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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 500,000
Max Cl/Cd: 79.34 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-500000-n5.txt
Download as CSV file: xf-hq2090sm-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4925   0.08491   0.08267  -0.0278   1.0000   0.0050
  -9.250  -0.4997   0.07923   0.07703  -0.0309   1.0000   0.0047
  -9.000  -0.5082   0.07352   0.07137  -0.0343   1.0000   0.0049
  -8.750  -0.5254   0.06643   0.06434  -0.0394   1.0000   0.0047
  -8.500  -0.5506   0.05701   0.05488  -0.0483   1.0000   0.0045
  -8.250  -0.5678   0.04930   0.04700  -0.0509   1.0000   0.0045
  -8.000  -0.5943   0.02551   0.02173  -0.0581   0.9879   0.0045
  -7.750  -0.5677   0.02266   0.01847  -0.0597   0.9832   0.0048
  -7.500  -0.5386   0.02097   0.01651  -0.0610   0.9788   0.0052
  -7.250  -0.5106   0.01869   0.01383  -0.0621   0.9739   0.0055
  -7.000  -0.4816   0.01708   0.01193  -0.0629   0.9686   0.0058
  -6.750  -0.4525   0.01563   0.01022  -0.0637   0.9635   0.0059
  -6.500  -0.4243   0.01451   0.00890  -0.0640   0.9569   0.0061
  -6.250  -0.3956   0.01367   0.00788  -0.0645   0.9508   0.0064
  -6.000  -0.3699   0.01244   0.00647  -0.0643   0.9425   0.0071
  -5.750  -0.3428   0.01185   0.00579  -0.0643   0.9350   0.0078
  -5.500  -0.3159   0.01138   0.00524  -0.0642   0.9267   0.0088
  -5.250  -0.2895   0.01096   0.00473  -0.0639   0.9179   0.0100
  -5.000  -0.2630   0.01054   0.00427  -0.0637   0.9096   0.0124
  -4.750  -0.2364   0.01023   0.00388  -0.0634   0.9004   0.0159
  -4.500  -0.2098   0.00990   0.00354  -0.0632   0.8917   0.0207
  -4.000  -0.1560   0.00944   0.00299  -0.0628   0.8746   0.0311
  -3.750  -0.1288   0.00929   0.00279  -0.0627   0.8665   0.0362
  -3.500  -0.1018   0.00904   0.00252  -0.0625   0.8583   0.0457
  -3.250  -0.0746   0.00885   0.00229  -0.0624   0.8504   0.0542
  -3.000  -0.0474   0.00866   0.00209  -0.0622   0.8425   0.0683
  -2.750  -0.0202   0.00846   0.00193  -0.0621   0.8344   0.0910
  -2.500   0.0068   0.00820   0.00176  -0.0620   0.8263   0.1310
  -2.250   0.0335   0.00787   0.00160  -0.0620   0.8164   0.1936
  -2.000   0.0598   0.00743   0.00143  -0.0620   0.8065   0.2913
  -1.750   0.0853   0.00685   0.00132  -0.0619   0.7977   0.4473
  -1.500   0.1119   0.00657   0.00128  -0.0617   0.7893   0.5332
  -1.250   0.1391   0.00647   0.00125  -0.0615   0.7818   0.5740
  -1.000   0.1662   0.00639   0.00126  -0.0613   0.7734   0.6178
  -0.750   0.1933   0.00634   0.00127  -0.0610   0.7635   0.6564
  -0.500   0.2199   0.00632   0.00129  -0.0606   0.7516   0.6910
  -0.250   0.2469   0.00633   0.00129  -0.0603   0.7385   0.7131
   0.000   0.2743   0.00635   0.00127  -0.0601   0.7262   0.7227
   0.250   0.3018   0.00637   0.00127  -0.0600   0.7152   0.7312
   0.500   0.3296   0.00640   0.00128  -0.0599   0.7041   0.7402
   0.750   0.3569   0.00642   0.00129  -0.0597   0.6915   0.7486
   1.000   0.3841   0.00647   0.00131  -0.0595   0.6751   0.7573
   1.500   0.4381   0.00659   0.00137  -0.0590   0.6394   0.7754
   1.750   0.4649   0.00667   0.00141  -0.0587   0.6189   0.7853
   2.000   0.4913   0.00676   0.00148  -0.0584   0.5948   0.7960
   2.250   0.5172   0.00689   0.00155  -0.0580   0.5667   0.8077
   2.500   0.5427   0.00704   0.00165  -0.0575   0.5349   0.8210
   2.750   0.5675   0.00724   0.00177  -0.0569   0.4976   0.8372
