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HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL (hq300gd2-il)
Reynolds number: 50,000
Max Cl/Cd: 5.4 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq300gd2-il-50000.txt
Download as CSV file: xf-hq300gd2-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HORSTMANN AND QUAST HQ-300 GD(MOD 2) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3260   0.13230   0.12641  -0.0336   1.0000   0.2573
 -10.250  -0.3217   0.12996   0.12414  -0.0302   1.0000   0.2651
 -10.000  -0.3473   0.13071   0.12501  -0.0271   1.0000   0.2729
  -9.750  -0.3456   0.12852   0.12289  -0.0243   1.0000   0.2813
  -9.500  -0.3752   0.12929   0.12379  -0.0217   1.0000   0.2898
  -9.250  -0.3643   0.12641   0.12093  -0.0191   1.0000   0.3008
  -9.000  -0.3898   0.12603   0.12068  -0.0169   1.0000   0.3090
  -8.750  -0.3964   0.12493   0.11963  -0.0143   1.0000   0.3220
  -8.500  -0.3878   0.12219   0.11692  -0.0121   1.0000   0.3337
  -8.250  -0.3966   0.12059   0.11540  -0.0098   1.0000   0.3453
  -8.000  -0.4185   0.11992   0.11483  -0.0071   1.0000   0.3581
  -7.750  -0.4384   0.11954   0.11453  -0.0041   1.0000   0.3725
  -7.500  -0.4385   0.11750   0.11253  -0.0015   1.0000   0.3888
  -7.250  -0.4431   0.11577   0.11086   0.0012   1.0000   0.4053
  -7.000  -0.4000   0.11113   0.10613  -0.0002   0.9962   0.4334
  -6.750  -0.3885   0.10834   0.10334  -0.0004   0.9922   0.4592
  -6.500  -0.3715   0.10542   0.10041  -0.0009   0.9881   0.4814
  -6.000  -0.3558   0.10002   0.09502  -0.0013   0.9806   0.5133
  -5.750  -0.3609   0.09785   0.09289   0.0000   0.9769   0.5248
  -5.250  -0.5813   0.06545   0.05895  -0.0379   1.0000   0.1779
  -5.000  -0.5567   0.06021   0.05335  -0.0399   1.0000   0.1572
  -4.750  -0.5253   0.05596   0.04822  -0.0433   1.0000   0.1442
  -4.500  -0.5001   0.05305   0.04494  -0.0448   1.0000   0.1415
  -4.250  -0.4718   0.05040   0.04175  -0.0464   1.0000   0.1371
  -4.000  -0.4415   0.04837   0.03899  -0.0477   1.0000   0.1330
  -3.750  -0.4166   0.04682   0.03715  -0.0482   1.0000   0.1339
  -3.500  -0.3932   0.04565   0.03582  -0.0484   1.0000   0.1374
  -3.250  -0.3691   0.04472   0.03464  -0.0484   1.0000   0.1402
  -3.000  -0.3457   0.04399   0.03368  -0.0480   1.0000   0.1426
  -2.750  -0.3230   0.04360   0.03304  -0.0474   1.0000   0.1470
  -2.500  -0.3040   0.04309   0.03267  -0.0461   1.0000   0.1549
  -2.250  -0.2843   0.04302   0.03247  -0.0446   1.0000   0.1629
  -2.000  -0.2644   0.04282   0.03239  -0.0435   1.0000   0.1739
  -1.750  -0.2394   0.04266   0.03238  -0.0439   1.0000   0.1966
  -1.500  -0.1065   0.04652   0.03894  -0.0405   0.9535   0.9982
  -0.750  -0.2097   0.04321   0.03576  -0.0142   1.0000   1.0000
  -0.500  -0.2046   0.04315   0.03545  -0.0124   1.0000   1.0000
  -0.250  -0.1986   0.04316   0.03523  -0.0108   1.0000   1.0000
