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HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 0/10 AIRFOIL (hq010-il)
Reynolds number: 500,000
Max Cl/Cd: 54.63 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq010-il-500000.txt
Download as CSV file: xf-hq010-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 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
  ------ -------- --------- --------- -------- -------- --------
 -14.000  -0.7880   0.09474   0.09250   0.0016   1.0000   0.0058
 -13.750  -0.8095   0.08460   0.08225  -0.0035   1.0000   0.0056
 -13.500  -0.8228   0.07638   0.07393  -0.0078   1.0000   0.0055
 -13.250  -0.9101   0.07304   0.07039  -0.0120   1.0000   0.0054
 -13.000  -0.9370   0.06324   0.06040  -0.0190   1.0000   0.0054
 -12.750  -0.9585   0.05593   0.05291  -0.0238   1.0000   0.0054
 -12.500  -0.9786   0.04994   0.04672  -0.0270   1.0000   0.0053
 -12.250  -0.9950   0.04520   0.04178  -0.0285   1.0000   0.0053
 -12.000  -1.0100   0.04115   0.03751  -0.0288   1.0000   0.0053
 -11.750  -1.0234   0.03772   0.03384  -0.0278   1.0000   0.0054
 -11.500  -1.0340   0.03491   0.03081  -0.0259   1.0000   0.0053
 -11.250  -1.0418   0.03253   0.02821  -0.0229   1.0000   0.0053
 -11.000  -1.0432   0.03050   0.02594  -0.0200   1.0000   0.0054
 -10.750  -1.0388   0.02838   0.02358  -0.0179   1.0000   0.0054
 -10.500  -1.0357   0.02573   0.02063  -0.0155   1.0000   0.0055
 -10.250  -1.0288   0.02340   0.01803  -0.0133   1.0000   0.0058
 -10.000  -1.0147   0.02193   0.01643  -0.0118   1.0000   0.0062
  -9.750  -0.9961   0.02097   0.01538  -0.0108   1.0000   0.0067
  -9.500  -0.9764   0.02010   0.01441  -0.0099   1.0000   0.0073
  -9.250  -0.9552   0.01935   0.01353  -0.0091   1.0000   0.0084
  -9.000  -0.9368   0.01821   0.01234  -0.0080   1.0000   0.0108
  -8.750  -0.9100   0.01827   0.01238  -0.0079   1.0000   0.0136
  -8.500  -0.8901   0.01731   0.01136  -0.0070   1.0000   0.0163
  -8.250  -0.8651   0.01714   0.01118  -0.0068   1.0000   0.0181
  -8.000  -0.8409   0.01678   0.01076  -0.0063   1.0000   0.0196
  -7.750  -0.8154   0.01666   0.01059  -0.0061   1.0000   0.0208
  -7.500  -0.7946   0.01569   0.00953  -0.0052   1.0000   0.0226
  -7.250  -0.7728   0.01496   0.00875  -0.0044   1.0000   0.0250
  -7.000  -0.7475   0.01479   0.00859  -0.0042   1.0000   0.0277
  -6.750  -0.7232   0.01443   0.00818  -0.0036   1.0000   0.0297
  -6.500  -0.6995   0.01398   0.00768  -0.0030   1.0000   0.0308
  -6.250  -0.6801   0.01292   0.00652  -0.0016   1.0000   0.0329
  -6.000  -0.6588   0.01224   0.00582  -0.0005   1.0000   0.0363
  -5.750  -0.6364   0.01181   0.00536   0.0004   1.0000   0.0400
  -5.500  -0.6153   0.01133   0.00483   0.0016   1.0000   0.0450
  -5.250  -0.5959   0.01091   0.00445   0.0030   1.0000   0.0541
  -5.000  -0.5607   0.01033   0.00398   0.0010   0.9933   0.0760
  -4.750  -0.5248   0.00973   0.00356  -0.0012   0.9850   0.1121
  -4.500  -0.4898   0.00901   0.00322  -0.0034   0.9759   0.1933
  -4.250  -0.4533   0.00857   0.00293  -0.0055   0.9669   0.2383
  -4.000  -0.4205   0.00809   0.00265  -0.0069   0.9540   0.2939
  -3.750  -0.3940   0.00752   0.00242  -0.0070   0.9366   0.3788
  -3.500  -0.3699   0.00712   0.00224  -0.0063   0.9187   0.4525
  -3.250  -0.3465   0.00680   0.00209  -0.0053   0.9024   0.5141
  -3.000  -0.3223   0.00661   0.00202  -0.0044   0.8879   0.5675
  -2.750  -0.2972   0.00652   0.00197  -0.0036   0.8740   0.6051
  -2.500  -0.2715   0.00648   0.00194  -0.0030   0.8610   0.6355
  -2.250  -0.2451   0.00646   0.00192  -0.0025   0.8500   0.6574
  -2.000  -0.2184   0.00647   0.00188  -0.0021   0.8403   0.6764
  -1.750  -0.1918   0.00645   0.00188  -0.0016   0.8306   0.6955
  -1.500  -0.1645   0.00644   0.00185  -0.0014   0.8211   0.7075
  -1.250  -0.1371   0.00646   0.00181  -0.0012   0.8123   0.7177
  -1.000  -0.1096   0.00644   0.00179  -0.0010   0.8039   0.7274
