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HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il)
Reynolds number: 50,000
Max Cl/Cd: 32.99 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3014-il-50000-n5.txt
Download as CSV file: xf-hq3014-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/14 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3701   0.10661   0.09939  -0.0519   1.0000   0.0607
 -10.750  -0.3771   0.10208   0.09495  -0.0533   1.0000   0.0609
 -10.500  -0.3854   0.09750   0.09046  -0.0546   1.0000   0.0608
 -10.250  -0.3976   0.09244   0.08552  -0.0563   1.0000   0.0608
 -10.000  -0.4129   0.08709   0.08029  -0.0581   1.0000   0.0606
  -9.750  -0.4358   0.08121   0.07453  -0.0602   1.0000   0.0600
  -9.500  -0.4668   0.07636   0.06978  -0.0610   1.0000   0.0591
  -9.250  -0.5035   0.07292   0.06642  -0.0596   1.0000   0.0581
  -9.000  -0.5441   0.07040   0.06396  -0.0566   1.0000   0.0571
  -8.750  -0.5788   0.06715   0.06066  -0.0540   1.0000   0.0563
  -8.500  -0.6026   0.06410   0.05751  -0.0517   1.0000   0.0562
  -8.250  -0.6185   0.06115   0.05440  -0.0496   1.0000   0.0567
  -8.000  -0.6109   0.05659   0.04946  -0.0524   0.9932   0.0584
  -7.750  -0.5995   0.05207   0.04436  -0.0549   0.9855   0.0614
  -7.500  -0.5863   0.04743   0.03879  -0.0569   0.9781   0.0647
  -7.250  -0.5622   0.04518   0.03655  -0.0583   0.9725   0.0682
  -7.000  -0.5386   0.04294   0.03396  -0.0595   0.9667   0.0732
  -6.750  -0.5153   0.04025   0.03060  -0.0603   0.9605   0.0781
  -6.500  -0.4855   0.03865   0.02896  -0.0619   0.9560   0.0837
  -6.250  -0.4619   0.03699   0.02687  -0.0619   0.9496   0.0892
  -6.000  -0.4336   0.03552   0.02527  -0.0627   0.9445   0.0952
  -5.750  -0.4011   0.03421   0.02374  -0.0638   0.9404   0.1009
  -5.500  -0.3778   0.03318   0.02253  -0.0632   0.9337   0.1073
  -5.250  -0.3482   0.03228   0.02157  -0.0639   0.9288   0.1156
  -5.000  -0.3187   0.03141   0.02060  -0.0642   0.9241   0.1233
  -4.750  -0.2957   0.03074   0.01985  -0.0637   0.9174   0.1340
  -4.500  -0.2657   0.02997   0.01910  -0.0646   0.9126   0.1487
  -4.250  -0.2427   0.02928   0.01846  -0.0643   0.9064   0.1668
  -4.000  -0.2173   0.02848   0.01780  -0.0647   0.9003   0.1967
  -3.750  -0.1863   0.02729   0.01704  -0.0664   0.8961   0.2651
  -3.500  -0.1728   0.02639   0.01703  -0.0646   0.8886   0.3851
  -3.250  -0.1491   0.02648   0.01753  -0.0630   0.8829   0.5281
  -3.000  -0.1280   0.02685   0.01789  -0.0611   0.8765   0.5922
  -2.750  -0.1075   0.02726   0.01823  -0.0589   0.8696   0.6384
  -2.500  -0.0801   0.02770   0.01859  -0.0575   0.8651   0.6822
  -2.250  -0.0702   0.02809   0.01895  -0.0535   0.8562   0.7130
  -2.000  -0.0452   0.02835   0.01912  -0.0518   0.8511   0.7434
  -1.750  -0.0302   0.02854   0.01923  -0.0491   0.8433   0.7634
  -1.500  -0.0060   0.02861   0.01918  -0.0478   0.8372   0.7850
  -1.250   0.0157   0.02867   0.01914  -0.0462   0.8309   0.8061
  -1.000   0.0352   0.02870   0.01909  -0.0445   0.8233   0.8237
  -0.750   0.0700   0.02861   0.01886  -0.0455   0.8189   0.8383
  -0.500   0.0850   0.02871   0.01888  -0.0439   0.8094   0.8507
  -0.250   0.1210   0.02862   0.01869  -0.0453   0.8045   0.8616
   0.000   0.1409   0.02875   0.01875  -0.0445   0.7957   0.8741
   0.250   0.1769   0.02871   0.01863  -0.0461   0.7902   0.8863
   0.500   0.2044   0.02885   0.01874  -0.0466   0.7822   0.9001
   0.750   0.2431   0.02889   0.01873  -0.0488   0.7759   0.9137
   1.000   0.2875   0.02892   0.01871  -0.0521   0.7705   0.9276
   1.250   0.3249   0.02916   0.01893  -0.0547   0.7618   0.9456
   1.500   0.3784   0.02902   0.01875  -0.0595   0.7575   0.9625
