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HQ-2.0/9 9.0% smoothed (hq2090sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ-2.0/9 9.0% smoothed (hq2090sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 104.68 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2090sm-il-1000000.txt
Download as CSV file: xf-hq2090sm-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3898   0.10544   0.10388  -0.0201   1.0000   0.0095
 -10.750  -0.3900   0.10055   0.09900  -0.0218   1.0000   0.0095
  -7.750  -0.5874   0.02071   0.01711  -0.0564   0.9915   0.0067
  -7.500  -0.5589   0.01789   0.01389  -0.0579   0.9882   0.0067
  -7.250  -0.5279   0.01604   0.01179  -0.0595   0.9858   0.0069
  -7.000  -0.4948   0.01499   0.01060  -0.0612   0.9840   0.0073
  -6.750  -0.4638   0.01377   0.00921  -0.0623   0.9806   0.0075
  -6.500  -0.4346   0.01255   0.00782  -0.0628   0.9754   0.0077
  -6.250  -0.4033   0.01166   0.00681  -0.0638   0.9711   0.0081
  -6.000  -0.3755   0.01095   0.00600  -0.0639   0.9643   0.0087
  -5.750  -0.3476   0.01044   0.00539  -0.0639   0.9572   0.0093
  -5.500  -0.3227   0.00975   0.00458  -0.0633   0.9482   0.0100
  -5.250  -0.2972   0.00917   0.00392  -0.0628   0.9400   0.0113
  -5.000  -0.2713   0.00888   0.00358  -0.0624   0.9306   0.0126
  -4.750  -0.2449   0.00864   0.00330  -0.0620   0.9216   0.0142
  -4.500  -0.2189   0.00828   0.00290  -0.0616   0.9127   0.0192
  -4.250  -0.1924   0.00798   0.00257  -0.0613   0.9028   0.0252
  -4.000  -0.1654   0.00786   0.00242  -0.0611   0.8936   0.0289
  -3.750  -0.1387   0.00761   0.00213  -0.0608   0.8847   0.0361
  -3.500  -0.1114   0.00747   0.00194  -0.0606   0.8753   0.0419
  -3.250  -0.0844   0.00728   0.00176  -0.0605   0.8659   0.0541
  -3.000  -0.0575   0.00706   0.00159  -0.0603   0.8559   0.0784
  -2.750  -0.0306   0.00681   0.00143  -0.0601   0.8458   0.1180
  -2.500  -0.0038   0.00645   0.00128  -0.0601   0.8371   0.1893
  -2.250   0.0219   0.00584   0.00110  -0.0601   0.8292   0.3330
  -2.000   0.0482   0.00536   0.00101  -0.0600   0.8210   0.4632
  -1.750   0.0753   0.00515   0.00096  -0.0599   0.8133   0.5310
  -1.500   0.1024   0.00500   0.00093  -0.0598   0.8039   0.5864
  -1.250   0.1298   0.00493   0.00092  -0.0596   0.7939   0.6229
  -1.000   0.1573   0.00491   0.00091  -0.0594   0.7838   0.6501
  -0.750   0.1850   0.00491   0.00089  -0.0593   0.7737   0.6681
  -0.500   0.2130   0.00490   0.00089  -0.0592   0.7647   0.6876
  -0.250   0.2406   0.00490   0.00090  -0.0591   0.7563   0.7056
   0.000   0.2681   0.00490   0.00093  -0.0589   0.7468   0.7277
   0.250   0.2958   0.00491   0.00094  -0.0588   0.7360   0.7428
   0.500   0.3234   0.00492   0.00095  -0.0586   0.7245   0.7517
   0.750   0.3512   0.00495   0.00095  -0.0585   0.7134   0.7602
   1.250   0.4064   0.00501   0.00100  -0.0583   0.6892   0.7779
   1.500   0.4341   0.00504   0.00102  -0.0582   0.6759   0.7874
   1.750   0.4614   0.00509   0.00106  -0.0581   0.6602   0.7977
   2.000   0.4886   0.00513   0.00110  -0.0579   0.6429   0.8088
   2.250   0.5154   0.00519   0.00116  -0.0576   0.6209   0.8216
   2.500   0.5416   0.00528   0.00122  -0.0572   0.5929   0.8371
