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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 50,000
Max Cl/Cd: 33.47 at α=7.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3512-il-50000.txt
Download as CSV file: xf-hq3512-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3302   0.10373   0.09753  -0.0269   1.0000   0.2677
  -8.000  -0.3394   0.10196   0.09588  -0.0246   1.0000   0.2775
  -7.750  -0.3637   0.10198   0.09606  -0.0216   1.0000   0.2873
  -7.500  -0.3648   0.09977   0.09393  -0.0186   1.0000   0.3016
  -7.250  -0.3685   0.09784   0.09208  -0.0155   1.0000   0.3160
  -7.000  -0.3798   0.09655   0.09090  -0.0119   1.0000   0.3314
  -6.750  -0.3892   0.09511   0.08956  -0.0084   1.0000   0.3464
  -6.500  -0.4001   0.09381   0.08836  -0.0046   1.0000   0.3614
  -6.250  -0.3815   0.09022   0.08476  -0.0020   1.0000   0.3854
  -6.000  -0.3923   0.08897   0.08360   0.0019   1.0000   0.4030
  -5.750  -0.4138   0.08846   0.08322   0.0068   1.0000   0.4205
  -5.500  -0.3999   0.08516   0.07994   0.0092   1.0000   0.4427
  -5.250  -0.4159   0.08437   0.07925   0.0141   1.0000   0.4643
  -4.750  -0.4399   0.05428   0.04753  -0.0444   1.0000   0.1533
  -4.500  -0.4128   0.04893   0.04154  -0.0473   1.0000   0.1381
  -4.250  -0.3895   0.04505   0.03736  -0.0482   1.0000   0.1330
  -4.000  -0.3615   0.04139   0.03304  -0.0497   1.0000   0.1298
  -3.750  -0.3356   0.03888   0.02999  -0.0503   1.0000   0.1349
  -3.500  -0.3073   0.03660   0.02697  -0.0508   1.0000   0.1395
  -3.250  -0.2844   0.03469   0.02498  -0.0506   1.0000   0.1507
  -3.000  -0.2604   0.03310   0.02319  -0.0503   1.0000   0.1635
  -2.750  -0.2363   0.03173   0.02163  -0.0497   1.0000   0.1751
  -2.500  -0.2137   0.03074   0.02057  -0.0489   1.0000   0.1929
  -2.250  -0.1915   0.02987   0.01963  -0.0479   1.0000   0.2093
  -2.000  -0.1685   0.02910   0.01895  -0.0473   1.0000   0.2392
  -1.750  -0.1413   0.02798   0.01826  -0.0476   1.0000   0.2999
  -1.500  -0.1397   0.02680   0.01944  -0.0394   1.0000   0.7302
  -1.250  -0.1472   0.02668   0.01948  -0.0301   1.0000   0.8418
  -1.000  -0.1329   0.02585   0.01874  -0.0271   1.0000   1.0000
  -0.750  -0.1070   0.02628   0.01870  -0.0289   1.0000   1.0000
  -0.500  -0.0813   0.02681   0.01884  -0.0306   1.0000   1.0000
  -0.250  -0.0564   0.02741   0.01911  -0.0322   1.0000   1.0000
   0.000  -0.0323   0.02808   0.01947  -0.0335   1.0000   1.0000
   0.250  -0.0089   0.02881   0.01993  -0.0347   1.0000   1.0000
   0.500   0.0135   0.02959   0.02047  -0.0357   1.0000   1.0000
   0.750   0.0586   0.03118   0.02177  -0.0408   0.9884   1.0000
   1.000   0.1047   0.03280   0.02314  -0.0460   0.9743   1.0000
   1.250   0.1461   0.03423   0.02438  -0.0502   0.9606   1.0000
   1.500   0.1850   0.03557   0.02554  -0.0538   0.9467   1.0000
   1.750   0.2238   0.03688   0.02671  -0.0573   0.9317   1.0000
   2.000   0.2651   0.03818   0.02787  -0.0609   0.9151   1.0000