   1.750   0.4081   0.02936   0.01908  -0.0613   0.7466   1.0000
   2.000   0.4335   0.02937   0.01902  -0.0614   0.7390   1.0000
   2.500   0.4776   0.02970   0.01924  -0.0606   0.7181   1.0000
   2.750   0.5188   0.02930   0.01879  -0.0623   0.7116   1.0000
   3.000   0.5384   0.02957   0.01903  -0.0614   0.6990   1.0000
   3.250   0.5620   0.02974   0.01919  -0.0610   0.6877   1.0000
   3.500   0.6022   0.02932   0.01875  -0.0623   0.6810   1.0000
   3.750   0.6217   0.02965   0.01908  -0.0613   0.6684   1.0000
   4.000   0.6446   0.02987   0.01932  -0.0606   0.6566   1.0000
   4.250   0.6793   0.02957   0.01903  -0.0612   0.6478   1.0000
   4.500   0.7063   0.02956   0.01904  -0.0608   0.6363   1.0000
   4.750   0.7283   0.02972   0.01926  -0.0598   0.6229   1.0000
   5.000   0.7521   0.02978   0.01935  -0.0589   0.6096   1.0000
   5.250   0.7774   0.02976   0.01936  -0.0582   0.5960   1.0000
   5.500   0.8032   0.02967   0.01934  -0.0574   0.5819   1.0000
   5.750   0.8285   0.02959   0.01930  -0.0566   0.5669   1.0000
   6.000   0.8530   0.02955   0.01929  -0.0556   0.5512   1.0000
   6.250   0.8772   0.02953   0.01933  -0.0546   0.5346   1.0000
   6.500   0.9017   0.02952   0.01934  -0.0536   0.5175   1.0000
   6.750   0.9271   0.02952   0.01934  -0.0527   0.4999   1.0000
   7.000   0.9526   0.02956   0.01938  -0.0519   0.4818   1.0000
   7.250   0.9700   0.03001   0.01985  -0.0503   0.4623   1.0000
   7.500   0.9901   0.03040   0.02022  -0.0490   0.4430   1.0000
   7.750   1.0110   0.03080   0.02058  -0.0478   0.4239   1.0000
   8.000   1.0318   0.03128   0.02102  -0.0466   0.4059   1.0000
   8.250   1.0468   0.03206   0.02180  -0.0450   0.3876   1.0000
   8.500   1.0620   0.03289   0.02262  -0.0435   0.3703   1.0000
   8.750   1.0775   0.03375   0.02349  -0.0421   0.3541   1.0000
   9.000   1.0924   0.03467   0.02443  -0.0406   0.3385   1.0000
   9.250   1.1075   0.03564   0.02540  -0.0393   0.3239   1.0000
   9.500   1.1227   0.03664   0.02641  -0.0380   0.3101   1.0000
   9.750   1.1378   0.03768   0.02744  -0.0367   0.2967   1.0000
  10.000   1.1543   0.03870   0.02846  -0.0357   0.2841   1.0000
  10.250   1.1644   0.04006   0.02995  -0.0342   0.2717   1.0000
  10.500   1.1750   0.04143   0.03142  -0.0328   0.2599   1.0000
  10.750   1.1872   0.04275   0.03280  -0.0316   0.2489   1.0000
  11.000   1.2002   0.04397   0.03401  -0.0304   0.2380   1.0000
  11.250   1.2046   0.04576   0.03599  -0.0289   0.2276   1.0000
  11.500   1.2117   0.04745   0.03778  -0.0276   0.2180   1.0000
  11.750   1.2222   0.04882   0.03916  -0.0265   0.2084   1.0000
  12.000   1.2223   0.05108   0.04167  -0.0252   0.1995   1.0000
  12.250   1.2284   0.05292   0.04357  -0.0241   0.1910   1.0000
  12.500   1.2308   0.05503   0.04579  -0.0231   0.1825   1.0000
  12.750   1.2316   0.05748   0.04840  -0.0222   0.1748   1.0000
  13.000   1.2359   0.05956   0.05053  -0.0214   0.1672   1.0000
  13.250   1.2322   0.06263   0.05380  -0.0209   0.1604   1.0000
  13.500   1.2331   0.06515   0.05641  -0.0204   0.1536   1.0000
  13.750   1.2300   0.06839   0.05981  -0.0201   0.1477   1.0000
  14.000   1.2220   0.07225   0.06391  -0.0202   0.1421   1.0000
  14.250   1.2285   0.07432   0.06596  -0.0199   0.1362   1.0000
  14.500   1.2072   0.08028   0.07226  -0.0211   0.1323   1.0000
  14.750   1.1946   0.08533   0.07750  -0.0223   0.1282   1.0000
  15.000   1.2084   0.08657   0.07868  -0.0218   0.1230   1.0000
  15.250   1.1731   0.09558   0.08804  -0.0253   0.1211   1.0000
  15.500   1.1206   0.10881   0.10156  -0.0318   0.1196   1.0000
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