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HQ 2.5/9 AIRFOIL (hq259-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 AIRFOIL (hq259-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.38 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259-il-1000000-n5.txt
Download as CSV file: xf-hq259-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4226   0.08165   0.08009  -0.0333   1.0000   0.0025
  -8.500  -0.4248   0.07789   0.07636  -0.0349   1.0000   0.0025
  -8.250  -0.4344   0.07330   0.07181  -0.0365   1.0000   0.0025
  -8.000  -0.4299   0.06656   0.06509  -0.0450   0.9857   0.0024
  -7.750  -0.4092   0.05335   0.05175  -0.0674   0.9731   0.0024
  -7.500  -0.3957   0.04364   0.04177  -0.0771   0.9554   0.0023
  -7.250  -0.4218   0.02055   0.01727  -0.0796   0.9221   0.0021
  -7.000  -0.4042   0.01680   0.01293  -0.0789   0.9111   0.0021
  -6.750  -0.3820   0.01475   0.01048  -0.0783   0.9024   0.0021
  -6.500  -0.3584   0.01322   0.00862  -0.0778   0.8939   0.0022
  -6.250  -0.3335   0.01214   0.00731  -0.0774   0.8862   0.0023
  -5.750  -0.2816   0.01086   0.00574  -0.0769   0.8715   0.0026
  -5.500  -0.2560   0.01008   0.00480  -0.0766   0.8646   0.0030
  -5.250  -0.2293   0.00966   0.00432  -0.0765   0.8576   0.0033
  -5.000  -0.2024   0.00938   0.00397  -0.0763   0.8512   0.0038
  -4.750  -0.1753   0.00905   0.00357  -0.0763   0.8444   0.0042
  -4.250  -0.1206   0.00855   0.00292  -0.0761   0.8313   0.0053
  -4.000  -0.0935   0.00823   0.00252  -0.0760   0.8247   0.0069
  -3.750  -0.0659   0.00799   0.00224  -0.0759   0.8178   0.0081
  -3.250  -0.0107   0.00766   0.00178  -0.0758   0.8025   0.0101
  -3.000   0.0168   0.00749   0.00158  -0.0757   0.7934   0.0163
  -2.500   0.0720   0.00722   0.00130  -0.0757   0.7743   0.0377
  -2.250   0.0997   0.00712   0.00119  -0.0756   0.7663   0.0474
  -2.000   0.1275   0.00703   0.00109  -0.0756   0.7580   0.0603
  -1.750   0.1552   0.00689   0.00100  -0.0757   0.7489   0.0864
  -1.500   0.1822   0.00656   0.00089  -0.0757   0.7380   0.1723
  -1.250   0.2093   0.00631   0.00081  -0.0757   0.7260   0.2475
  -1.000   0.2360   0.00599   0.00074  -0.0757   0.7116   0.3540
  -0.750   0.2628   0.00578   0.00070  -0.0757   0.6954   0.4356
  -0.500   0.2899   0.00568   0.00067  -0.0756   0.6803   0.4897
  -0.250   0.3166   0.00547   0.00071  -0.0755   0.6680   0.5876
   0.000   0.3435   0.00539   0.00076  -0.0753   0.6556   0.6475
   0.250   0.3707   0.00542   0.00078  -0.0752   0.6393   0.6717
   0.500   0.3978   0.00549   0.00081  -0.0750   0.6198   0.6865
   0.750   0.4251   0.00557   0.00084  -0.0749   0.5990   0.6962
   1.000   0.4522   0.00568   0.00088  -0.0748   0.5785   0.7045
   1.500   0.5056   0.00597   0.00100  -0.0744   0.5225   0.7222
   1.750   0.5315   0.00621   0.00110  -0.0741   0.4830   0.7311
   2.250   0.5837   0.00665   0.00132  -0.0736   0.4146   0.7507
   2.500   0.6098   0.00686   0.00145  -0.0734   0.3846   0.7610
   2.750   0.6359   0.00707   0.00158  -0.0731   0.3552   0.7722
   3.000   0.6615   0.00733   0.00173  -0.0728   0.3204   0.7841
   3.250   0.6869   0.00759   0.00190  -0.0725   0.2867   0.7970
