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HQ 3.5/13 AIRFOIL (hq3513-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/13 AIRFOIL (hq3513-il)
Reynolds number: 500,000
Max Cl/Cd: 105.6 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3513-il-500000.txt
Download as CSV file: xf-hq3513-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/13 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3477   0.09956   0.09742  -0.0495   0.9994   0.0252
 -10.250  -0.3394   0.09306   0.09093  -0.0556   0.9971   0.0253
 -10.000  -0.5346   0.02989   0.02623  -0.1088   0.9703   0.0130
  -9.750  -0.5164   0.02759   0.02368  -0.1101   0.9624   0.0132
  -9.500  -0.4903   0.02602   0.02192  -0.1118   0.9576   0.0137
  -9.250  -0.4708   0.02417   0.01982  -0.1121   0.9499   0.0141
  -9.000  -0.4505   0.02217   0.01751  -0.1123   0.9429   0.0144
  -8.750  -0.4314   0.02050   0.01558  -0.1116   0.9350   0.0147
  -8.500  -0.4100   0.01905   0.01388  -0.1111   0.9282   0.0150
  -8.250  -0.3883   0.01792   0.01255  -0.1104   0.9212   0.0154
  -8.000  -0.3651   0.01705   0.01149  -0.1098   0.9145   0.0157
  -7.750  -0.3446   0.01565   0.00995  -0.1090   0.9078   0.0164
  -7.500  -0.3212   0.01501   0.00925  -0.1085   0.9011   0.0172
  -7.250  -0.2958   0.01450   0.00865  -0.1082   0.8956   0.0182
  -7.000  -0.2718   0.01399   0.00807  -0.1076   0.8886   0.0194
  -6.750  -0.2475   0.01331   0.00727  -0.1071   0.8828   0.0206
  -6.500  -0.2219   0.01297   0.00694  -0.1068   0.8768   0.0231
  -6.250  -0.1967   0.01251   0.00642  -0.1064   0.8705   0.0267
  -6.000  -0.1692   0.01234   0.00621  -0.1063   0.8655   0.0317
  -5.750  -0.1438   0.01199   0.00587  -0.1060   0.8591   0.0378
  -5.500  -0.1172   0.01170   0.00551  -0.1058   0.8536   0.0421
  -5.250  -0.0903   0.01149   0.00528  -0.1057   0.8483   0.0462
  -5.000  -0.0631   0.01138   0.00512  -0.1055   0.8422   0.0497
  -4.750  -0.0368   0.01098   0.00468  -0.1054   0.8371   0.0542
  -4.500  -0.0098   0.01081   0.00449  -0.1052   0.8313   0.0589
  -4.250   0.0175   0.01064   0.00428  -0.1051   0.8256   0.0632
  -4.000   0.0444   0.01028   0.00388  -0.1050   0.8208   0.0699
  -3.750   0.0714   0.01009   0.00366  -0.1049   0.8146   0.0755
  -3.500   0.0984   0.00976   0.00335  -0.1047   0.8091   0.0888
  -3.250   0.1254   0.00943   0.00309  -0.1047   0.8040   0.1167
  -3.000   0.1509   0.00884   0.00286  -0.1047   0.7977   0.2115
  -2.750   0.1757   0.00806   0.00261  -0.1047   0.7922   0.3785
  -2.500   0.2014   0.00767   0.00257  -0.1044   0.7859   0.4907
  -2.250   0.2285   0.00755   0.00254  -0.1042   0.7792   0.5448
  -2.000   0.2559   0.00752   0.00252  -0.1039   0.7723   0.5781
  -1.750   0.2833   0.00750   0.00250  -0.1037   0.7647   0.6008
  -1.500   0.3112   0.00753   0.00249  -0.1035   0.7580   0.6216
  -1.250   0.3388   0.00754   0.00249  -0.1033   0.7512   0.6374
  -1.000   0.3669   0.00757   0.00248  -0.1032   0.7453   0.6497
  -0.750   0.3940   0.00761   0.00253  -0.1029   0.7379   0.6687
  -0.500   0.4214   0.00767   0.00257  -0.1026   0.7317   0.6862
  -0.250   0.4487   0.00769   0.00261  -0.1024   0.7246   0.6966
   0.000   0.4763   0.00772   0.00261  -0.1022   0.7180   0.7056
   0.500   0.5313   0.00776   0.00261  -0.1019   0.7026   0.7205
   0.750   0.5589   0.00779   0.00262  -0.1018   0.6949   0.7272
   1.000   0.5864   0.00782   0.00262  -0.1017   0.6878   0.7333
   1.250   0.6139   0.00784   0.00266  -0.1015   0.6803   0.7396
   1.500   0.6413   0.00789   0.00267  -0.1014   0.6725   0.7463
   1.750   0.6682   0.00791   0.00271  -0.1012   0.6635   0.7524
   2.000   0.6954   0.00798   0.00273  -0.1010   0.6549   0.7596
   2.250   0.7221   0.00799   0.00279  -0.1007   0.6454   0.7659
   2.500   0.7489   0.00805   0.00284  -0.1005   0.6358   0.7734
   2.750   0.7750   0.00811   0.00289  -0.1001   0.6249   0.7803
