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HQ 1.5/11 AIRFOIL (hq1511-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/11 AIRFOIL (hq1511-il)
Reynolds number: 50,000
Max Cl/Cd: 34.42 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1511-il-50000-n5.txt
Download as CSV file: xf-hq1511-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/11 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5228   0.09775   0.09055  -0.0302   1.0000   0.0443
 -10.250  -0.5284   0.09178   0.08466  -0.0335   1.0000   0.0441
 -10.000  -0.5365   0.08506   0.07798  -0.0377   1.0000   0.0437
  -9.750  -0.5502   0.07830   0.07127  -0.0425   1.0000   0.0433
  -9.500  -0.5662   0.07261   0.06558  -0.0463   1.0000   0.0428
  -9.250  -0.5860   0.06780   0.06075  -0.0484   1.0000   0.0424
  -9.000  -0.6037   0.06354   0.05638  -0.0489   1.0000   0.0423
  -8.750  -0.6155   0.05944   0.05211  -0.0489   1.0000   0.0422
  -8.500  -0.6239   0.05537   0.04777  -0.0483   1.0000   0.0426
  -8.250  -0.6276   0.05157   0.04364  -0.0472   1.0000   0.0432
  -8.000  -0.6289   0.04777   0.03938  -0.0458   1.0000   0.0446
  -7.750  -0.6258   0.04436   0.03546  -0.0440   1.0000   0.0462
  -7.500  -0.6152   0.04238   0.03348  -0.0427   1.0000   0.0490
  -7.250  -0.6045   0.04021   0.03108  -0.0410   1.0000   0.0526
  -7.000  -0.5939   0.03770   0.02790  -0.0390   1.0000   0.0575
  -6.750  -0.5810   0.03612   0.02642  -0.0377   1.0000   0.0634
  -6.500  -0.5666   0.03416   0.02393  -0.0358   1.0000   0.0698
  -6.250  -0.5515   0.03245   0.02226  -0.0342   1.0000   0.0761
  -6.000  -0.5341   0.03082   0.02027  -0.0324   1.0000   0.0825
  -5.750  -0.5169   0.02933   0.01877  -0.0308   1.0000   0.0885
  -5.500  -0.4993   0.02822   0.01744  -0.0290   1.0000   0.0968
  -5.250  -0.4824   0.02704   0.01626  -0.0273   1.0000   0.1032
  -5.000  -0.4656   0.02613   0.01521  -0.0255   1.0000   0.1132
  -4.750  -0.4496   0.02522   0.01431  -0.0238   1.0000   0.1238
  -4.500  -0.4334   0.02435   0.01346  -0.0223   1.0000   0.1365
  -4.250  -0.4167   0.02351   0.01271  -0.0210   1.0000   0.1566
  -4.000  -0.3986   0.02260   0.01192  -0.0201   1.0000   0.1893
  -3.750  -0.3822   0.02141   0.01117  -0.0192   1.0000   0.2607
  -3.500  -0.3586   0.02018   0.01099  -0.0193   0.9947   0.4398
  -3.250  -0.3332   0.02012   0.01138  -0.0181   0.9872   0.5737
  -3.000  -0.3060   0.02039   0.01163  -0.0173   0.9797   0.6515
  -2.750  -0.2815   0.02076   0.01200  -0.0156   0.9720   0.7179
  -2.500  -0.2597   0.02105   0.01227  -0.0131   0.9643   0.7653
  -2.250  -0.2305   0.02121   0.01229  -0.0128   0.9575   0.7956
  -2.000  -0.2027   0.02125   0.01214  -0.0126   0.9500   0.8174
  -1.750  -0.1713   0.02135   0.01213  -0.0127   0.9435   0.8458
  -1.500  -0.1401   0.02144   0.01213  -0.0127   0.9366   0.8755
  -1.250  -0.0986   0.02155   0.01208  -0.0151   0.9306   0.9002
  -1.000  -0.0524   0.02161   0.01198  -0.0189   0.9243   0.9163
  -0.750  -0.0059   0.02164   0.01186  -0.0230   0.9166   0.9303
  -0.500   0.0458   0.02167   0.01176  -0.0280   0.9101   0.9431
  -0.250   0.0948   0.02169   0.01168  -0.0327   0.9023   0.9562
   0.000   0.1524   0.02169   0.01158  -0.0389   0.8975   0.9665
   0.250   0.1981   0.02171   0.01157  -0.0432   0.8889   0.9807
   0.500   0.2513   0.02166   0.01149  -0.0486   0.8832   0.9936
