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HQ 0/7 AIRFOIL (hq07-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: HQ 0/7 AIRFOIL (hq07-il)
Reynolds number: 500,000
Max Cl/Cd: 50.25 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq07-il-500000.txt
Download as CSV file: xf-hq07-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/7 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.6514   0.08050   0.07837  -0.0005   1.0000   0.0122
  -8.500  -0.6579   0.07352   0.07136  -0.0072   1.0000   0.0122
  -8.250  -0.6704   0.06894   0.06671  -0.0096   1.0000   0.0122
  -8.000  -0.6780   0.06449   0.06215  -0.0107   1.0000   0.0122
  -7.750  -0.6994   0.05600   0.05345  -0.0123   1.0000   0.0125
  -7.500  -0.7080   0.04914   0.04633  -0.0128   1.0000   0.0130
  -7.250  -0.7047   0.04418   0.04112  -0.0127   1.0000   0.0133
  -7.000  -0.6952   0.04003   0.03672  -0.0122   1.0000   0.0136
  -6.750  -0.6826   0.03607   0.03247  -0.0115   1.0000   0.0139
  -6.500  -0.6649   0.03216   0.02814  -0.0101   1.0000   0.0131
  -6.250  -0.6515   0.02634   0.02191  -0.0087   1.0000   0.0091
  -6.000  -0.6352   0.01882   0.01342  -0.0058   1.0000   0.0070
  -5.750  -0.6122   0.01643   0.01070  -0.0047   1.0000   0.0069
  -5.500  -0.5894   0.01450   0.00853  -0.0036   1.0000   0.0071
  -5.250  -0.5659   0.01319   0.00708  -0.0027   1.0000   0.0079
  -5.000  -0.5412   0.01236   0.00617  -0.0021   1.0000   0.0100
  -4.750  -0.5176   0.01123   0.00490  -0.0012   1.0000   0.0162
  -4.500  -0.4899   0.01146   0.00516  -0.0012   1.0000   0.0220
  -4.250  -0.4662   0.01065   0.00432  -0.0007   1.0000   0.0290
  -4.000  -0.4410   0.01017   0.00376  -0.0001   1.0000   0.0318
  -3.750  -0.4163   0.00962   0.00313   0.0005   1.0000   0.0367
  -3.500  -0.3919   0.00902   0.00258   0.0012   1.0000   0.0555
  -3.250  -0.3697   0.00813   0.00216   0.0018   1.0000   0.1551
  -3.000  -0.3471   0.00748   0.00187   0.0025   1.0000   0.2580
  -2.750  -0.3260   0.00671   0.00164   0.0033   1.0000   0.3947
  -2.500  -0.3055   0.00609   0.00150   0.0044   1.0000   0.5197
  -2.250  -0.2824   0.00568   0.00150   0.0051   0.9985   0.6331
  -2.000  -0.2444   0.00548   0.00149   0.0029   0.9897   0.6967
  -1.750  -0.2058   0.00537   0.00144   0.0006   0.9817   0.7343
  -1.500  -0.1699   0.00528   0.00142  -0.0010   0.9709   0.7650
  -1.250  -0.1351   0.00521   0.00141  -0.0023   0.9583   0.7904
  -1.000  -0.1030   0.00518   0.00138  -0.0030   0.9423   0.8060
  -0.750  -0.0753   0.00516   0.00135  -0.0028   0.9235   0.8200
  -0.500  -0.0494   0.00514   0.00132  -0.0020   0.9053   0.8350
  -0.250  -0.0243   0.00512   0.00131  -0.0011   0.8883   0.8508
   0.000   0.0000   0.00512   0.00130   0.0000   0.8692   0.8694
   0.250   0.0244   0.00512   0.00131   0.0011   0.8507   0.8883
   0.500   0.0495   0.00514   0.00132   0.0020   0.8350   0.9053
   0.750   0.0753   0.00516   0.00135   0.0027   0.8200   0.9235
   1.000   0.1031   0.00518   0.00138   0.0030   0.8060   0.9424
   1.250   0.1352   0.00521   0.00141   0.0023   0.7904   0.9582
   1.500   0.1699   0.00528   0.00142   0.0010   0.7650   0.9710
   1.750   0.2058   0.00537   0.00144  -0.0006   0.7342   0.9818
   2.000   0.2445   0.00548   0.00149  -0.0029   0.6971   0.9897
   2.250   0.2823   0.00569   0.00150  -0.0051   0.6306   0.9986
   2.500   0.3055   0.00608   0.00150  -0.0044   0.5216   1.0000
   2.750   0.3259   0.00672   0.00164  -0.0033   0.3934   1.0000
   3.000   0.3471   0.00748   0.00187  -0.0025   0.2581   1.0000
   3.250   0.3696   0.00813   0.00216  -0.0018   0.1551   1.0000
   3.500   0.3918   0.00902   0.00259  -0.0012   0.0552   1.0000
   3.750   0.4162   0.00963   0.00314  -0.0005   0.0365   1.0000
   4.000   0.4410   0.01016   0.00376   0.0001   0.0318   1.0000
   4.250   0.4661   0.01065   0.00432   0.0007   0.0290   1.0000
   4.500   0.4899   0.01147   0.00517   0.0012   0.0220   1.0000
   4.750   0.5176   0.01124   0.00491   0.0012   0.0162   1.0000
   5.000   0.5411   0.01237   0.00618   0.0021   0.0101   1.0000
   5.250   0.5658   0.01320   0.00710   0.0027   0.0080   1.0000
   5.500   0.5893   0.01451   0.00855   0.0036   0.0071   1.0000
   5.750   0.6122   0.01643   0.01070   0.0047   0.0069   1.0000
   6.000   0.6352   0.01878   0.01338   0.0058   0.0070   1.0000
   6.250   0.6515   0.02639   0.02196   0.0087   0.0091   1.0000
   6.500   0.6465   0.02006   0.01635   0.0104   0.0136   1.0000
   6.750   0.6591   0.02490   0.02162   0.0116   0.0140   1.0000
   7.000   0.6693   0.02927   0.02627   0.0122   0.0138   1.0000
   7.250   0.6762   0.03381   0.03104   0.0125   0.0135   1.0000
   7.500   0.6786   0.03883   0.03627   0.0127   0.0133   1.0000
   7.750   0.6743   0.04435   0.04198   0.0126   0.0130   1.0000
   8.000   0.6646   0.04986   0.04765   0.0122   0.0129   1.0000
   8.250   0.6499   0.05431   0.05222   0.0120   0.0128   1.0000
   8.500   0.6321   0.05881   0.05681   0.0098   0.0129   1.0000
   8.750   0.6172   0.06716   0.06523   0.0026   0.0132   1.0000
   9.000   0.6067   0.07484   0.07289  -0.0023   0.0133   1.0000
   9.250   0.5992   0.08136   0.07940  -0.0056   0.0133   1.0000
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