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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 1,000,000
Max Cl/Cd: 129.27 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3510-il-1000000.txt
Download as CSV file: xf-hq3510-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3368   0.10453   0.10291  -0.0385   1.0000   0.0084
  -9.750  -0.3365   0.10141   0.09982  -0.0387   1.0000   0.0084
  -9.500  -0.3386   0.09862   0.09706  -0.0383   1.0000   0.0084
  -9.250  -0.3347   0.09528   0.09373  -0.0397   0.9995   0.0084
  -9.000  -0.3221   0.09050   0.08896  -0.0443   0.9979   0.0084
  -8.750  -0.3091   0.08572   0.08418  -0.0492   0.9949   0.0085
  -8.500  -0.2976   0.08098   0.07944  -0.0538   0.9907   0.0085
  -8.250  -0.2848   0.07571   0.07419  -0.0596   0.9863   0.0085
  -8.000  -0.2801   0.06705   0.06555  -0.0697   0.9795   0.0087
  -7.750  -0.2596   0.05784   0.05633  -0.0862   0.9716   0.0089
  -7.500  -0.2395   0.04939   0.04773  -0.1002   0.9590   0.0091
  -7.250  -0.2266   0.04486   0.04305  -0.1046   0.9454   0.0093
  -7.000  -0.2161   0.04076   0.03878  -0.1067   0.9324   0.0094
  -6.750  -0.2034   0.03738   0.03522  -0.1077   0.9217   0.0097
  -6.500  -0.1887   0.03382   0.03144  -0.1085   0.9124   0.0101
  -6.250  -0.1872   0.02013   0.01662  -0.1078   0.9005   0.0088
  -6.000  -0.1648   0.01779   0.01395  -0.1075   0.8936   0.0087
  -5.750  -0.1421   0.01531   0.01106  -0.1071   0.8875   0.0087
  -5.500  -0.1175   0.01360   0.00909  -0.1068   0.8815   0.0088
  -5.250  -0.0921   0.01228   0.00754  -0.1065   0.8757   0.0088
  -5.000  -0.0663   0.01115   0.00623  -0.1062   0.8704   0.0090
  -4.750  -0.0403   0.01026   0.00523  -0.1060   0.8644   0.0095
  -4.500  -0.0137   0.00962   0.00446  -0.1057   0.8591   0.0097
  -4.250   0.0132   0.00903   0.00378  -0.1056   0.8534   0.0098
  -4.000   0.0404   0.00857   0.00322  -0.1054   0.8476   0.0101
  -3.750   0.0680   0.00821   0.00278  -0.1053   0.8423   0.0108
  -3.500   0.0957   0.00791   0.00242  -0.1052   0.8361   0.0121
  -3.250   0.1234   0.00769   0.00210  -0.1051   0.8301   0.0133
  -3.000   0.1512   0.00742   0.00183  -0.1050   0.8226   0.0188
  -2.750   0.1787   0.00724   0.00169  -0.1050   0.8148   0.0382
  -2.500   0.2064   0.00711   0.00156  -0.1049   0.8058   0.0495
  -2.250   0.2342   0.00699   0.00144  -0.1049   0.7974   0.0617
  -2.000   0.2618   0.00685   0.00133  -0.1048   0.7893   0.0860
  -1.750   0.2890   0.00641   0.00121  -0.1050   0.7813   0.1961
  -1.500   0.3149   0.00560   0.00109  -0.1052   0.7737   0.4461
  -1.250   0.3421   0.00537   0.00108  -0.1052   0.7649   0.5367
  -1.000   0.3698   0.00531   0.00107  -0.1051   0.7569   0.5794
  -0.750   0.3975   0.00529   0.00106  -0.1050   0.7485   0.6074
  -0.500   0.4252   0.00529   0.00106  -0.1050   0.7388   0.6294
  -0.250   0.4527   0.00528   0.00108  -0.1048   0.7292   0.6580
   0.000   0.4800   0.00530   0.00111  -0.1046   0.7199   0.6859
   0.250   0.5074   0.00530   0.00115  -0.1045   0.7111   0.7112
   0.500   0.5349   0.00533   0.00118  -0.1044   0.7017   0.7250
   0.750   0.5624   0.00539   0.00119  -0.1042   0.6910   0.7336
   1.000   0.5900   0.00543   0.00122  -0.1042   0.6801   0.7423
   1.250   0.6175   0.00547   0.00125  -0.1041   0.6694   0.7508
   1.500   0.6448   0.00553   0.00129  -0.1039   0.6572   0.7602
   1.750   0.6718   0.00560   0.00134  -0.1038   0.6435   0.7699
   2.000   0.6986   0.00567   0.00140  -0.1036   0.6287   0.7798
   2.250   0.7252   0.00576   0.00146  -0.1033   0.6116   0.7907
   2.500   0.7513   0.00588   0.00153  -0.1030   0.5908   0.8028
   2.750   0.7768   0.00602   0.00162  -0.1025   0.5661   0.8165
   3.000   0.8015   0.00620   0.00174  -0.1019   0.5352   0.8328