  -0.750  -0.0821   0.00643   0.00178  -0.0008   0.7957   0.7369
  -0.500  -0.0546   0.00644   0.00176  -0.0005   0.7874   0.7471
  -0.250  -0.0272   0.00643   0.00175  -0.0003   0.7774   0.7571
   0.000   0.0000   0.00642   0.00175   0.0000   0.7668   0.7667
   0.250   0.0272   0.00643   0.00175   0.0003   0.7571   0.7774
   0.500   0.0547   0.00644   0.00176   0.0005   0.7471   0.7874
   0.750   0.0821   0.00643   0.00178   0.0008   0.7369   0.7957
   1.000   0.1096   0.00644   0.00179   0.0009   0.7274   0.8038
   1.250   0.1371   0.00646   0.00181   0.0012   0.7177   0.8123
   1.500   0.1646   0.00644   0.00185   0.0014   0.7075   0.8211
   1.750   0.1918   0.00645   0.00188   0.0016   0.6954   0.8307
   2.000   0.2185   0.00647   0.00188   0.0021   0.6764   0.8403
   2.250   0.2452   0.00646   0.00192   0.0025   0.6574   0.8499
   2.500   0.2716   0.00648   0.00194   0.0030   0.6356   0.8610
   2.750   0.2972   0.00653   0.00197   0.0036   0.6051   0.8739
   3.000   0.3223   0.00661   0.00202   0.0044   0.5676   0.8879
   3.250   0.3465   0.00679   0.00209   0.0053   0.5143   0.9024
   3.500   0.3699   0.00712   0.00224   0.0062   0.4530   0.9187
   3.750   0.3941   0.00752   0.00242   0.0069   0.3792   0.9366
   4.000   0.4205   0.00809   0.00266   0.0069   0.2934   0.9539
   4.250   0.4533   0.00857   0.00293   0.0055   0.2384   0.9669
   4.500   0.4897   0.00901   0.00322   0.0034   0.1929   0.9760
   4.750   0.5248   0.00973   0.00356   0.0012   0.1121   0.9850
   5.000   0.5608   0.01033   0.00398  -0.0010   0.0761   0.9933
   5.250   0.5960   0.01091   0.00445  -0.0030   0.0540   1.0000
   5.500   0.6154   0.01132   0.00483  -0.0016   0.0452   1.0000
   5.750   0.6364   0.01181   0.00536  -0.0004   0.0399   1.0000
   6.000   0.6588   0.01224   0.00582   0.0005   0.0361   1.0000
   6.250   0.6801   0.01293   0.00653   0.0016   0.0328   1.0000
   6.500   0.6997   0.01396   0.00765   0.0029   0.0307   1.0000
   6.750   0.7232   0.01443   0.00818   0.0036   0.0297   1.0000
   7.000   0.7479   0.01471   0.00850   0.0041   0.0274   1.0000
   7.250   0.7729   0.01494   0.00873   0.0044   0.0248   1.0000
   7.500   0.7945   0.01571   0.00955   0.0052   0.0225   1.0000
   7.750   0.8157   0.01659   0.01051   0.0060   0.0208   1.0000
   8.000   0.8406   0.01683   0.01081   0.0064   0.0197   1.0000
   8.250   0.8653   0.01710   0.01113   0.0067   0.0180   1.0000
   8.500   0.8901   0.01730   0.01135   0.0070   0.0163   1.0000
   8.750   0.9101   0.01825   0.01235   0.0079   0.0136   1.0000
   9.000   0.9369   0.01819   0.01231   0.0080   0.0108   1.0000
   9.250   0.9560   0.01925   0.01341   0.0090   0.0082   1.0000
   9.500   0.9757   0.02020   0.01452   0.0100   0.0075   1.0000
   9.750   0.9956   0.02104   0.01546   0.0109   0.0067   1.0000
  10.000   1.0145   0.02195   0.01645   0.0119   0.0062   1.0000
  10.250   1.0292   0.02334   0.01797   0.0132   0.0058   1.0000
  10.500   1.0368   0.02559   0.02047   0.0154   0.0056   1.0000
  10.750   1.0389   0.02836   0.02356   0.0179   0.0054   1.0000
  11.000   1.0437   0.03044   0.02588   0.0200   0.0054   1.0000
  11.250   1.0420   0.03251   0.02818   0.0229   0.0054   1.0000
  11.500   1.0346   0.03487   0.03077   0.0258   0.0053   1.0000
  11.750   1.0243   0.03767   0.03380   0.0278   0.0053   1.0000
  12.000   1.0107   0.04113   0.03749   0.0287   0.0053   1.0000
  12.250   0.9961   0.04511   0.04169   0.0285   0.0053   1.0000
  12.500   0.9792   0.04991   0.04669   0.0269   0.0053   1.0000
  12.750   0.9563   0.05632   0.05331   0.0236   0.0054   1.0000
  13.000   0.9357   0.06365   0.06084   0.0186   0.0053   1.0000
  13.250   0.9131   0.07249   0.06983   0.0123   0.0054   1.0000
  13.500   0.8964   0.08138   0.07886   0.0061   0.0055   1.0000
  13.750   0.8767   0.09137   0.08897  -0.0002   0.0055   1.0000
  14.000   0.8710   0.09776   0.09540  -0.0038   0.0056   1.0000
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