   3.000   0.8011   0.00817   0.00295  -0.0997   0.6124   0.7882
   3.250   0.8267   0.00823   0.00302  -0.0993   0.5989   0.7957
   3.500   0.8522   0.00832   0.00309  -0.0988   0.5841   0.8045
   3.750   0.8763   0.00842   0.00319  -0.0981   0.5665   0.8131
   4.000   0.9004   0.00855   0.00329  -0.0973   0.5454   0.8229
   4.250   0.9229   0.00874   0.00342  -0.0963   0.5212   0.8342
   4.500   0.9439   0.00896   0.00357  -0.0950   0.4923   0.8469
   4.750   0.9636   0.00922   0.00377  -0.0935   0.4613   0.8633
   5.000   0.9811   0.00949   0.00400  -0.0915   0.4284   0.8912
   5.250   1.0090   0.00983   0.00427  -0.0919   0.3916   1.0000
   5.500   1.0293   0.01031   0.00459  -0.0908   0.3599   1.0000
   5.750   1.0497   0.01077   0.00490  -0.0897   0.3327   1.0000
   6.000   1.0697   0.01123   0.00523  -0.0885   0.3118   1.0000
   6.250   1.0903   0.01165   0.00556  -0.0874   0.2971   1.0000
   6.500   1.1111   0.01203   0.00590  -0.0864   0.2854   1.0000
   6.750   1.1321   0.01238   0.00622  -0.0853   0.2754   1.0000
   7.000   1.1517   0.01278   0.00658  -0.0841   0.2662   1.0000
   7.250   1.1724   0.01309   0.00690  -0.0829   0.2588   1.0000
   7.500   1.1897   0.01350   0.00728  -0.0812   0.2523   1.0000
   7.750   1.2101   0.01377   0.00759  -0.0800   0.2458   1.0000
   8.000   1.2269   0.01420   0.00799  -0.0783   0.2392   1.0000
   8.250   1.2468   0.01449   0.00834  -0.0771   0.2333   1.0000
   8.500   1.2647   0.01488   0.00874  -0.0756   0.2266   1.0000
   8.750   1.2830   0.01525   0.00913  -0.0742   0.2192   1.0000
   9.000   1.2996   0.01569   0.00955  -0.0726   0.2097   1.0000
   9.250   1.3186   0.01604   0.00993  -0.0714   0.2005   1.0000
   9.500   1.3351   0.01651   0.01039  -0.0699   0.1901   1.0000
   9.750   1.3505   0.01705   0.01090  -0.0682   0.1791   1.0000
  10.250   1.3801   0.01826   0.01205  -0.0650   0.1537   1.0000
  10.500   1.3933   0.01898   0.01275  -0.0633   0.1413   1.0000
  10.750   1.4050   0.01981   0.01353  -0.0614   0.1285   1.0000
  11.000   1.4160   0.02072   0.01440  -0.0596   0.1163   1.0000
  11.250   1.4257   0.02173   0.01538  -0.0577   0.1038   1.0000
  11.500   1.4356   0.02277   0.01639  -0.0559   0.0930   1.0000
  11.750   1.4449   0.02388   0.01748  -0.0542   0.0832   1.0000
  12.000   1.4531   0.02509   0.01867  -0.0524   0.0738   1.0000
  12.250   1.4609   0.02638   0.01994  -0.0507   0.0649   1.0000
  12.500   1.4682   0.02775   0.02129  -0.0491   0.0558   1.0000
  12.750   1.4723   0.02940   0.02290  -0.0474   0.0449   1.0000
  13.000   1.4724   0.03144   0.02486  -0.0455   0.0317   1.0000
  13.250   1.4685   0.03389   0.02726  -0.0436   0.0207   1.0000
  13.500   1.4633   0.03660   0.02996  -0.0418   0.0137   1.0000
  13.750   1.4628   0.03899   0.03242  -0.0405   0.0113   1.0000
  14.000   1.4642   0.04128   0.03480  -0.0394   0.0104   1.0000
  14.250   1.4608   0.04416   0.03778  -0.0385   0.0094   1.0000
  14.500   1.4626   0.04661   0.04034  -0.0378   0.0091   1.0000
  14.750   1.4624   0.04936   0.04321  -0.0374   0.0086   1.0000
  15.000   1.4617   0.05228   0.04623  -0.0371   0.0083   1.0000
  15.250   1.4594   0.05552   0.04959  -0.0370   0.0080   1.0000
  15.500   1.4551   0.05911   0.05329  -0.0372   0.0077   1.0000
  15.750   1.4481   0.06322   0.05753  -0.0377   0.0075   1.0000
  16.000   1.4387   0.06785   0.06228  -0.0385   0.0073   1.0000
  16.250   1.4254   0.07327   0.06784  -0.0399   0.0071   1.0000
  16.500   1.4151   0.07847   0.07319  -0.0414   0.0070   1.0000
  16.750   1.4068   0.08356   0.07841  -0.0431   0.0069   1.0000
  17.000   1.3975   0.08896   0.08395  -0.0450   0.0068   1.0000
  17.250   1.3854   0.09499   0.09012  -0.0474   0.0068   1.0000
  17.500   1.3741   0.10103   0.09629  -0.0500   0.0067   1.0000
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