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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 85.19 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq209-il-1000000-n5.txt
Download as CSV file: xf-hq209-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4977   0.08674   0.08513  -0.0257   1.0000   0.0024
  -8.750  -0.6618   0.02174   0.01843  -0.0609   0.9832   0.0022
  -8.500  -0.6366   0.01891   0.01519  -0.0621   0.9761   0.0022
  -8.250  -0.6085   0.01718   0.01317  -0.0632   0.9695   0.0023
  -8.000  -0.5805   0.01589   0.01166  -0.0640   0.9608   0.0024
  -7.750  -0.5532   0.01499   0.01060  -0.0643   0.9507   0.0025
  -7.500  -0.5296   0.01339   0.00872  -0.0641   0.9380   0.0028
  -7.250  -0.5040   0.01283   0.00803  -0.0639   0.9261   0.0030
  -7.000  -0.4782   0.01244   0.00755  -0.0636   0.9153   0.0032
  -6.750  -0.4528   0.01195   0.00695  -0.0633   0.9052   0.0034
  -6.500  -0.4271   0.01151   0.00641  -0.0630   0.8962   0.0038
  -6.250  -0.4013   0.01109   0.00589  -0.0627   0.8881   0.0041
  -6.000  -0.3753   0.01063   0.00532  -0.0624   0.8802   0.0044
  -5.750  -0.3490   0.01026   0.00486  -0.0621   0.8732   0.0046
  -5.500  -0.3222   0.01002   0.00456  -0.0620   0.8663   0.0048
  -5.250  -0.2964   0.00942   0.00383  -0.0617   0.8597   0.0058
  -5.000  -0.2694   0.00918   0.00356  -0.0616   0.8532   0.0065
  -4.750  -0.2424   0.00892   0.00324  -0.0614   0.8473   0.0071
  -4.500  -0.2152   0.00866   0.00292  -0.0613   0.8410   0.0077
  -4.000  -0.1605   0.00822   0.00234  -0.0611   0.8286   0.0088
  -3.750  -0.1332   0.00798   0.00205  -0.0610   0.8220   0.0114
  -3.500  -0.1056   0.00777   0.00185  -0.0609   0.8153   0.0177
  -3.250  -0.0783   0.00758   0.00168  -0.0609   0.8078   0.0292
  -3.000  -0.0506   0.00746   0.00154  -0.0608   0.7992   0.0366
  -2.500   0.0042   0.00718   0.00127  -0.0607   0.7798   0.0642
  -2.250   0.0316   0.00698   0.00115  -0.0606   0.7697   0.0959
  -2.000   0.0585   0.00673   0.00103  -0.0606   0.7573   0.1505
  -1.750   0.0853   0.00647   0.00093  -0.0605   0.7428   0.2178
  -1.500   0.1121   0.00621   0.00082  -0.0605   0.7292   0.2891
  -1.250   0.1388   0.00591   0.00074  -0.0604   0.7165   0.3782
  -1.000   0.1657   0.00569   0.00069  -0.0604   0.7035   0.4542
  -0.750   0.1925   0.00550   0.00068  -0.0602   0.6896   0.5307
  -0.500   0.2196   0.00541   0.00068  -0.0601   0.6757   0.5821
  -0.250   0.2466   0.00539   0.00069  -0.0599   0.6588   0.6199
   0.000   0.2738   0.00541   0.00071  -0.0598   0.6422   0.6439
   0.250   0.3013   0.00543   0.00073  -0.0597   0.6284   0.6648
   0.500   0.3287   0.00546   0.00076  -0.0596   0.6121   0.6852
   0.750   0.3561   0.00552   0.00080  -0.0594   0.5936   0.6983
   1.000   0.3834   0.00561   0.00083  -0.0593   0.5747   0.7070
   1.250   0.4106   0.00571   0.00088  -0.0592   0.5509   0.7150
   1.750   0.4641   0.00602   0.00102  -0.0588   0.4924   0.7328
   2.000   0.4905   0.00622   0.00111  -0.0586   0.4584   0.7418
   2.500   0.5426   0.00670   0.00136  -0.0581   0.3826   0.7618
   2.750   0.5668   0.00714   0.00154  -0.0576   0.3131   0.7723
   3.000   0.5919   0.00749   0.00172  -0.0572   0.2673   0.7836
   3.250   0.6179   0.00771   0.00187  -0.0570   0.2432   0.7954
   3.500   0.6442   0.00787   0.00203  -0.0567   0.2254   0.8080
