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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 50,000
Max Cl/Cd: 42.16 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq308-il-50000-n5.txt
Download as CSV file: xf-hq308-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3810   0.09815   0.09158  -0.0311   1.0000   0.0925
  -7.750  -0.3870   0.09602   0.08958  -0.0318   1.0000   0.0954
  -7.500  -0.4077   0.09504   0.08881  -0.0362   1.0000   0.0977
  -7.250  -0.4041   0.09106   0.08494  -0.0352   1.0000   0.0989
  -7.000  -0.3983   0.08763   0.08148  -0.0332   1.0000   0.1005
  -6.750  -0.3974   0.08454   0.07846  -0.0330   1.0000   0.1022
  -6.500  -0.3978   0.08149   0.07549  -0.0338   1.0000   0.1033
  -6.250  -0.3910   0.07592   0.06986  -0.0379   1.0000   0.0644
  -6.000  -0.3823   0.06992   0.06368  -0.0452   1.0000   0.0432
  -5.750  -0.3788   0.06663   0.06039  -0.0433   1.0000   0.0414
  -5.500  -0.3724   0.06314   0.05685  -0.0439   1.0000   0.0400
  -5.250  -0.3628   0.05936   0.05297  -0.0451   1.0000   0.0386
  -5.000  -0.3498   0.05550   0.04894  -0.0468   1.0000   0.0381
  -4.750  -0.3336   0.05169   0.04489  -0.0485   1.0000   0.0382
  -4.500  -0.3144   0.04808   0.04097  -0.0501   1.0000   0.0388
  -4.250  -0.2926   0.04459   0.03710  -0.0516   1.0000   0.0397
  -4.000  -0.2685   0.04121   0.03327  -0.0529   1.0000   0.0402
  -3.750  -0.2431   0.03806   0.02967  -0.0538   1.0000   0.0399
  -3.500  -0.2164   0.03515   0.02626  -0.0545   1.0000   0.0395
  -3.250  -0.1890   0.03257   0.02318  -0.0549   1.0000   0.0397
  -3.000  -0.1616   0.03036   0.02049  -0.0549   1.0000   0.0403
  -2.750  -0.1340   0.02841   0.01805  -0.0545   1.0000   0.0417
  -2.500  -0.1081   0.02691   0.01615  -0.0538   1.0000   0.0433
  -2.250  -0.0785   0.02551   0.01460  -0.0543   0.9971   0.0497
  -2.000  -0.0446   0.02443   0.01328  -0.0553   0.9923   0.0607
  -1.750  -0.0083   0.02340   0.01204  -0.0570   0.9876   0.0833
  -1.500   0.0302   0.02187   0.01080  -0.0598   0.9836   0.1561
  -1.250   0.0462   0.01934   0.01086  -0.0564   0.9794   0.7806
  -1.000   0.0811   0.01896   0.01030  -0.0571   0.9707   1.0000
  -0.750   0.1181   0.01928   0.01006  -0.0595   0.9635   1.0000
  -0.500   0.1537   0.01960   0.00998  -0.0616   0.9559   1.0000
  -0.250   0.1914   0.01994   0.00999  -0.0641   0.9487   1.0000
   0.000   0.2246   0.02025   0.01004  -0.0657   0.9399   1.0000
   0.250   0.2621   0.02058   0.01010  -0.0680   0.9323   1.0000
   0.500   0.2964   0.02088   0.01022  -0.0698   0.9231   1.0000
   0.750   0.3298   0.02117   0.01038  -0.0712   0.9134   1.0000
   1.000   0.3667   0.02144   0.01053  -0.0733   0.9046   1.0000
   1.250   0.4028   0.02168   0.01070  -0.0751   0.8949   1.0000
   1.500   0.4352   0.02193   0.01090  -0.0762   0.8839   1.0000
   1.750   0.4690   0.02215   0.01111  -0.0774   0.8731   1.0000
   2.000   0.5045   0.02231   0.01132  -0.0789   0.8625   1.0000
