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HQ 1.5/9 B AIRFOIL (hq159b-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/9 B AIRFOIL (hq159b-il)
Reynolds number: 100,000
Max Cl/Cd: 49.08 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq159b-il-100000-n5.txt
Download as CSV file: xf-hq159b-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/9 B 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5249   0.08909   0.08411  -0.0235   1.0000   0.0205
  -9.250  -0.5269   0.08434   0.07941  -0.0261   1.0000   0.0202
  -9.000  -0.5319   0.07873   0.07387  -0.0297   1.0000   0.0201
  -8.750  -0.5391   0.07247   0.06767  -0.0346   1.0000   0.0199
  -8.500  -0.5512   0.06676   0.06205  -0.0390   1.0000   0.0196
  -8.250  -0.5613   0.06150   0.05671  -0.0418   1.0000   0.0194
  -8.000  -0.5683   0.05636   0.05141  -0.0435   1.0000   0.0192
  -7.750  -0.5719   0.05133   0.04615  -0.0442   1.0000   0.0192
  -7.500  -0.5712   0.04666   0.04117  -0.0442   1.0000   0.0192
  -7.250  -0.5675   0.04211   0.03622  -0.0435   1.0000   0.0193
  -7.000  -0.5604   0.03783   0.03135  -0.0424   1.0000   0.0200
  -6.750  -0.5499   0.03388   0.02665  -0.0408   1.0000   0.0213
  -6.500  -0.5356   0.03198   0.02467  -0.0399   1.0000   0.0228
  -6.250  -0.5196   0.02993   0.02233  -0.0385   1.0000   0.0241
  -6.000  -0.5026   0.02754   0.01955  -0.0370   1.0000   0.0254
  -5.750  -0.4843   0.02530   0.01690  -0.0354   1.0000   0.0273
  -5.500  -0.4658   0.02342   0.01476  -0.0339   1.0000   0.0299
  -5.250  -0.4474   0.02275   0.01403  -0.0327   1.0000   0.0349
  -5.000  -0.4281   0.02137   0.01243  -0.0312   1.0000   0.0396
  -4.750  -0.4095   0.02064   0.01168  -0.0300   1.0000   0.0467
  -4.500  -0.3831   0.01947   0.01034  -0.0300   0.9974   0.0529
  -4.250  -0.3502   0.01845   0.00929  -0.0314   0.9917   0.0599
  -4.000  -0.3169   0.01769   0.00842  -0.0330   0.9856   0.0710
  -3.750  -0.2833   0.01692   0.00756  -0.0345   0.9800   0.0812
  -3.500  -0.2506   0.01622   0.00686  -0.0359   0.9735   0.0977
  -3.000  -0.1883   0.01409   0.00582  -0.0389   0.9615   0.3231
  -2.750  -0.1586   0.01324   0.00584  -0.0395   0.9563   0.5439
  -2.500  -0.1302   0.01312   0.00592  -0.0392   0.9491   0.6400
  -2.250  -0.0990   0.01311   0.00596  -0.0393   0.9431   0.7041
  -2.000  -0.0725   0.01310   0.00600  -0.0384   0.9355   0.7503
  -1.750  -0.0424   0.01308   0.00594  -0.0383   0.9293   0.7831
  -1.500  -0.0146   0.01305   0.00588  -0.0379   0.9216   0.8083
  -1.250   0.0163   0.01299   0.00578  -0.0379   0.9148   0.8347
  -1.000   0.0448   0.01292   0.00565  -0.0376   0.9052   0.8561
  -0.750   0.0776   0.01281   0.00550  -0.0381   0.8969   0.8729
  -0.500   0.1103   0.01272   0.00537  -0.0388   0.8883   0.8880
  -0.250   0.1435   0.01267   0.00527  -0.0397   0.8807   0.9036
   0.000   0.1802   0.01261   0.00519  -0.0414   0.8740   0.9193
   0.250   0.2176   0.01258   0.00514  -0.0433   0.8665   0.9364
   0.500   0.2582   0.01251   0.00506  -0.0458   0.8593   0.9534