   3.000   0.5916   0.00746   0.00192  -0.0561   0.4602   0.8577
   3.250   0.6141   0.00774   0.00210  -0.0550   0.4113   0.8885
   3.500   0.6402   0.00810   0.00229  -0.0548   0.3499   0.9435
   3.750   0.6720   0.00847   0.00250  -0.0560   0.3065   1.0000
   4.000   0.6967   0.00891   0.00276  -0.0557   0.2643   1.0000
   4.250   0.7218   0.00931   0.00300  -0.0554   0.2299   1.0000
   4.500   0.7473   0.00964   0.00324  -0.0551   0.2050   1.0000
   4.750   0.7725   0.01001   0.00350  -0.0548   0.1770   1.0000
   5.000   0.7974   0.01042   0.00379  -0.0545   0.1489   1.0000
   5.250   0.8221   0.01084   0.00413  -0.0541   0.1232   1.0000
   5.500   0.8465   0.01129   0.00447  -0.0537   0.0976   1.0000
   6.000   0.8946   0.01228   0.00527  -0.0528   0.0565   1.0000
   6.250   0.9190   0.01271   0.00568  -0.0524   0.0459   1.0000
   6.500   0.9433   0.01316   0.00609  -0.0519   0.0368   1.0000
   6.750   0.9678   0.01356   0.00652  -0.0515   0.0306   1.0000
   7.000   0.9917   0.01403   0.00698  -0.0510   0.0246   1.0000
   7.250   1.0157   0.01446   0.00744  -0.0505   0.0194   1.0000
   7.500   1.0385   0.01505   0.00800  -0.0499   0.0126   1.0000
   7.750   1.0608   0.01568   0.00863  -0.0492   0.0091   1.0000
   8.000   1.0826   0.01639   0.00938  -0.0483   0.0071   1.0000
   8.250   1.1043   0.01708   0.01019  -0.0475   0.0063   1.0000
   8.500   1.1258   0.01774   0.01096  -0.0466   0.0058   1.0000
   8.750   1.1466   0.01848   0.01180  -0.0457   0.0054   1.0000
   9.000   1.1665   0.01928   0.01271  -0.0446   0.0051   1.0000
   9.250   1.1856   0.02013   0.01367  -0.0435   0.0047   1.0000
   9.500   1.2031   0.02112   0.01477  -0.0422   0.0044   1.0000
   9.750   1.2188   0.02226   0.01603  -0.0407   0.0041   1.0000
  10.000   1.2284   0.02397   0.01792  -0.0384   0.0038   1.0000
  10.250   1.2422   0.02514   0.01922  -0.0367   0.0037   1.0000
  10.500   1.2576   0.02604   0.02027  -0.0352   0.0035   1.0000
  10.750   1.2695   0.02704   0.02140  -0.0333   0.0033   1.0000
  11.000   1.2755   0.02842   0.02294  -0.0306   0.0032   1.0000
  11.250   1.2816   0.02979   0.02446  -0.0281   0.0031   1.0000
  11.500   1.2865   0.03127   0.02609  -0.0258   0.0030   1.0000
  11.750   1.2887   0.03303   0.02802  -0.0235   0.0029   1.0000
  12.000   1.2901   0.03492   0.03008  -0.0216   0.0028   1.0000
  12.250   1.2894   0.03712   0.03245  -0.0198   0.0027   1.0000
  12.500   1.2869   0.03962   0.03513  -0.0184   0.0027   1.0000
  12.750   1.2832   0.04239   0.03807  -0.0174   0.0027   1.0000
  13.000   1.2809   0.04513   0.04096  -0.0169   0.0025   1.0000
  13.250   1.2670   0.04957   0.04564  -0.0169   0.0026   1.0000
  13.500   1.2644   0.05279   0.04898  -0.0175   0.0025   1.0000
  13.750   1.2552   0.05721   0.05357  -0.0188   0.0025   1.0000
  14.000   1.2384   0.06324   0.05982  -0.0211   0.0025   1.0000
  14.250   1.2246   0.06937   0.06611  -0.0242   0.0025   1.0000
  14.500   1.2075   0.07672   0.07365  -0.0284   0.0025   1.0000
  14.750   1.1862   0.08561   0.08273  -0.0337   0.0025   1.0000
  15.000   1.1601   0.09632   0.09365  -0.0401   0.0026   1.0000
  15.250   1.1355   0.10722   0.10471  -0.0466   0.0026   1.0000
  15.500   1.1098   0.11882   0.11646  -0.0533   0.0027   1.0000
  15.750   1.0797   0.13195   0.12973  -0.0607   0.0028   1.0000
  16.000   1.0447   0.14737   0.14528  -0.0692   0.0029   1.0000
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