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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 50,000
Max Cl/Cd: 36.92 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-50000.txt
Download as CSV file: xf-hq2090sm-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ-2.0/9  9.0%   smoothed                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4743   0.12078   0.11371  -0.0110   1.0000   0.2035
  -9.750  -0.4621   0.11632   0.10926  -0.0106   1.0000   0.2123
  -9.500  -0.4820   0.11576   0.10885  -0.0135   1.0000   0.2191
  -9.250  -0.4702   0.11160   0.10471  -0.0128   1.0000   0.2328
  -9.000  -0.4650   0.10825   0.10141  -0.0125   1.0000   0.2469
  -8.750  -0.4629   0.10523   0.09845  -0.0123   1.0000   0.2613
  -8.500  -0.4627   0.10247   0.09577  -0.0122   1.0000   0.2758
  -8.250  -0.4388   0.09740   0.09068  -0.0102   1.0000   0.2947
  -8.000  -0.4322   0.09428   0.08760  -0.0093   1.0000   0.3128
  -7.750  -0.4370   0.09221   0.08563  -0.0087   1.0000   0.3312
  -7.500  -0.4227   0.08823   0.08169  -0.0072   1.0000   0.3518
  -7.250  -0.4298   0.08660   0.08017  -0.0057   1.0000   0.3742
  -7.000  -0.4168   0.08332   0.07689  -0.0036   1.0000   0.4018
  -6.750  -0.3984   0.07970   0.07327  -0.0011   1.0000   0.4358
  -5.750  -0.4718   0.05311   0.04643  -0.0394   1.0000   0.1713
  -5.500  -0.4554   0.04645   0.03870  -0.0429   1.0000   0.1336
  -5.250  -0.4390   0.04231   0.03433  -0.0423   1.0000   0.1266
  -5.000  -0.4206   0.03868   0.03009  -0.0421   1.0000   0.1237
  -4.750  -0.4012   0.03582   0.02687  -0.0413   1.0000   0.1265
  -4.500  -0.3790   0.03290   0.02342  -0.0405   1.0000   0.1266
  -4.250  -0.3558   0.03050   0.02049  -0.0395   1.0000   0.1308
  -4.000  -0.3334   0.02838   0.01813  -0.0386   1.0000   0.1415
  -3.750  -0.3087   0.02641   0.01576  -0.0374   1.0000   0.1501
  -3.500  -0.2866   0.02478   0.01417  -0.0362   1.0000   0.1694
  -3.250  -0.2630   0.02325   0.01257  -0.0346   1.0000   0.1897
  -3.000  -0.2409   0.02173   0.01126  -0.0334   1.0000   0.2317
  -2.750  -0.2194   0.01868   0.00995  -0.0324   1.0000   0.4290
  -2.250  -0.1181   0.01850   0.01037  -0.0276   1.0000   1.0000
  -2.000  -0.1298   0.01811   0.00990  -0.0231   1.0000   1.0000
  -1.750  -0.1322   0.01781   0.00943  -0.0201   1.0000   1.0000
  -1.500  -0.1202   0.01771   0.00902  -0.0191   1.0000   1.0000
  -1.250  -0.1018   0.01775   0.00877  -0.0190   1.0000   1.0000
  -1.000  -0.0810   0.01787   0.00862  -0.0192   1.0000   1.0000
  -0.750  -0.0595   0.01806   0.00856  -0.0194   1.0000   1.0000
  -0.500  -0.0377   0.01831   0.00855  -0.0195   1.0000   1.0000
  -0.250  -0.0160   0.01860   0.00864  -0.0196   1.0000   1.0000
   0.000   0.0056   0.01893   0.00880  -0.0197   1.0000   1.0000
   0.250   0.0269   0.01930   0.00901  -0.0198   1.0000   1.0000
   0.500   0.0479   0.01972   0.00930  -0.0198   1.0000   1.0000
   0.750   0.0687   0.02017   0.00963  -0.0198   1.0000   1.0000
   1.000   0.0891   0.02067   0.01003  -0.0199   1.0000   1.0000
   1.250   0.1093   0.02122   0.01051  -0.0199   1.0000   1.0000
   1.500   0.1290   0.02182   0.01105  -0.0200   1.0000   1.0000
   1.750   0.1483   0.02247   0.01167  -0.0201   1.0000   1.0000
   2.000   0.1671   0.02319   0.01236  -0.0202   1.0000   1.0000
   2.250   0.1858   0.02397   0.01313  -0.0204   0.9999   1.0000
   2.500   0.2449   0.02557   0.01480  -0.0282   0.9791   1.0000
   2.750   0.3052   0.02702   0.01636  -0.0356   0.9564   1.0000
   3.000   0.3567   0.02807   0.01754  -0.0410   0.9319   1.0000
   3.250   0.4077   0.02898   0.01864  -0.0459   0.9077   1.0000
   3.500   0.4618   0.02967   0.01954  -0.0508   0.8832   1.0000
   3.750   0.5189   0.03001   0.02016  -0.0554   0.8574   1.0000
   4.000   0.5735   0.02997   0.02046  -0.0589   0.8294   1.0000
   4.250   0.6327   0.02936   0.02022  -0.0620   0.8007   1.0000
   4.500   0.6765   0.02870   0.01987  -0.0621   0.7692   1.0000
   4.750   0.7207   0.02762   0.01916  -0.0614   0.7359   1.0000
   5.000   0.7641   0.02613   0.01796  -0.0596   0.6994   1.0000
   5.250   0.7975   0.02487   0.01689  -0.0565   0.6543   1.0000
   5.500   0.8266   0.02369   0.01578  -0.0526   0.5997   1.0000
   5.750   0.8497   0.02314   0.01501  -0.0486   0.5346   1.0000
   6.000   0.8683   0.02352   0.01501  -0.0450   0.4631   1.0000
   6.250   0.8834   0.02469   0.01575  -0.0419   0.3877   1.0000
   6.500   0.8973   0.02639   0.01693  -0.0389   0.3121   1.0000
   6.750   0.9146   0.02867   0.01877  -0.0368   0.2483   1.0000
   7.000   0.9339   0.03085   0.02074  -0.0351   0.2039   1.0000
   7.250   0.9579   0.03339   0.02324  -0.0340   0.1750   1.0000
   7.500   0.9791   0.03582   0.02567  -0.0328   0.1515   1.0000
   7.750   1.0007   0.03883   0.02894  -0.0316   0.1355   1.0000
   8.000   1.0190   0.04189   0.03227  -0.0301   0.1216   1.0000
   8.250   1.0359   0.04536   0.03600  -0.0288   0.1120   1.0000
   8.500   1.0521   0.04861   0.03946  -0.0275   0.1033   1.0000
   8.750   1.0621   0.05336   0.04471  -0.0258   0.1009   1.0000
   9.000   1.0630   0.05790   0.04989  -0.0236   0.0998   1.0000
   9.250   1.0588   0.06257   0.05509  -0.0216   0.0990   1.0000
   9.500   1.0502   0.06735   0.06027  -0.0199   0.0989   1.0000
   9.750   1.0379   0.07217   0.06541  -0.0185   0.0992   1.0000
  10.000   1.0236   0.07707   0.07052  -0.0176   0.0999   1.0000
  10.250   1.0066   0.08178   0.07536  -0.0167   0.1005   1.0000
  10.500   0.9933   0.08687   0.08052  -0.0167   0.1013   1.0000
  10.750   0.9323   0.09673   0.09050  -0.0231   0.1136   1.0000
  11.000   0.8812   0.11108   0.10475  -0.0358   0.1256   1.0000
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