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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 50,000
Max Cl/Cd: 35.79 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2010-il-50000.txt
Download as CSV file: xf-hq2010-il-50000.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 =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4139   0.09927   0.09254  -0.0138   1.0000   0.2971
  -8.250  -0.4101   0.09621   0.08954  -0.0133   1.0000   0.3118
  -8.000  -0.4077   0.09334   0.08673  -0.0127   1.0000   0.3276
  -7.750  -0.4168   0.09151   0.08503  -0.0119   1.0000   0.3450
  -7.500  -0.3967   0.08750   0.08101  -0.0099   1.0000   0.3701
  -6.000  -0.4992   0.05161   0.04447  -0.0418   1.0000   0.1320
  -5.750  -0.4888   0.04719   0.03980  -0.0411   1.0000   0.1244
  -5.500  -0.4756   0.04307   0.03498  -0.0407   1.0000   0.1173
  -5.250  -0.4601   0.03978   0.03121  -0.0398   1.0000   0.1174
  -5.000  -0.4422   0.03690   0.02762  -0.0389   1.0000   0.1198
  -4.750  -0.4231   0.03400   0.02466  -0.0379   1.0000   0.1239
  -4.500  -0.4013   0.03154   0.02179  -0.0369   1.0000   0.1290
  -4.250  -0.3800   0.02951   0.01951  -0.0359   1.0000   0.1412
  -4.000  -0.3570   0.02753   0.01730  -0.0347   1.0000   0.1537
  -3.750  -0.3343   0.02602   0.01553  -0.0335   1.0000   0.1755
  -3.500  -0.3122   0.02445   0.01412  -0.0321   1.0000   0.2008
  -3.250  -0.2901   0.02293   0.01280  -0.0308   1.0000   0.2410
  -3.000  -0.2689   0.02032   0.01145  -0.0298   1.0000   0.3790
  -2.750  -0.2793   0.01973   0.01256  -0.0182   1.0000   0.7293
  -2.500  -0.2845   0.01983   0.01274  -0.0086   1.0000   0.8230
  -2.250  -0.1077   0.02086   0.01263  -0.0276   1.0000   1.0000
  -2.000  -0.1205   0.02045   0.01217  -0.0234   1.0000   1.0000
  -1.750  -0.1330   0.02000   0.01166  -0.0192   1.0000   1.0000
  -1.500  -0.1395   0.01961   0.01115  -0.0158   1.0000   1.0000
  -1.250  -0.1312   0.01947   0.01079  -0.0146   1.0000   1.0000
  -1.000  -0.1147   0.01952   0.01057  -0.0146   1.0000   1.0000
  -0.750  -0.0950   0.01970   0.01049  -0.0148   1.0000   1.0000
  -0.500  -0.0742   0.01996   0.01052  -0.0152   1.0000   1.0000
  -0.250  -0.0532   0.02028   0.01063  -0.0155   1.0000   1.0000
   0.000  -0.0322   0.02066   0.01080  -0.0157   1.0000   1.0000
   0.250  -0.0113   0.02109   0.01106  -0.0160   1.0000   1.0000
   0.500   0.0092   0.02156   0.01139  -0.0162   1.0000   1.0000
   0.750   0.0296   0.02208   0.01178  -0.0163   1.0000   1.0000
   1.000   0.0496   0.02265   0.01221  -0.0165   1.0000   1.0000
   1.250   0.0693   0.02326   0.01273  -0.0167   1.0000   1.0000
   1.500   0.0887   0.02392   0.01332  -0.0168   1.0000   1.0000
   1.750   0.1077   0.02463   0.01397  -0.0170   1.0000   1.0000
   2.000   0.1537   0.02601   0.01531  -0.0223   0.9865   1.0000
   2.250   0.2097   0.02757   0.01686  -0.0291   0.9679   1.0000
   2.500   0.2642   0.02877   0.01810  -0.0352   0.9440   1.0000
   2.750   0.3159   0.02977   0.01917  -0.0403   0.9198   1.0000
   3.000   0.3716   0.03068   0.02018  -0.0457   0.8982   1.0000
   3.250   0.4113   0.03133   0.02097  -0.0482   0.8752   1.0000
   3.500   0.4586   0.03189   0.02169  -0.0516   0.8529   1.0000
   3.750   0.5088   0.03219   0.02217  -0.0549   0.8298   1.0000
   4.000   0.5507   0.03236   0.02258  -0.0566   0.8045   1.0000
   4.250   0.6002   0.03211   0.02259  -0.0587   0.7787   1.0000
   4.500   0.6513   0.03141   0.02216  -0.0601   0.7524   1.0000
   4.750   0.6983   0.03040   0.02146  -0.0602   0.7244   1.0000
   5.000   0.7423   0.02915   0.02046  -0.0594   0.6940   1.0000
   5.250   0.7865   0.02760   0.01912  -0.0580   0.6615   1.0000
   5.500   0.8195   0.02668   0.01836  -0.0557   0.6234   1.0000
   5.750   0.8509   0.02589   0.01758  -0.0533   0.5827   1.0000
   6.000   0.8781   0.02548   0.01710  -0.0507   0.5394   1.0000
   6.250   0.9019   0.02545   0.01692  -0.0481   0.4941   1.0000
   6.500   0.9226   0.02578   0.01709  -0.0456   0.4472   1.0000
   6.750   0.9405   0.02657   0.01765  -0.0430   0.3977   1.0000
   7.000   0.9570   0.02780   0.01860  -0.0405   0.3454   1.0000
   7.250   0.9731   0.02945   0.01985  -0.0382   0.2922   1.0000
   7.500   0.9901   0.03158   0.02176  -0.0363   0.2464   1.0000
   7.750   1.0111   0.03389   0.02400  -0.0349   0.2146   1.0000
   8.000   1.0301   0.03589   0.02601  -0.0336   0.1908   1.0000
   8.250   1.0513   0.03829   0.02865  -0.0324   0.1746   1.0000
   8.500   1.0715   0.04106   0.03166  -0.0313   0.1628   1.0000
   8.750   1.0884   0.04352   0.03431  -0.0299   0.1507   1.0000
   9.000   1.1099   0.04646   0.03726  -0.0292   0.1412   1.0000
   9.250   1.1135   0.05054   0.04212  -0.0266   0.1375   1.0000
   9.500   1.1332   0.05371   0.04522  -0.0259   0.1281   1.0000
   9.750   1.1231   0.05780   0.05007  -0.0227   0.1250   1.0000
  10.000   1.1129   0.06234   0.05510  -0.0203   0.1229   1.0000
  10.250   1.0986   0.06720   0.06034  -0.0181   0.1225   1.0000
  10.500   1.0774   0.07211   0.06554  -0.0163   0.1233   1.0000
  10.750   1.0521   0.07684   0.07043  -0.0147   0.1246   1.0000
  11.000   1.0276   0.08211   0.07582  -0.0146   0.1259   1.0000
  11.250   1.0065   0.08807   0.08185  -0.0157   0.1271   1.0000
  11.500   0.9907   0.09464   0.08845  -0.0176   0.1280   1.0000
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