   0.750   0.2985   0.01243   0.00497  -0.0483   0.8479   0.9727
   1.000   0.3383   0.01231   0.00482  -0.0506   0.8337   0.9971
   1.250   0.3627   0.01227   0.00473  -0.0498   0.8173   1.0000
   1.500   0.3853   0.01227   0.00469  -0.0486   0.7998   1.0000
   1.750   0.4093   0.01231   0.00470  -0.0478   0.7837   1.0000
   2.000   0.4344   0.01237   0.00475  -0.0472   0.7700   1.0000
   2.250   0.4599   0.01244   0.00485  -0.0466   0.7557   1.0000
   2.500   0.4855   0.01251   0.00494  -0.0460   0.7407   1.0000
   2.750   0.5112   0.01260   0.00505  -0.0454   0.7249   1.0000
   3.000   0.5369   0.01268   0.00519  -0.0447   0.7075   1.0000
   3.250   0.5624   0.01279   0.00533  -0.0441   0.6878   1.0000
   3.500   0.5878   0.01290   0.00549  -0.0433   0.6661   1.0000
   3.750   0.6127   0.01303   0.00565  -0.0425   0.6388   1.0000
   4.000   0.6365   0.01318   0.00574  -0.0413   0.5963   1.0000
   4.250   0.6591   0.01343   0.00587  -0.0399   0.5356   1.0000
   4.500   0.6802   0.01393   0.00602  -0.0383   0.4654   1.0000
   4.750   0.7002   0.01463   0.00636  -0.0370   0.3899   1.0000
   5.000   0.7192   0.01551   0.00680  -0.0357   0.3113   1.0000
   5.250   0.7396   0.01633   0.00734  -0.0347   0.2567   1.0000
   5.500   0.7613   0.01707   0.00793  -0.0340   0.2127   1.0000
   5.750   0.7834   0.01779   0.00862  -0.0332   0.1634   1.0000
   6.000   0.8027   0.01893   0.00940  -0.0323   0.1047   1.0000
   6.250   0.8220   0.02016   0.01048  -0.0312   0.0760   1.0000
   6.500   0.8421   0.02128   0.01162  -0.0301   0.0637   1.0000
   6.750   0.8622   0.02234   0.01273  -0.0291   0.0553   1.0000
   7.000   0.8821   0.02340   0.01386  -0.0281   0.0489   1.0000
   7.250   0.9005   0.02473   0.01529  -0.0268   0.0455   1.0000
   7.500   0.9200   0.02604   0.01678  -0.0256   0.0421   1.0000
   7.750   0.9386   0.02732   0.01811  -0.0246   0.0372   1.0000
   8.000   0.9570   0.02906   0.01999  -0.0234   0.0335   1.0000
   8.250   0.9764   0.03071   0.02192  -0.0224   0.0303   1.0000
   8.500   0.9927   0.03261   0.02381  -0.0215   0.0270   1.0000
   8.750   1.0113   0.03475   0.02632  -0.0203   0.0247   1.0000
   9.000   1.0281   0.03733   0.02924  -0.0190   0.0230   1.0000
   9.250   1.0419   0.03998   0.03221  -0.0176   0.0217   1.0000
   9.500   1.0527   0.04228   0.03474  -0.0163   0.0204   1.0000
   9.750   1.0594   0.04549   0.03809  -0.0150   0.0192   1.0000
  10.000   1.0600   0.04826   0.04137  -0.0127   0.0183   1.0000
  10.250   1.0553   0.05152   0.04508  -0.0103   0.0178   1.0000
  10.500   1.0436   0.05490   0.04880  -0.0076   0.0175   1.0000
  10.750   1.0300   0.05847   0.05265  -0.0058   0.0174   1.0000
  11.000   1.0126   0.06260   0.05706  -0.0051   0.0173   1.0000
  11.250   0.9942   0.06728   0.06197  -0.0058   0.0173   1.0000
  11.500   0.9756   0.07257   0.06747  -0.0078   0.0174   1.0000
  11.750   0.9548   0.07898   0.07406  -0.0114   0.0175   1.0000
  12.000   0.9356   0.08617   0.08138  -0.0162   0.0177   1.0000
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