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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 50,000
Max Cl/Cd: 39.34 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq359-il-50000.txt
Download as CSV file: xf-hq359-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3649   0.10372   0.09740  -0.0297   1.0000   0.1911
  -7.750  -0.3538   0.09972   0.09344  -0.0278   1.0000   0.2009
  -7.500  -0.3780   0.09978   0.09370  -0.0265   1.0000   0.2053
  -7.250  -0.3682   0.09608   0.09005  -0.0243   1.0000   0.2167
  -7.000  -0.3742   0.09382   0.08791  -0.0219   1.0000   0.2249
  -6.750  -0.3943   0.09327   0.08751  -0.0195   1.0000   0.2324
  -6.500  -0.3938   0.09057   0.08489  -0.0168   1.0000   0.2444
  -6.250  -0.3984   0.08832   0.08274  -0.0144   1.0000   0.2569
  -6.000  -0.4038   0.08622   0.08074  -0.0120   1.0000   0.2700
  -5.750  -0.4102   0.08425   0.07886  -0.0098   1.0000   0.2855
  -5.500  -0.4238   0.08279   0.07751  -0.0091   1.0000   0.3030
  -5.250  -0.4169   0.07994   0.07472  -0.0039   1.0000   0.3273
  -5.000  -0.4178   0.07781   0.07263   0.0000   1.0000   0.3544
  -3.250  -0.2346   0.04143   0.03377  -0.0563   1.0000   0.1479
  -3.000  -0.1992   0.03802   0.02973  -0.0583   1.0000   0.1323
  -2.750  -0.1639   0.03545   0.02635  -0.0596   1.0000   0.1212
  -2.500  -0.1345   0.03299   0.02352  -0.0600   1.0000   0.1165
  -2.250  -0.1050   0.03102   0.02109  -0.0600   1.0000   0.1146
  -2.000  -0.0778   0.02951   0.01922  -0.0596   1.0000   0.1169
  -1.750  -0.0529   0.02819   0.01768  -0.0590   1.0000   0.1309
  -1.500  -0.0281   0.02694   0.01630  -0.0579   1.0000   0.1478
  -1.250  -0.0006   0.02564   0.01507  -0.0576   1.0000   0.1888
  -1.000   0.0312   0.02239   0.01446  -0.0572   1.0000   0.6850
  -0.750   0.0319   0.02149   0.01371  -0.0503   1.0000   1.0000
  -0.500   0.0560   0.02196   0.01357  -0.0505   1.0000   1.0000
  -0.250   0.0794   0.02246   0.01363  -0.0508   1.0000   1.0000
   0.000   0.1021   0.02300   0.01378  -0.0510   1.0000   1.0000
   0.250   0.1241   0.02359   0.01406  -0.0513   1.0000   1.0000
   0.500   0.1457   0.02421   0.01444  -0.0514   1.0000   1.0000
   0.750   0.1667   0.02489   0.01490  -0.0516   1.0000   1.0000
   1.000   0.1872   0.02561   0.01543  -0.0518   1.0000   1.0000
   1.250   0.2072   0.02638   0.01601  -0.0519   1.0000   1.0000
   1.500   0.2268   0.02720   0.01670  -0.0521   1.0000   1.0000
   1.750   0.2458   0.02809   0.01748  -0.0522   1.0000   1.0000
   2.000   0.2830   0.02945   0.01874  -0.0559   0.9902   1.0000
   2.250   0.3347   0.03110   0.02027  -0.0620   0.9719   1.0000
   2.500   0.3873   0.03247   0.02160  -0.0678   0.9485   1.0000
   2.750   0.4411   0.03359   0.02271  -0.0733   0.9240   1.0000
   3.000   0.4955   0.03449   0.02364  -0.0784   0.9016   1.0000
   3.250   0.5332   0.03517   0.02437  -0.0806   0.8793   1.0000
   3.500   0.5832   0.03571   0.02501  -0.0844   0.8590   1.0000
   3.750   0.6214   0.03613   0.02558  -0.0861   0.8363   1.0000
   4.000   0.6635   0.03633   0.02593  -0.0880   0.8140   1.0000
   4.250   0.7168   0.03599   0.02579  -0.0909   0.7926   1.0000
   4.500   0.7573   0.03568   0.02575  -0.0917   0.7679   1.0000
   4.750   0.8052   0.03479   0.02511  -0.0928   0.7433   1.0000
   5.000   0.8593   0.03321   0.02382  -0.0938   0.7191   1.0000
   5.250   0.9105   0.03139   0.02235  -0.0939   0.6923   1.0000
   5.500   0.9565   0.02975   0.02095  -0.0933   0.6612   1.0000
   5.750   1.0054   0.02800   0.01934  -0.0928   0.6278   1.0000
   6.000   1.0360   0.02765   0.01907  -0.0912   0.5901   1.0000
   6.250   1.0664   0.02759   0.01909  -0.0897   0.5544   1.0000
   6.500   1.0946   0.02789   0.01937  -0.0884   0.5205   1.0000
   6.750   1.1211   0.02850   0.01995  -0.0870   0.4886   1.0000
   7.000   1.1436   0.02943   0.02093  -0.0854   0.4574   1.0000
   7.250   1.1663   0.03043   0.02196  -0.0839   0.4264   1.0000
   7.500   1.1895   0.03148   0.02296  -0.0824   0.3947   1.0000
   7.750   1.2078   0.03280   0.02445  -0.0804   0.3626   1.0000
   8.000   1.2255   0.03411   0.02576  -0.0782   0.3277   1.0000
   8.250   1.2385   0.03545   0.02707  -0.0754   0.2887   1.0000
   8.500   1.2472   0.03666   0.02793  -0.0721   0.2424   1.0000
   8.750   1.2437   0.03813   0.02940  -0.0674   0.1971   1.0000
   9.000   1.2376   0.03990   0.03095  -0.0625   0.1535   1.0000
   9.250   1.2304   0.04174   0.03237  -0.0583   0.1209   1.0000
   9.500   1.2354   0.04472   0.03510  -0.0556   0.0959   1.0000
   9.750   1.2525   0.04849   0.03909  -0.0540   0.0814   1.0000
  10.000   1.2707   0.05230   0.04286  -0.0532   0.0714   1.0000
  10.250   1.2748   0.05594   0.04718  -0.0505   0.0680   1.0000
  10.500   1.2786   0.06012   0.05186  -0.0482   0.0661   1.0000
  10.750   1.2749   0.06422   0.05638  -0.0456   0.0651   1.0000
  11.000   1.2646   0.06828   0.06081  -0.0428   0.0648   1.0000
  11.250   1.2488   0.07247   0.06534  -0.0404   0.0649   1.0000
  11.500   1.2289   0.07697   0.07016  -0.0387   0.0654   1.0000
  11.750   1.2061   0.08195   0.07542  -0.0381   0.0660   1.0000
  12.000   1.1816   0.08753   0.08125  -0.0388   0.0667   1.0000
  12.250   1.1569   0.09379   0.08770  -0.0407   0.0677   1.0000
  12.500   1.1320   0.10084   0.09491  -0.0439   0.0686   1.0000
  12.750   1.1095   0.10852   0.10268  -0.0480   0.0696   1.0000
  13.000   1.0913   0.11647   0.11069  -0.0524   0.0706   1.0000
  13.250   1.0779   0.12439   0.11863  -0.0565   0.0714   1.0000
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