   3.750   0.6706   0.00801   0.00217  -0.0565   0.2126   0.8216
   4.000   0.6959   0.00823   0.00234  -0.0561   0.1870   0.8377
   4.250   0.7207   0.00846   0.00252  -0.0556   0.1603   0.8580
   4.500   0.7429   0.00876   0.00278  -0.0546   0.1209   0.8948
   4.750   0.7738   0.00920   0.00311  -0.0556   0.0748   1.0000
   5.000   0.7981   0.00967   0.00342  -0.0551   0.0468   1.0000
   5.250   0.8234   0.01002   0.00369  -0.0548   0.0341   1.0000
   5.500   0.8489   0.01034   0.00396  -0.0545   0.0244   1.0000
   5.750   0.8740   0.01069   0.00425  -0.0542   0.0163   1.0000
   6.000   0.8995   0.01100   0.00456  -0.0539   0.0113   1.0000
   6.250   0.9231   0.01155   0.00506  -0.0532   0.0036   1.0000
   6.500   0.9482   0.01189   0.00543  -0.0528   0.0029   1.0000
   6.750   0.9733   0.01222   0.00580  -0.0525   0.0026   1.0000
   7.000   0.9982   0.01257   0.00619  -0.0521   0.0025   1.0000
   7.250   1.0227   0.01296   0.00663  -0.0516   0.0024   1.0000
   7.500   1.0469   0.01337   0.00712  -0.0511   0.0022   1.0000
   7.750   1.0706   0.01383   0.00763  -0.0505   0.0020   1.0000
   8.000   1.0940   0.01433   0.00819  -0.0499   0.0018   1.0000
   8.250   1.1167   0.01487   0.00880  -0.0492   0.0017   1.0000
   8.500   1.1390   0.01547   0.00947  -0.0485   0.0016   1.0000
   8.750   1.1591   0.01632   0.01042  -0.0474   0.0014   1.0000
   9.000   1.1753   0.01763   0.01189  -0.0457   0.0012   1.0000
   9.250   1.1946   0.01849   0.01284  -0.0446   0.0012   1.0000
   9.500   1.2137   0.01931   0.01376  -0.0435   0.0012   1.0000
   9.750   1.2318   0.02020   0.01478  -0.0422   0.0012   1.0000
  10.000   1.2488   0.02116   0.01584  -0.0408   0.0011   1.0000
  10.250   1.2643   0.02221   0.01701  -0.0392   0.0011   1.0000
  10.500   1.2780   0.02334   0.01827  -0.0374   0.0011   1.0000
  10.750   1.2900   0.02454   0.01960  -0.0355   0.0011   1.0000
  11.000   1.2973   0.02587   0.02108  -0.0328   0.0011   1.0000
  11.250   1.3020   0.02716   0.02250  -0.0298   0.0011   1.0000
  11.500   1.3036   0.02868   0.02417  -0.0267   0.0011   1.0000
  11.750   1.3050   0.03028   0.02592  -0.0239   0.0010   1.0000
  12.000   1.3033   0.03223   0.02803  -0.0213   0.0010   1.0000
  12.250   1.3013   0.03432   0.03028  -0.0192   0.0010   1.0000
  12.500   1.2975   0.03672   0.03284  -0.0174   0.0010   1.0000
  12.750   1.2923   0.03944   0.03571  -0.0160   0.0010   1.0000
  13.000   1.2839   0.04271   0.03916  -0.0152   0.0010   1.0000
  13.250   1.2737   0.04649   0.04312  -0.0150   0.0010   1.0000
  13.500   1.2643   0.05052   0.04730  -0.0155   0.0010   1.0000
  13.750   1.2506   0.05555   0.05250  -0.0170   0.0010   1.0000
  14.000   1.2358   0.06130   0.05841  -0.0194   0.0010   1.0000
  14.250   1.2192   0.06796   0.06524  -0.0228   0.0010   1.0000
  14.500   1.2018   0.07554   0.07299  -0.0273   0.0010   1.0000
  14.750   1.1806   0.08470   0.08230  -0.0328   0.0010   1.0000
  15.000   1.1585   0.09471   0.09247  -0.0389   0.0010   1.0000
  15.250   1.1373   0.10489   0.10277  -0.0448   0.0011   1.0000
  15.500   1.1169   0.11490   0.11288  -0.0505   0.0011   1.0000
  15.750   1.0909   0.12663   0.12474  -0.0571   0.0011   1.0000
  16.000   1.0710   0.13708   0.13527  -0.0628   0.0011   1.0000
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