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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.79 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq359-il-1000000-n5.txt
Download as CSV file: xf-hq359-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/9 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.3440   0.10840   0.10674  -0.0337   1.0000   0.0029
  -9.750  -0.3417   0.10527   0.10363  -0.0343   1.0000   0.0027
  -9.500  -0.3403   0.10143   0.09981  -0.0353   0.9998   0.0024
  -9.000  -0.3241   0.09222   0.09062  -0.0419   0.9901   0.0022
  -8.750  -0.3145   0.08730   0.08570  -0.0461   0.9855   0.0022
  -8.500  -0.3040   0.08273   0.08114  -0.0505   0.9795   0.0022
  -8.250  -0.2893   0.07763   0.07604  -0.0565   0.9748   0.0022
  -8.000  -0.2719   0.07214   0.07054  -0.0640   0.9681   0.0022
  -7.750  -0.2517   0.06663   0.06502  -0.0726   0.9582   0.0023
  -7.500  -0.2349   0.06136   0.05970  -0.0811   0.9412   0.0025
  -7.250  -0.2238   0.05548   0.05374  -0.0901   0.9212   0.0029
  -7.000  -0.2169   0.04950   0.04762  -0.0962   0.9053   0.0029
  -6.750  -0.2076   0.04378   0.04172  -0.1002   0.8931   0.0031
  -6.500  -0.1953   0.03806   0.03578  -0.1030   0.8832   0.0031
  -6.250  -0.1800   0.03201   0.02942  -0.1050   0.8749   0.0032
  -6.000  -0.1641   0.02318   0.02003  -0.1059   0.8669   0.0035
  -5.750  -0.1440   0.01664   0.01278  -0.1059   0.8606   0.0037
  -5.500  -0.1188   0.01470   0.01049  -0.1058   0.8547   0.0038
  -5.250  -0.0929   0.01323   0.00871  -0.1057   0.8495   0.0038
  -5.000  -0.0671   0.01149   0.00665  -0.1056   0.8437   0.0040
  -4.750  -0.0409   0.01039   0.00537  -0.1055   0.8383   0.0044
  -4.500  -0.0136   0.00994   0.00485  -0.1055   0.8329   0.0048
  -4.250   0.0137   0.00952   0.00434  -0.1054   0.8272   0.0052
  -4.000   0.0410   0.00911   0.00383  -0.1054   0.8217   0.0056
  -3.750   0.0686   0.00874   0.00338  -0.1053   0.8156   0.0060
  -3.500   0.0961   0.00844   0.00301  -0.1053   0.8097   0.0064
  -3.250   0.1239   0.00821   0.00272  -0.1053   0.8029   0.0067
  -3.000   0.1514   0.00791   0.00233  -0.1052   0.7946   0.0068
  -2.750   0.1787   0.00768   0.00198  -0.1051   0.7827   0.0069
  -2.500   0.2060   0.00748   0.00166  -0.1049   0.7678   0.0071
  -2.250   0.2334   0.00732   0.00137  -0.1047   0.7537   0.0081
  -2.000   0.2612   0.00721   0.00120  -0.1047   0.7429   0.0097
  -1.750   0.2889   0.00712   0.00108  -0.1046   0.7316   0.0142
  -1.500   0.3165   0.00702   0.00099  -0.1046   0.7206   0.0333
  -1.250   0.3440   0.00693   0.00093  -0.1046   0.7095   0.0534
  -1.000   0.3715   0.00686   0.00088  -0.1046   0.6979   0.0794
  -0.750   0.3989   0.00668   0.00083  -0.1046   0.6860   0.1473
  -0.500   0.4252   0.00599   0.00079  -0.1049   0.6712   0.4118
  -0.250   0.4519   0.00578   0.00081  -0.1049   0.6553   0.5217
   0.000   0.4788   0.00572   0.00085  -0.1047   0.6406   0.5858
   0.250   0.5058   0.00571   0.00091  -0.1046   0.6262   0.6330
   0.500   0.5325   0.00574   0.00097  -0.1044   0.6088   0.6735
   0.750   0.5591   0.00584   0.00102  -0.1041   0.5884   0.6897
   1.250   0.6124   0.00612   0.00113  -0.1037   0.5414   0.7057
   1.500   0.6383   0.00632   0.00122  -0.1034   0.5098   0.7141
   1.750   0.6641   0.00654   0.00132  -0.1031   0.4797   0.7231
   2.000   0.6898   0.00677   0.00144  -0.1027   0.4473   0.7318
   2.250   0.7153   0.00702   0.00158  -0.1024   0.4153   0.7413
   2.500   0.7410   0.00725   0.00171  -0.1021   0.3873   0.7518