   0.000  -0.1902   0.04330   0.03516  -0.0096   1.0000   1.0000
   0.250  -0.1791   0.04361   0.03528  -0.0090   1.0000   1.0000
   0.500  -0.1654   0.04410   0.03557  -0.0089   1.0000   1.0000
   0.750  -0.1496   0.04476   0.03605  -0.0093   1.0000   1.0000
   1.000  -0.1321   0.04556   0.03667  -0.0100   1.0000   1.0000
   1.250  -0.1135   0.04649   0.03744  -0.0109   1.0000   1.0000
   1.500  -0.0909   0.04771   0.03850  -0.0126   0.9986   1.0000
   1.750  -0.0514   0.05006   0.04064  -0.0177   0.9898   1.0000
   2.000  -0.0125   0.05256   0.04296  -0.0226   0.9807   1.0000
   2.250   0.0306   0.05546   0.04568  -0.0282   0.9698   1.0000
   2.500   0.0621   0.05730   0.04741  -0.0315   0.9563   1.0000
   2.750   0.0904   0.05900   0.04902  -0.0342   0.9425   1.0000
   3.000   0.1172   0.06074   0.05067  -0.0366   0.9287   1.0000
   3.250   0.1437   0.06261   0.05248  -0.0389   0.9157   1.0000
   3.500   0.1744   0.06494   0.05474  -0.0420   0.9039   1.0000
   3.750   0.2156   0.06813   0.05786  -0.0469   0.8915   1.0000
   4.000   0.2355   0.06944   0.05915  -0.0479   0.8766   1.0000
   4.250   0.2549   0.07097   0.06066  -0.0489   0.8623   1.0000
   4.500   0.2748   0.07274   0.06242  -0.0501   0.8488   1.0000
   4.750   0.2980   0.07488   0.06455  -0.0519   0.8364   1.0000
   5.000   0.3363   0.07826   0.06791  -0.0560   0.8255   1.0000
   5.250   0.3586   0.08014   0.06981  -0.0575   0.8108   1.0000
   5.500   0.3714   0.08157   0.07125  -0.0576   0.7967   1.0000
   5.750   0.3865   0.08343   0.07314  -0.0582   0.7837   1.0000
   6.000   0.4072   0.08583   0.07556  -0.0597   0.7722   1.0000
   6.250   0.4475   0.08956   0.07932  -0.0638   0.7608   1.0000
   6.500   0.4583   0.09096   0.08078  -0.0637   0.7465   1.0000
   6.750   0.4665   0.09265   0.08251  -0.0635   0.7336   1.0000
   7.000   0.4816   0.09503   0.08494  -0.0644   0.7225   1.0000
   7.250   0.5158   0.09858   0.08855  -0.0675   0.7118   1.0000
   7.500   0.5301   0.10052   0.09055  -0.0680   0.6982   1.0000
   7.750   0.5342   0.10233   0.09243  -0.0677   0.6862   1.0000
   8.000   0.5506   0.10514   0.09530  -0.0689   0.6765   1.0000
   8.250   0.5891   0.10900   0.09925  -0.0721   0.6646   1.0000
   8.500   0.5854   0.11022   0.10054  -0.0711   0.6521   1.0000
   8.750   0.5927   0.11279   0.10318  -0.0715   0.6427   1.0000
   9.000   0.6257   0.11660   0.10708  -0.0742   0.6323   1.0000
   9.250   0.6302   0.11842   0.10898  -0.0741   0.6197   1.0000
   9.500   0.6332   0.12100   0.11166  -0.0744   0.6111   1.0000
   9.750   0.6645   0.12489   0.11564  -0.0768   0.6008   1.0000
  10.000   0.6655   0.12674   0.11757  -0.0767   0.5891   1.0000
  10.250   0.6719   0.12972   0.12064  -0.0775   0.5813   1.0000
  10.500   0.7051   0.13378   0.12483  -0.0798   0.5699   1.0000
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