00691  -0.0431   0.8754   0.7407
  -1.500   0.0142   0.01437   0.00680  -0.0429   0.8683   0.7583
  -1.250   0.0389   0.01436   0.00675  -0.0418   0.8583   0.7751
  -1.000   0.0669   0.01432   0.00667  -0.0413   0.8514   0.7896
  -0.750   0.0925   0.01432   0.00664  -0.0406   0.8432   0.8021
  -0.500   0.1210   0.01427   0.00656  -0.0404   0.8373   0.8140
  -0.250   0.1461   0.01427   0.00654  -0.0397   0.8285   0.8257
   0.000   0.1740   0.01422   0.00645  -0.0395   0.8213   0.8363
   0.250   0.2003   0.01418   0.00641  -0.0389   0.8122   0.8461
   0.500   0.2269   0.01413   0.00635  -0.0384   0.8028   0.8568
   0.750   0.2552   0.01402   0.00621  -0.0380   0.7935   0.8682
   1.000   0.2813   0.01394   0.00616  -0.0373   0.7812   0.8801
   1.250   0.3090   0.01385   0.00608  -0.0368   0.7685   0.8927
   1.500   0.3385   0.01375   0.00600  -0.0368   0.7556   0.9066
   1.750   0.3704   0.01368   0.00594  -0.0372   0.7434   0.9214
   2.000   0.4048   0.01362   0.00591  -0.0383   0.7314   0.9364
   2.250   0.4414   0.01357   0.00588  -0.0399   0.7196   0.9514
   2.500   0.4787   0.01356   0.00593  -0.0419   0.7066   0.9675
   2.750   0.5166   0.01354   0.00597  -0.0440   0.6922   0.9863
   3.000   0.5463   0.01357   0.00601  -0.0446   0.6768   1.0000
   3.250   0.5679   0.01364   0.00607  -0.0435   0.6608   1.0000
   3.500   0.5909   0.01374   0.00619  -0.0426   0.6433   1.0000
   3.750   0.6145   0.01385   0.00633  -0.0418   0.6237   1.0000
   4.000   0.6386   0.01396   0.00642  -0.0410   0.6015   1.0000
   4.250   0.6624   0.01411   0.00655  -0.0401   0.5739   1.0000
   4.500   0.6853   0.01429   0.00665  -0.0390   0.5348   1.0000
   4.750   0.7068   0.01460   0.00672  -0.0376   0.4856   1.0000
   5.000   0.7275   0.01509   0.00694  -0.0363   0.4392   1.0000
   5.250   0.7489   0.01559   0.00731  -0.0352   0.3990   1.0000
   5.500   0.7703   0.01612   0.00774  -0.0342   0.3602   1.0000
   5.750   0.7912   0.01670   0.00817  -0.0332   0.3273   1.0000
   6.000   0.8120   0.01732   0.00867  -0.0323   0.3005   1.0000
   6.250   0.8328   0.01796   0.00923  -0.0313   0.2770   1.0000
   6.500   0.8540   0.01858   0.00984  -0.0304   0.2530   1.0000
   6.750   0.8745   0.01923   0.01046  -0.0295   0.2282   1.0000
   7.000   0.8945   0.01991   0.01110  -0.0285   0.1998   1.0000
   7.250   0.9144   0.02059   0.01172  -0.0276   0.1626   1.0000
   7.500   0.9319   0.02152   0.01246  -0.0264   0.1295   1.0000
   7.750   0.9481   0.02261   0.01340  -0.0251   0.1065   1.0000
   8.000   0.9648   0.02368   0.01445  -0.0238   0.0893   1.0000
   8.250   0.9807   0.02481   0.01556  -0.0224   0.0756   1.0000
   8.500   0.9952   0.02602   0.01677  -0.0209   0.0660   1.0000
   8.750   1.0095   0.02721   0.01800  -0.0194   0.0583   1.0000
   9.000   1.0232   0.02844   0.01935  -0.0177   0.0521   1.0000
   9.250   1.0356   0.02969   0.02067  -0.0160   0.0479   1.0000
   9.500   1.0447   0.03119   0.02220  -0.0140   0.0451   1.0000
   9.750   1.0566   0.03254   0.02373  -0.0121   0.0421   1.0000
  10.000   1.0670   0.03389   0.02517  -0.0104   0.0392   1.0000
  10.250   1.0754   0.03542   0.02673  -0.0087   0.0371   1.0000
  10.500   1.0856   0.03726   0.02868  -0.0071   0.0355   1.0000
  10.750   1.0975   0.03911   0.03078  -0.0057   0.0341   1.0000
  11.000   1.1075   0.04104   0.03293  -0.0043   0.0326   1.0000
  11.250   1.1149   0.04297   0.03503  -0.0030   0.0311   1.0000
  11.500   1.1204   0.04490   0.03707  -0.0017   0.0298   1.0000
  11.750   1.1247   0.04705   0.03929  -0.0006   0.0287   1.0000
  12.000   1.1276   0.04981   0.04219   0.0004   0.0278   1.0000
  12.250   1.1269   0.05280   0.04550   0.0014   0.0273   1.0000
  12.500   1.1227   0.05612   0.04912   0.0020   0.0269   1.0000
  12.750   1.1147   0.05989   0.05319   0.0023   0.0265   1.0000
  13.000   1.1037   0.06408   0.05766   0.0020   0.0262   1.0000
  13.250   1.0902   0.06877   0.06262   0.0010   0.0260   1.0000
  13.500   1.0734   0.07415   0.06825  -0.0008   0.0258   1.0000
  13.750   1.0539   0.08036   0.07471  -0.0037   0.0258   1.0000
  14.000   1.0321   0.08749   0.08207  -0.0077   0.0258   1.0000
  14.250   1.0072   0.09603   0.09082  -0.0130   0.0261   1.0000
  14.500   0.9796   0.10611   0.10108  -0.0196   0.0265   1.0000
  14.750   0.9477   0.11859   0.11370  -0.0280   0.0269   1.0000
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