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HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il)
Reynolds number: 100,000
Max Cl/Cd: 45.1 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1012-il-100000-n5.txt
Download as CSV file: xf-hq1012-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.6612   0.09127   0.08612  -0.0279   1.0000   0.0252
 -12.250  -0.6848   0.08154   0.07635  -0.0343   1.0000   0.0247
 -12.000  -0.7108   0.07263   0.06734  -0.0408   1.0000   0.0242
 -11.750  -0.7351   0.06549   0.06005  -0.0457   1.0000   0.0239
 -11.500  -0.7577   0.05967   0.05408  -0.0490   1.0000   0.0238
 -11.250  -0.7789   0.05479   0.04897  -0.0507   1.0000   0.0239
 -11.000  -0.7967   0.05082   0.04475  -0.0508   1.0000   0.0241
 -10.750  -0.8117   0.04754   0.04120  -0.0494   1.0000   0.0243
 -10.500  -0.8226   0.04464   0.03797  -0.0471   1.0000   0.0249
 -10.250  -0.8248   0.04200   0.03504  -0.0453   1.0000   0.0258
 -10.000  -0.8180   0.04029   0.03326  -0.0440   1.0000   0.0268
  -9.750  -0.8096   0.03868   0.03152  -0.0426   1.0000   0.0282
  -9.500  -0.8007   0.03666   0.02925  -0.0410   1.0000   0.0297
  -9.250  -0.7899   0.03438   0.02664  -0.0394   1.0000   0.0313
  -9.000  -0.7765   0.03227   0.02417  -0.0378   1.0000   0.0331
  -8.750  -0.7628   0.03071   0.02257  -0.0364   1.0000   0.0354
  -8.500  -0.7479   0.02969   0.02149  -0.0350   1.0000   0.0385
  -8.250  -0.7319   0.02835   0.01992  -0.0334   1.0000   0.0419
  -8.000  -0.7170   0.02698   0.01844  -0.0318   1.0000   0.0453
  -7.750  -0.7022   0.02612   0.01756  -0.0301   1.0000   0.0495
  -7.500  -0.6864   0.02519   0.01643  -0.0283   1.0000   0.0543
  -7.250  -0.6734   0.02421   0.01550  -0.0264   1.0000   0.0589
  -7.000  -0.6599   0.02348   0.01470  -0.0243   1.0000   0.0641
  -6.750  -0.6473   0.02272   0.01386  -0.0220   1.0000   0.0692
  -6.500  -0.6312   0.02200   0.01315  -0.0206   0.9985   0.0753
  -6.250  -0.5984   0.02108   0.01214  -0.0223   0.9906   0.0841
  -6.000  -0.5645   0.02031   0.01127  -0.0241   0.9835   0.0946
  -5.750  -0.5335   0.01946   0.01044  -0.0255   0.9753   0.1060
  -5.500  -0.5004   0.01868   0.00971  -0.0272   0.9684   0.1242
  -5.250  -0.4693   0.01793   0.00906  -0.0285   0.9605   0.1514
  -5.000  -0.4368   0.01719   0.00850  -0.0302   0.9538   0.1954
  -4.750  -0.4072   0.01649   0.00800  -0.0312   0.9456   0.2500
  -4.500  -0.3787   0.01574   0.00756  -0.0319   0.9378   0.3156
  -4.250  -0.3508   0.01510   0.00729  -0.0324   0.9300   0.4041
  -4.000  -0.3238   0.01474   0.00722  -0.0322   0.9219   0.4832
  -3.750  -0.2938   0.01461   0.00722  -0.0324   0.9150   0.5438
  -3.500  -0.2661   0.01460   0.00722  -0.0320   0.9069   0.5868
  -3.250  -0.2358   0.01462   0.00722  -0.0321   0.9003   0.6207
  -3.000  -0.2088   0.01468   0.00723  -0.0316   0.8921   0.6485
  -2.750  -0.1791   0.01473   0.00724  -0.0315   0.8855   0.6697
  -2.500  -0.1525   0.01476   0.00720  -0.0310   0.8772   0.6859
  -2.250  -0.1230   0.01476   0.00713  -0.0309   0.8706   0.7001
  -2.000  -0.0968   0.01478   0.00709  -0.0304   0.8622   0.7130
  -1.750  -0.0682   0.01478   0.00702  -0.0302   0.8558   0.7263
  -1.500  -0.0432   0.01483   0.00705  -0.0293   0.8473   0.7411
  -1.250  -0.0158   0.01486   0.00704  -0.0287   0.8408   0.7563
  -1.000   0.0087   0.01489   0.00706  -0.0278   0.8320   0.7696
  -0.750   0.0366   0.01486   0.00697  -0.0275   0.8257   0.7808
  -0.500   0.0618   0.01487   0.00698  -0.0268   0.8166   0.7890
  -0.250   0.0896   0.01482   0.00688  -0.0266   0.8100   0.7982
   0.000   0.1150   0.01483   0.00689  -0.0260   0.8011   0.8072
   0.250   0.1425   0.01480   0.00685  -0.0257   0.7942   0.8160
   0.500   0.1683   0.01479   0.00684  -0.0252   0.7855   0.8261
   0.750   0.1952   0.01476   0.00682  -0.0247   0.7765   0.8348