   2.750   0.7662   0.00751   0.00187  -0.1017   0.3550   0.7632
   3.000   0.7910   0.00780   0.00204  -0.1013   0.3186   0.7752
   3.250   0.8159   0.00808   0.00221  -0.1008   0.2894   0.7883
   3.500   0.8414   0.00828   0.00239  -0.1005   0.2718   0.8030
   3.750   0.8669   0.00844   0.00255  -0.1001   0.2589   0.8206
   4.000   0.8918   0.00859   0.00272  -0.0996   0.2443   0.8449
   4.250   0.9130   0.00863   0.00289  -0.0983   0.2229   0.9259
   4.500   0.9412   0.00902   0.00313  -0.0987   0.1874   1.0000
   4.750   0.9658   0.00937   0.00336  -0.0983   0.1622   1.0000
   5.000   0.9900   0.00976   0.00362  -0.0979   0.1371   1.0000
   5.250   1.0127   0.01029   0.00397  -0.0972   0.1029   1.0000
   5.500   1.0337   0.01100   0.00444  -0.0962   0.0609   1.0000
   5.750   1.0527   0.01195   0.00512  -0.0949   0.0128   1.0000
   6.000   1.0763   0.01239   0.00552  -0.0943   0.0041   1.0000
   6.250   1.1009   0.01270   0.00585  -0.0938   0.0034   1.0000
   6.500   1.1250   0.01305   0.00624  -0.0933   0.0029   1.0000
   6.750   1.1485   0.01346   0.00670  -0.0926   0.0025   1.0000
   7.000   1.1716   0.01390   0.00720  -0.0919   0.0022   1.0000
   7.250   1.1935   0.01447   0.00787  -0.0910   0.0020   1.0000
   7.500   1.2138   0.01522   0.00872  -0.0898   0.0018   1.0000
   7.750   1.2360   0.01568   0.00923  -0.0890   0.0018   1.0000
   8.000   1.2582   0.01614   0.00972  -0.0882   0.0016   1.0000
   8.250   1.2790   0.01671   0.01035  -0.0872   0.0015   1.0000
   8.500   1.2991   0.01733   0.01104  -0.0861   0.0015   1.0000
   8.750   1.3179   0.01803   0.01182  -0.0848   0.0014   1.0000
   9.000   1.3359   0.01877   0.01263  -0.0833   0.0013   1.0000
   9.250   1.3527   0.01956   0.01350  -0.0817   0.0013   1.0000
   9.500   1.3683   0.02038   0.01444  -0.0800   0.0012   1.0000
   9.750   1.3808   0.02125   0.01540  -0.0777   0.0011   1.0000
  10.000   1.3919   0.02211   0.01634  -0.0752   0.0011   1.0000
  10.250   1.4023   0.02300   0.01732  -0.0727   0.0010   1.0000
  10.500   1.4118   0.02396   0.01837  -0.0702   0.0010   1.0000
  10.750   1.4207   0.02499   0.01950  -0.0678   0.0009   1.0000
  11.000   1.4279   0.02618   0.02079  -0.0653   0.0009   1.0000
  11.250   1.4357   0.02734   0.02204  -0.0631   0.0009   1.0000
  11.500   1.4412   0.02874   0.02354  -0.0607   0.0008   1.0000
  11.750   1.4443   0.03038   0.02529  -0.0584   0.0008   1.0000
  12.000   1.4453   0.03228   0.02732  -0.0560   0.0008   1.0000
  12.250   1.4374   0.03511   0.03032  -0.0533   0.0007   1.0000
  12.500   1.4205   0.03909   0.03452  -0.0505   0.0006   1.0000
  12.750   1.4259   0.04091   0.03645  -0.0495   0.0006   1.0000
  13.000   1.4225   0.04381   0.03952  -0.0484   0.0006   1.0000
  13.250   1.4221   0.04648   0.04232  -0.0476   0.0006   1.0000
  13.500   1.4139   0.05026   0.04627  -0.0471   0.0006   1.0000
  13.750   1.4076   0.05403   0.05020  -0.0471   0.0006   1.0000
  14.000   1.4013   0.05803   0.05434  -0.0476   0.0006   1.0000
  14.250   1.3916   0.06280   0.05927  -0.0486   0.0006   1.0000
  14.500   1.3809   0.06806   0.06469  -0.0502   0.0006   1.0000
  14.750   1.3672   0.07424   0.07103  -0.0525   0.0006   1.0000
  15.000   1.3578   0.08009   0.07703  -0.0551   0.0006   1.0000
  15.250   1.3412   0.08765   0.08475  -0.0588   0.0006   1.0000
  15.500   1.3262   0.09535   0.09261  -0.0629   0.0006   1.0000
  15.750   1.3086   0.10397   0.10138  -0.0676   0.0006   1.0000
  16.000   1.2921   0.11263   0.11018  -0.0724   0.0006   1.0000
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