   3.250   0.8251   0.00641   0.00187  -0.1011   0.4984   0.8546
   3.500   0.8457   0.00655   0.00202  -0.0996   0.4602   0.9061
   3.750   0.8749   0.00683   0.00220  -0.1002   0.4193   1.0000
   4.000   0.8991   0.00721   0.00241  -0.0997   0.3815   1.0000
   4.250   0.9231   0.00760   0.00262  -0.0991   0.3436   1.0000
   4.500   0.9471   0.00799   0.00285  -0.0986   0.3095   1.0000
   4.750   0.9713   0.00835   0.00308  -0.0981   0.2842   1.0000
   5.000   0.9963   0.00863   0.00331  -0.0977   0.2678   1.0000
   5.250   1.0214   0.00890   0.00352  -0.0973   0.2535   1.0000
   5.500   1.0463   0.00918   0.00374  -0.0970   0.2391   1.0000
   5.750   1.0712   0.00945   0.00396  -0.0966   0.2247   1.0000
   6.000   1.0960   0.00972   0.00418  -0.0962   0.2109   1.0000
   6.250   1.1199   0.01005   0.00444  -0.0956   0.1915   1.0000
   6.500   1.1431   0.01045   0.00472  -0.0950   0.1675   1.0000
   6.750   1.1643   0.01099   0.00508  -0.0941   0.1368   1.0000
   7.000   1.1845   0.01161   0.00553  -0.0930   0.1060   1.0000
   7.250   1.2032   0.01235   0.00607  -0.0916   0.0738   1.0000
   7.500   1.2194   0.01331   0.00679  -0.0899   0.0369   1.0000
   7.750   1.2334   0.01447   0.00773  -0.0878   0.0070   1.0000
   8.000   1.2540   0.01502   0.00830  -0.0866   0.0050   1.0000
   8.250   1.2749   0.01551   0.00886  -0.0856   0.0046   1.0000
   8.500   1.2948   0.01606   0.00947  -0.0843   0.0044   1.0000
   8.750   1.3138   0.01665   0.01013  -0.0830   0.0042   1.0000
   9.000   1.3319   0.01728   0.01083  -0.0815   0.0040   1.0000
   9.250   1.3480   0.01796   0.01160  -0.0797   0.0038   1.0000
   9.500   1.3611   0.01872   0.01243  -0.0774   0.0036   1.0000
   9.750   1.3718   0.01958   0.01338  -0.0747   0.0035   1.0000
  10.000   1.3804   0.02057   0.01448  -0.0718   0.0034   1.0000
  10.250   1.3877   0.02165   0.01567  -0.0689   0.0033   1.0000
  10.500   1.3914   0.02300   0.01714  -0.0656   0.0032   1.0000
  10.750   1.3951   0.02438   0.01863  -0.0626   0.0032   1.0000
  11.000   1.3945   0.02614   0.02053  -0.0593   0.0032   1.0000
  11.250   1.3931   0.02809   0.02260  -0.0562   0.0031   1.0000
  11.500   1.4027   0.02923   0.02382  -0.0545   0.0031   1.0000
  11.750   1.4075   0.03082   0.02551  -0.0525   0.0031   1.0000
  12.000   1.4110   0.03258   0.02739  -0.0506   0.0030   1.0000
  12.250   1.4170   0.03418   0.02910  -0.0490   0.0030   1.0000
  12.500   1.4180   0.03634   0.03138  -0.0473   0.0029   1.0000
  12.750   1.4166   0.03884   0.03400  -0.0457   0.0029   1.0000
  13.000   1.4184   0.04109   0.03638  -0.0446   0.0028   1.0000
  13.250   1.4182   0.04367   0.03907  -0.0436   0.0028   1.0000
  13.500   1.4151   0.04670   0.04224  -0.0428   0.0027   1.0000
  13.750   1.4114   0.04994   0.04562  -0.0423   0.0026   1.0000
  14.000   1.4056   0.05362   0.04943  -0.0420   0.0026   1.0000
  14.250   1.3998   0.05747   0.05343  -0.0422   0.0025   1.0000
  14.500   1.3921   0.06182   0.05793  -0.0428   0.0025   1.0000
  14.750   1.3823   0.06672   0.06299  -0.0437   0.0025   1.0000
  15.000   1.3724   0.07190   0.06832  -0.0452   0.0025   1.0000
  15.250   1.3612   0.07761   0.07419  -0.0472   0.0025   1.0000
  15.500   1.3476   0.08405   0.08080  -0.0498   0.0025   1.0000
  15.750   1.3348   0.09065   0.08755  -0.0528   0.0025   1.0000
  16.000   1.3201   0.09794   0.09501  -0.0564   0.0025   1.0000
  16.250   1.3040   0.10585   0.10309  -0.0605   0.0025   1.0000
  16.500   1.2887   0.11385   0.11124  -0.0649   0.0026   1.0000
  16.750   1.2740   0.12202   0.11956  -0.0696   0.0026   1.0000
  17.000   1.2581   0.13074   0.12843  -0.0748   0.0026   1.0000
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