   1.000   0.2224   0.01467   0.00671  -0.0241   0.7668   0.8442
   1.250   0.2475   0.01460   0.00665  -0.0233   0.7541   0.8548
   1.500   0.2740   0.01452   0.00658  -0.0226   0.7410   0.8641
   1.750   0.3007   0.01444   0.00652  -0.0220   0.7279   0.8743
   2.000   0.3279   0.01438   0.00650  -0.0216   0.7159   0.8854
   2.250   0.3570   0.01434   0.00649  -0.0216   0.7052   0.8964
   2.500   0.3879   0.01431   0.00650  -0.0219   0.6936   0.9070
   2.750   0.4195   0.01430   0.00657  -0.0225   0.6804   0.9183
   3.000   0.4526   0.01429   0.00662  -0.0234   0.6662   0.9303
   3.250   0.4868   0.01428   0.00666  -0.0246   0.6507   0.9432
   3.500   0.5220   0.01428   0.00672  -0.0260   0.6331   0.9564
   4.000   0.5949   0.01431   0.00684  -0.0295   0.5857   0.9845
   4.250   0.6284   0.01438   0.00690  -0.0308   0.5539   1.0000
   4.500   0.6449   0.01452   0.00695  -0.0288   0.5221   1.0000
   4.750   0.6629   0.01475   0.00704  -0.0270   0.4849   1.0000
   5.000   0.6814   0.01511   0.00719  -0.0253   0.4431   1.0000
   5.250   0.6998   0.01557   0.00744  -0.0237   0.4001   1.0000
   5.500   0.7186   0.01611   0.00781  -0.0223   0.3593   1.0000
   5.750   0.7376   0.01670   0.00822  -0.0210   0.3238   1.0000
   6.000   0.7569   0.01731   0.00868  -0.0198   0.2948   1.0000
   6.250   0.7766   0.01792   0.00919  -0.0187   0.2712   1.0000
   6.500   0.7969   0.01852   0.00977  -0.0177   0.2500   1.0000
   6.750   0.8170   0.01913   0.01036  -0.0167   0.2290   1.0000
   7.000   0.8370   0.01975   0.01096  -0.0157   0.2074   1.0000
   7.250   0.8566   0.02039   0.01157  -0.0146   0.1853   1.0000
   7.500   0.8757   0.02107   0.01223  -0.0135   0.1638   1.0000
   7.750   0.8939   0.02184   0.01297  -0.0124   0.1445   1.0000
   8.000   0.9113   0.02268   0.01377  -0.0111   0.1291   1.0000
   8.250   0.9282   0.02357   0.01464  -0.0098   0.1158   1.0000
   8.500   0.9448   0.02449   0.01559  -0.0085   0.1044   1.0000
   8.750   0.9604   0.02550   0.01661  -0.0070   0.0956   1.0000
   9.000   0.9746   0.02656   0.01766  -0.0056   0.0875   1.0000
   9.250   0.9902   0.02754   0.01875  -0.0042   0.0792   1.0000
   9.500   1.0020   0.02872   0.01994  -0.0025   0.0732   1.0000
   9.750   1.0154   0.02976   0.02115  -0.0008   0.0669   1.0000
  10.000   1.0239   0.03103   0.02242   0.0012   0.0622   1.0000
  10.250   1.0352   0.03228   0.02385   0.0029   0.0570   1.0000
  10.500   1.0440   0.03359   0.02524   0.0046   0.0525   1.0000
  10.750   1.0502   0.03526   0.02692   0.0063   0.0491   1.0000
  11.000   1.0593   0.03678   0.02869   0.0078   0.0449   1.0000
  11.250   1.0647   0.03834   0.03035   0.0092   0.0414   1.0000
  11.500   1.0675   0.04031   0.03235   0.0105   0.0385   1.0000
  11.750   1.0726   0.04226   0.03460   0.0116   0.0353   1.0000
  12.000   1.0748   0.04422   0.03669   0.0123   0.0325   1.0000
  12.250   1.0749   0.04654   0.03907   0.0130   0.0308   1.0000
  12.500   1.0736   0.04931   0.04201   0.0134   0.0288   1.0000
  12.750   1.0721   0.05224   0.04520   0.0137   0.0270   1.0000
  13.000   1.0687   0.05544   0.04859   0.0136   0.0257   1.0000
  13.250   1.0641   0.05891   0.05223   0.0131   0.0248   1.0000
  13.500   1.0579   0.06266   0.05611   0.0123   0.0240   1.0000
  13.750   1.0507   0.06674   0.06034   0.0111   0.0235   1.0000
  14.000   1.0416   0.07123   0.06493   0.0094   0.0229   1.0000
  14.250   1.0304   0.07636   0.07017   0.0073   0.0225   1.0000
  14.500   1.0157   0.08248   0.07654   0.0043   0.0222   1.0000
  14.750   0.9994   0.08933   0.08361   0.0005   0.0221   1.0000
  15.000   0.9810   0.09706   0.09154  -0.0040   0.0221   1.0000
  15.250   0.9586   0.10627   0.10095  -0.0097   0.0221   1.0000
  15.500   0.9401   0.11501   0.10983  -0.0149   0.0224   1.0000
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