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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 500,000
Max Cl/Cd: 97.34 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2010-il-500000.txt
Download as CSV file: xf-hq2010-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4548   0.09999   0.09769  -0.0281   1.0000   0.0198
 -10.000  -0.4527   0.09553   0.09325  -0.0309   1.0000   0.0201
  -7.000  -0.4887   0.02282   0.01830  -0.0618   0.9817   0.0129
  -6.750  -0.4613   0.01942   0.01442  -0.0626   0.9763   0.0128
  -6.500  -0.4288   0.01726   0.01194  -0.0640   0.9730   0.0131
  -6.250  -0.3949   0.01580   0.01025  -0.0655   0.9701   0.0136
  -6.000  -0.3667   0.01410   0.00834  -0.0659   0.9638   0.0145
  -5.750  -0.3369   0.01290   0.00703  -0.0666   0.9578   0.0158
  -5.500  -0.3073   0.01243   0.00653  -0.0670   0.9508   0.0177
  -5.250  -0.2789   0.01196   0.00599  -0.0671   0.9432   0.0197
  -5.000  -0.2542   0.01100   0.00494  -0.0665   0.9347   0.0230
  -4.750  -0.2268   0.01066   0.00455  -0.0663   0.9279   0.0283
  -4.500  -0.2012   0.01023   0.00408  -0.0659   0.9196   0.0392
  -4.250  -0.1747   0.00986   0.00370  -0.0656   0.9129   0.0502
  -4.000  -0.1489   0.00955   0.00337  -0.0652   0.9048   0.0599
  -3.750  -0.1222   0.00927   0.00309  -0.0649   0.8986   0.0741
  -3.500  -0.0964   0.00889   0.00283  -0.0646   0.8908   0.1068
  -3.250  -0.0713   0.00830   0.00255  -0.0644   0.8845   0.1975
  -3.000  -0.0468   0.00766   0.00232  -0.0641   0.8766   0.3162
  -2.750  -0.0229   0.00699   0.00218  -0.0637   0.8702   0.4822
  -2.500   0.0030   0.00677   0.00215  -0.0632   0.8624   0.5512
  -2.250   0.0298   0.00670   0.00210  -0.0629   0.8560   0.5911
  -2.000   0.0568   0.00664   0.00207  -0.0625   0.8480   0.6196
  -1.750   0.0839   0.00662   0.00205  -0.0622   0.8414   0.6470
  -1.500   0.1107   0.00659   0.00202  -0.0618   0.8323   0.6694
  -1.250   0.1376   0.00658   0.00199  -0.0613   0.8229   0.6879
  -1.000   0.1642   0.00656   0.00197  -0.0608   0.8142   0.7092
  -0.750   0.1911   0.00654   0.00196  -0.0604   0.8042   0.7259
  -0.500   0.2182   0.00653   0.00193  -0.0601   0.7950   0.7393
  -0.250   0.2454   0.00652   0.00190  -0.0598   0.7864   0.7516
   0.000   0.2724   0.00650   0.00190  -0.0594   0.7762   0.7650
   0.250   0.2993   0.00650   0.00189  -0.0590   0.7661   0.7779
   0.500   0.3265   0.00650   0.00187  -0.0588   0.7567   0.7887
   0.750   0.3539   0.00650   0.00186  -0.0586   0.7464   0.7988
   1.000   0.3809   0.00649   0.00186  -0.0583   0.7360   0.8084
   1.250   0.4080   0.00649   0.00187  -0.0580   0.7260   0.8188
   1.500   0.4349   0.00650   0.00188  -0.0577   0.7155   0.8302
   1.750   0.4617   0.00650   0.00190  -0.0573   0.7032   0.8425
   2.000   0.4880   0.00650   0.00192  -0.0569   0.6908   0.8561
   2.250   0.5139   0.00648   0.00196  -0.0563   0.6775   0.8716
   2.500   0.5391   0.00647   0.00199  -0.0556   0.6628   0.8921
   2.750   0.5649   0.00645   0.00203  -0.0549   0.6469   0.9221
   3.000   0.6028   0.00648   0.00208  -0.0570   0.6263   0.9693
   3.250   0.6364   0.00661   0.00214  -0.0584   0.6015   1.0000
   3.500   0.6619   0.00680   0.00222  -0.0580   0.5702   1.0000
   3.750   0.6865   0.00708   0.00233  -0.0574   0.5306   1.0000
   4.000   0.7094   0.00750   0.00251  -0.0566   0.4692   1.0000