   0.750   0.2754   0.02173   0.01155  -0.0490   0.8721   1.0000
   1.000   0.2942   0.02182   0.01163  -0.0482   0.8609   1.0000
   1.250   0.3218   0.02189   0.01169  -0.0487   0.8520   1.0000
   1.500   0.3423   0.02202   0.01181  -0.0479   0.8401   1.0000
   1.750   0.3665   0.02207   0.01184  -0.0473   0.8262   1.0000
   2.000   0.3960   0.02192   0.01171  -0.0471   0.8104   1.0000
   2.250   0.4265   0.02167   0.01146  -0.0467   0.7934   1.0000
   2.500   0.4488   0.02161   0.01140  -0.0453   0.7743   1.0000
   2.750   0.4742   0.02158   0.01139  -0.0444   0.7585   1.0000
   3.000   0.4998   0.02162   0.01150  -0.0437   0.7441   1.0000
   3.250   0.5253   0.02166   0.01160  -0.0429   0.7291   1.0000
   3.500   0.5505   0.02171   0.01172  -0.0420   0.7133   1.0000
   3.750   0.5757   0.02176   0.01188  -0.0412   0.6966   1.0000
   4.000   0.6013   0.02178   0.01199  -0.0402   0.6789   1.0000
   4.250   0.6278   0.02174   0.01203  -0.0393   0.6602   1.0000
   4.500   0.6501   0.02186   0.01227  -0.0379   0.6367   1.0000
   4.750   0.6749   0.02188   0.01240  -0.0368   0.6127   1.0000
   5.000   0.6995   0.02191   0.01250  -0.0355   0.5856   1.0000
   5.250   0.7223   0.02201   0.01266  -0.0340   0.5523   1.0000
   5.500   0.7456   0.02209   0.01269  -0.0324   0.5142   1.0000
   5.750   0.7672   0.02236   0.01282  -0.0307   0.4728   1.0000
   6.000   0.7876   0.02288   0.01317  -0.0290   0.4333   1.0000
   6.250   0.8070   0.02354   0.01373  -0.0276   0.3970   1.0000
   6.500   0.8256   0.02428   0.01443  -0.0261   0.3630   1.0000
   6.750   0.8434   0.02508   0.01516  -0.0247   0.3311   1.0000
   7.000   0.8602   0.02600   0.01597  -0.0232   0.3010   1.0000
   7.250   0.8762   0.02703   0.01694  -0.0217   0.2709   1.0000
   7.500   0.8909   0.02814   0.01801  -0.0201   0.2401   1.0000
   7.750   0.9044   0.02934   0.01920  -0.0185   0.2096   1.0000
   8.000   0.9172   0.03057   0.02043  -0.0169   0.1792   1.0000
   8.250   0.9288   0.03183   0.02163  -0.0152   0.1522   1.0000
   8.500   0.9396   0.03331   0.02297  -0.0136   0.1316   1.0000
   8.750   0.9517   0.03498   0.02458  -0.0121   0.1144   1.0000
   9.000   0.9641   0.03673   0.02633  -0.0106   0.1005   1.0000
   9.250   0.9785   0.03857   0.02821  -0.0093   0.0906   1.0000
   9.500   0.9913   0.04041   0.03009  -0.0080   0.0821   1.0000
   9.750   1.0071   0.04244   0.03238  -0.0069   0.0746   1.0000
  10.000   1.0227   0.04451   0.03446  -0.0059   0.0696   1.0000
  10.250   1.0365   0.04694   0.03721  -0.0048   0.0649   1.0000
  10.500   1.0451   0.04922   0.03973  -0.0034   0.0609   1.0000
  10.750   1.0552   0.05154   0.04213  -0.0023   0.0580   1.0000
  11.000   1.0645   0.05461   0.04539  -0.0013   0.0561   1.0000
  11.250   1.0615   0.05797   0.04922   0.0002   0.0547   1.0000
  11.500   1.0541   0.06153   0.05315   0.0014   0.0535   1.0000
  11.750   1.0432   0.06542   0.05734   0.0020   0.0524   1.0000
  12.000   1.0294   0.06971   0.06191   0.0019   0.0517   1.0000
  12.250   1.0121   0.07469   0.06714   0.0008   0.0512   1.0000
  12.500   0.9904   0.08067   0.07336  -0.0014   0.0513   1.0000
  12.750   0.9630   0.08821   0.08108  -0.0053   0.0518   1.0000
  13.000   0.9317   0.09761   0.09065  -0.0110   0.0529   1.0000
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