   3.500   0.7122   0.00785   0.00209  -0.0721   0.2576   0.8110
   3.750   0.7379   0.00802   0.00225  -0.0718   0.2396   0.8272
   4.000   0.7623   0.00830   0.00245  -0.0712   0.2064   0.8477
   4.250   0.7849   0.00862   0.00268  -0.0704   0.1659   0.8789
   4.500   0.8139   0.00881   0.00290  -0.0708   0.1359   1.0000
   4.750   0.8365   0.00946   0.00326  -0.0701   0.0836   1.0000
   5.000   0.8589   0.01015   0.00371  -0.0694   0.0372   1.0000
   5.250   0.8813   0.01086   0.00423  -0.0686   0.0045   1.0000
   5.500   0.9070   0.01114   0.00453  -0.0683   0.0032   1.0000
   5.750   0.9325   0.01143   0.00486  -0.0680   0.0028   1.0000
   6.000   0.9578   0.01175   0.00521  -0.0676   0.0025   1.0000
   6.250   0.9825   0.01213   0.00564  -0.0672   0.0021   1.0000
   6.500   1.0060   0.01267   0.00627  -0.0665   0.0017   1.0000
   6.750   1.0284   0.01336   0.00708  -0.0656   0.0015   1.0000
   7.000   1.0519   0.01386   0.00763  -0.0649   0.0015   1.0000
   7.250   1.0746   0.01445   0.00830  -0.0642   0.0014   1.0000
   7.500   1.0964   0.01514   0.00907  -0.0632   0.0014   1.0000
   7.750   1.1176   0.01587   0.00988  -0.0622   0.0014   1.0000
   8.000   1.1376   0.01671   0.01082  -0.0611   0.0013   1.0000
   8.250   1.1567   0.01762   0.01182  -0.0598   0.0013   1.0000
   8.500   1.1744   0.01866   0.01298  -0.0583   0.0013   1.0000
   8.750   1.1912   0.01977   0.01419  -0.0567   0.0013   1.0000
   9.000   1.2070   0.02096   0.01554  -0.0550   0.0013   1.0000
   9.250   1.2214   0.02229   0.01700  -0.0531   0.0013   1.0000
   9.500   1.2350   0.02365   0.01850  -0.0512   0.0013   1.0000
   9.750   1.2465   0.02523   0.02023  -0.0491   0.0013   1.0000
  10.000   1.2564   0.02682   0.02198  -0.0467   0.0013   1.0000
  10.250   1.2617   0.02849   0.02382  -0.0437   0.0013   1.0000
  10.500   1.2642   0.03028   0.02578  -0.0405   0.0013   1.0000
  10.750   1.2649   0.03219   0.02786  -0.0374   0.0013   1.0000
  11.000   1.2622   0.03446   0.03033  -0.0343   0.0013   1.0000
  11.250   1.2620   0.03635   0.03237  -0.0319   0.0013   1.0000
  11.500   1.2538   0.03930   0.03554  -0.0293   0.0013   1.0000
  11.750   1.2487   0.04194   0.03834  -0.0275   0.0013   1.0000
  12.000   1.2423   0.04487   0.04143  -0.0262   0.0013   1.0000
  12.250   1.2295   0.04882   0.04559  -0.0254   0.0013   1.0000
  12.500   1.2203   0.05257   0.04950  -0.0254   0.0013   1.0000
  12.750   1.2064   0.05735   0.05445  -0.0262   0.0013   1.0000
  13.000   1.1893   0.06309   0.06038  -0.0280   0.0013   1.0000
  13.250   1.1768   0.06864   0.06607  -0.0305   0.0013   1.0000
  13.500   1.1561   0.07632   0.07393  -0.0346   0.0013   1.0000
  13.750   1.1464   0.08261   0.08034  -0.0384   0.0013   1.0000
  14.000   1.1236   0.09248   0.09037  -0.0445   0.0013   1.0000
  14.250   1.1072   0.10162   0.09964  -0.0503   0.0013   1.0000
  14.500   1.0889   0.11174   0.10988  -0.0564   0.0013   1.0000
  14.750   1.0707   0.12218   0.12043  -0.0626   0.0014   1.0000
  15.000   1.0466   0.13464   0.13299  -0.0697   0.0014   1.0000
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