   2.250   0.3084   0.03931   0.02891  -0.0645   0.8945   1.0000
   2.500   0.3496   0.04020   0.02973  -0.0673   0.8727   1.0000
   2.750   0.3992   0.04110   0.03056  -0.0712   0.8528   1.0000
   3.000   0.4281   0.04181   0.03125  -0.0720   0.8332   1.0000
   3.250   0.4649   0.04252   0.03195  -0.0738   0.8148   1.0000
   3.500   0.5064   0.04311   0.03255  -0.0760   0.7972   1.0000
   3.750   0.5472   0.04355   0.03301  -0.0778   0.7795   1.0000
   4.000   0.5724   0.04413   0.03364  -0.0776   0.7590   1.0000
   4.250   0.6115   0.04435   0.03393  -0.0788   0.7406   1.0000
   4.500   0.6584   0.04408   0.03375  -0.0805   0.7231   1.0000
   4.750   0.6828   0.04451   0.03424  -0.0798   0.7015   1.0000
   5.000   0.7239   0.04409   0.03396  -0.0803   0.6826   1.0000
   5.250   0.7738   0.04294   0.03294  -0.0812   0.6656   1.0000
   5.500   0.8278   0.04119   0.03139  -0.0821   0.6497   1.0000
   5.750   0.8490   0.04137   0.03165  -0.0804   0.6268   1.0000
   6.000   0.9031   0.03951   0.02996  -0.0812   0.6097   1.0000
   6.250   0.9618   0.03722   0.02786  -0.0822   0.5927   1.0000
   6.500   0.9986   0.03652   0.02726  -0.0818   0.5724   1.0000
   6.750   1.0372   0.03577   0.02663  -0.0815   0.5519   1.0000
   7.000   1.0907   0.03427   0.02516  -0.0827   0.5326   1.0000
   7.250   1.1075   0.03520   0.02619  -0.0809   0.5122   1.0000
   7.500   1.1408   0.03522   0.02627  -0.0806   0.4925   1.0000
   7.750   1.1780   0.03520   0.02623  -0.0808   0.4736   1.0000
   8.000   1.1949   0.03640   0.02755  -0.0792   0.4554   1.0000
   8.250   1.2168   0.03738   0.02863  -0.0780   0.4374   1.0000
   8.500   1.2432   0.03818   0.02947  -0.0773   0.4191   1.0000
   8.750   1.2739   0.03889   0.03019  -0.0770   0.4004   1.0000
   9.000   1.2875   0.04045   0.03192  -0.0751   0.3834   1.0000
   9.250   1.3021   0.04195   0.03356  -0.0733   0.3659   1.0000
   9.500   1.3190   0.04342   0.03514  -0.0716   0.3486   1.0000
   9.750   1.3423   0.04460   0.03635  -0.0706   0.3300   1.0000
  10.000   1.3629   0.04612   0.03794  -0.0694   0.3123   1.0000
  10.250   1.3711   0.04811   0.04012  -0.0670   0.2964   1.0000
  10.500   1.3796   0.05025   0.04243  -0.0647   0.2810   1.0000
  10.750   1.3864   0.05241   0.04475  -0.0623   0.2658   1.0000
  11.000   1.3918   0.05461   0.04710  -0.0597   0.2509   1.0000
  11.250   1.3961   0.05685   0.04948  -0.0572   0.2368   1.0000
  11.500   1.3988   0.05893   0.05168  -0.0545   0.2227   1.0000
  11.750   1.1254   0.08713   0.08020  -0.0516   0.2752   1.0000
  12.000   1.0907   0.09731   0.09035  -0.0548   0.2709   1.0000
  12.250   1.3685   0.06673   0.05996  -0.0442   0.1938   1.0000
  12.500   1.3327   0.07176   0.06525  -0.0411   0.1932   1.0000
  12.750   1.2929   0.07817   0.07185  -0.0397   0.1943   1.0000
  13.000   1.2515   0.08600   0.07981  -0.0400   0.1960   1.0000
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