   3.000   0.5897   0.00568   0.00143  -0.0557   0.4974   0.8876
   3.250   0.6134   0.00586   0.00157  -0.0548   0.4470   0.9487
   3.500   0.6473   0.00624   0.00173  -0.0564   0.3904   1.0000
   3.750   0.6724   0.00664   0.00191  -0.0561   0.3385   1.0000
   4.000   0.6976   0.00703   0.00212  -0.0558   0.2934   1.0000
   4.250   0.7235   0.00734   0.00231  -0.0555   0.2625   1.0000
   4.500   0.7493   0.00765   0.00251  -0.0553   0.2355   1.0000
   4.750   0.7750   0.00798   0.00272  -0.0550   0.2052   1.0000
   5.000   0.8002   0.00835   0.00296  -0.0547   0.1738   1.0000
   5.250   0.8249   0.00880   0.00324  -0.0543   0.1392   1.0000
   5.500   0.8488   0.00933   0.00357  -0.0539   0.0994   1.0000
   5.750   0.8729   0.00984   0.00393  -0.0534   0.0698   1.0000
   6.000   0.8974   0.01029   0.00428  -0.0530   0.0527   1.0000
   6.250   0.9225   0.01065   0.00462  -0.0526   0.0428   1.0000
   6.500   0.9479   0.01098   0.00494  -0.0523   0.0362   1.0000
   6.750   0.9726   0.01138   0.00531  -0.0519   0.0291   1.0000
   7.000   0.9972   0.01178   0.00567  -0.0515   0.0222   1.0000
   7.250   1.0207   0.01232   0.00617  -0.0509   0.0138   1.0000
   7.500   1.0443   0.01286   0.00670  -0.0502   0.0105   1.0000
   7.750   1.0675   0.01345   0.00737  -0.0495   0.0090   1.0000
   8.000   1.0909   0.01397   0.00795  -0.0489   0.0082   1.0000
   8.250   1.1137   0.01454   0.00857  -0.0482   0.0075   1.0000
   8.500   1.1350   0.01529   0.00939  -0.0472   0.0068   1.0000
   8.750   1.1510   0.01668   0.01095  -0.0455   0.0062   1.0000
   9.000   1.1730   0.01727   0.01161  -0.0447   0.0060   1.0000
   9.250   1.1931   0.01806   0.01251  -0.0436   0.0058   1.0000
   9.500   1.2130   0.01882   0.01335  -0.0426   0.0054   1.0000
   9.750   1.2322   0.01963   0.01424  -0.0414   0.0051   1.0000
  10.000   1.2505   0.02048   0.01518  -0.0402   0.0048   1.0000
  10.250   1.2675   0.02141   0.01620  -0.0389   0.0047   1.0000
  10.500   1.2827   0.02247   0.01736  -0.0373   0.0045   1.0000
  10.750   1.2956   0.02370   0.01870  -0.0354   0.0044   1.0000
  11.000   1.3043   0.02522   0.02036  -0.0331   0.0042   1.0000
  11.250   1.3079   0.02677   0.02205  -0.0299   0.0041   1.0000
  11.500   1.3055   0.02874   0.02421  -0.0262   0.0040   1.0000
  11.750   1.3021   0.03087   0.02654  -0.0229   0.0040   1.0000
  12.000   1.2968   0.03328   0.02914  -0.0199   0.0040   1.0000
  12.250   1.2824   0.03673   0.03285  -0.0169   0.0039   1.0000
  12.500   1.2678   0.04040   0.03676  -0.0148   0.0039   1.0000
  12.750   1.2605   0.04347   0.03999  -0.0137   0.0039   1.0000
  13.000   1.2428   0.04802   0.04477  -0.0132   0.0038   1.0000
  13.250   1.2343   0.05175   0.04865  -0.0136   0.0038   1.0000
  13.500   1.2422   0.05349   0.05047  -0.0141   0.0037   1.0000
  13.750   1.2235   0.05932   0.05649  -0.0160   0.0038   1.0000
  14.000   1.2093   0.06504   0.06237  -0.0186   0.0038   1.0000
  14.250   1.1904   0.07226   0.06977  -0.0226   0.0038   1.0000
  14.500   1.1558   0.08341   0.08113  -0.0293   0.0038   1.0000
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