   2.250   0.5407   0.02239   0.01142  -0.0802   0.8514   1.0000
   2.500   0.5754   0.02240   0.01149  -0.0811   0.8385   1.0000
   2.750   0.6069   0.02241   0.01158  -0.0813   0.8240   1.0000
   3.000   0.6374   0.02242   0.01175  -0.0813   0.8087   1.0000
   3.250   0.6677   0.02239   0.01184  -0.0812   0.7928   1.0000
   3.500   0.6986   0.02229   0.01187  -0.0810   0.7763   1.0000
   3.750   0.7311   0.02206   0.01178  -0.0808   0.7590   1.0000
   4.000   0.7576   0.02197   0.01185  -0.0798   0.7368   1.0000
   4.250   0.7862   0.02178   0.01191  -0.0788   0.7134   1.0000
   4.500   0.8138   0.02163   0.01192  -0.0777   0.6874   1.0000
   4.750   0.8402   0.02157   0.01202  -0.0765   0.6578   1.0000
   5.000   0.8670   0.02153   0.01211  -0.0752   0.6243   1.0000
   5.250   0.8920   0.02161   0.01228  -0.0738   0.5845   1.0000
   5.500   0.9160   0.02183   0.01263  -0.0721   0.5383   1.0000
   5.750   0.9384   0.02226   0.01298  -0.0704   0.4878   1.0000
   6.000   0.9585   0.02296   0.01356  -0.0686   0.4363   1.0000
   6.250   0.9769   0.02387   0.01435  -0.0668   0.3874   1.0000
   6.500   0.9940   0.02494   0.01531  -0.0650   0.3407   1.0000
   6.750   1.0096   0.02612   0.01636  -0.0632   0.2965   1.0000
   7.000   1.0242   0.02737   0.01753  -0.0615   0.2531   1.0000
   7.250   1.0386   0.02871   0.01881  -0.0598   0.2128   1.0000
   7.500   1.0519   0.03021   0.02036  -0.0581   0.1743   1.0000
   7.750   1.0657   0.03193   0.02210  -0.0565   0.1383   1.0000
   8.000   1.0774   0.03390   0.02396  -0.0547   0.1060   1.0000
   8.250   1.0886   0.03624   0.02626  -0.0528   0.0790   1.0000
   8.500   1.0965   0.03844   0.02838  -0.0511   0.0532   1.0000
   8.750   1.1048   0.04081   0.03080  -0.0493   0.0383   1.0000
   9.000   1.1118   0.04351   0.03364  -0.0472   0.0322   1.0000
   9.250   1.1240   0.04638   0.03688  -0.0452   0.0287   1.0000
   9.500   1.1338   0.04932   0.04010  -0.0434   0.0263   1.0000
   9.750   1.1404   0.05246   0.04348  -0.0416   0.0248   1.0000
  10.000   1.1439   0.05615   0.04740  -0.0400   0.0237   1.0000
  10.250   1.1444   0.06009   0.05165  -0.0382   0.0231   1.0000
  10.500   1.1401   0.06397   0.05593  -0.0366   0.0228   1.0000
  10.750   1.1316   0.06808   0.06039  -0.0355   0.0227   1.0000
  11.000   1.1197   0.07253   0.06517  -0.0350   0.0226   1.0000
  11.250   1.1057   0.07739   0.07031  -0.0354   0.0225   1.0000
  11.500   1.0898   0.08279   0.07596  -0.0369   0.0226   1.0000
  11.750   1.0732   0.08876   0.08214  -0.0393   0.0227   1.0000
  12.000   1.0566   0.09529   0.08884  -0.0427   0.0228   1.0000
  12.250   1.0404   0.10245   0.09614  -0.0469   0.0230   1.0000
  12.500   1.0250   0.11022   0.10403  -0.0518   0.0232   1.0000
  12.750   1.0111   0.11841   0.11231  -0.0570   0.0233   1.0000
  13.000   0.9929   0.12995   0.12407  -0.0648   0.0243   1.0000
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