   4.250   0.7309   0.00808   0.00275  -0.0557   0.3999   1.0000
   4.500   0.7544   0.00855   0.00301  -0.0551   0.3527   1.0000
   4.750   0.7782   0.00898   0.00327  -0.0545   0.3131   1.0000
   5.000   0.8025   0.00938   0.00356  -0.0541   0.2851   1.0000
   5.250   0.8269   0.00977   0.00385  -0.0536   0.2622   1.0000
   5.500   0.8515   0.01012   0.00413  -0.0532   0.2415   1.0000
   5.750   0.8762   0.01047   0.00442  -0.0527   0.2213   1.0000
   6.000   0.9008   0.01081   0.00470  -0.0523   0.1988   1.0000
   6.250   0.9247   0.01123   0.00503  -0.0518   0.1703   1.0000
   6.500   0.9463   0.01187   0.00544  -0.0510   0.1276   1.0000
   6.750   0.9665   0.01267   0.00598  -0.0501   0.0868   1.0000
   7.000   0.9877   0.01336   0.00653  -0.0492   0.0648   1.0000
   7.250   1.0102   0.01390   0.00703  -0.0485   0.0541   1.0000
   7.500   1.0332   0.01436   0.00752  -0.0478   0.0477   1.0000
   7.750   1.0549   0.01496   0.00811  -0.0470   0.0407   1.0000
   8.000   1.0784   0.01534   0.00855  -0.0464   0.0376   1.0000
   8.250   1.1011   0.01578   0.00900  -0.0457   0.0335   1.0000
   8.500   1.1228   0.01631   0.00955  -0.0449   0.0289   1.0000
   8.750   1.1449   0.01678   0.01000  -0.0442   0.0217   1.0000
   9.000   1.1635   0.01760   0.01079  -0.0429   0.0131   1.0000
   9.250   1.1806   0.01855   0.01175  -0.0414   0.0098   1.0000
   9.500   1.1989   0.01930   0.01262  -0.0401   0.0087   1.0000
   9.750   1.2167   0.02006   0.01346  -0.0387   0.0080   1.0000
  10.000   1.2324   0.02095   0.01444  -0.0371   0.0074   1.0000
  10.250   1.2458   0.02197   0.01555  -0.0352   0.0069   1.0000
  10.500   1.2551   0.02305   0.01674  -0.0326   0.0067   1.0000
  10.750   1.2566   0.02458   0.01841  -0.0290   0.0063   1.0000
  11.000   1.2592   0.02608   0.02005  -0.0259   0.0062   1.0000
  11.250   1.2665   0.02731   0.02141  -0.0236   0.0061   1.0000
  11.500   1.2705   0.02884   0.02308  -0.0213   0.0060   1.0000
  11.750   1.2742   0.03048   0.02486  -0.0191   0.0059   1.0000
  12.000   1.2758   0.03239   0.02695  -0.0170   0.0057   1.0000
  12.250   1.2770   0.03443   0.02914  -0.0153   0.0056   1.0000
  12.500   1.2767   0.03670   0.03157  -0.0137   0.0055   1.0000
  12.750   1.2747   0.03928   0.03432  -0.0124   0.0055   1.0000
  13.000   1.2708   0.04219   0.03741  -0.0113   0.0054   1.0000
  13.250   1.2662   0.04531   0.04070  -0.0108   0.0053   1.0000
  13.500   1.2594   0.04888   0.04446  -0.0105   0.0054   1.0000
  13.750   1.2517   0.05276   0.04852  -0.0108   0.0053   1.0000
  14.000   1.2410   0.05728   0.05323  -0.0117   0.0053   1.0000
  14.250   1.2282   0.06241   0.05857  -0.0132   0.0053   1.0000
  14.500   1.2153   0.06790   0.06424  -0.0154   0.0053   1.0000
  14.750   1.1995   0.07435   0.07089  -0.0184   0.0054   1.0000
  15.000   1.1823   0.08154   0.07828  -0.0222   0.0054   1.0000
  15.250   1.1652   0.08931   0.08622  -0.0267   0.0054   1.0000
  15.500   1.1472   0.09770   0.09478  -0.0316   0.0055   1.0000
  15.750   1.1274   0.10697   0.10423  -0.0372   0.0055   1.0000
  16.000   1.1077   0.11664   0.11404  -0.0431   0.0055   1.0000
  16.250   1.0860   0.12709   0.12464  -0.0494   0.0056   1.0000
  16.500   1.0642   0.13801   0.13569  -0.0559   0.0057   1.0000
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