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HQ 1.0/10 AIRFOIL (hq1010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/10 AIRFOIL (hq1010-il)
Reynolds number: 50,000
Max Cl/Cd: 32.91 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq1010-il-50000-n5.txt
Download as CSV file: xf-hq1010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/10 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.5697   0.09381   0.08691  -0.0209   1.0000   0.0431
  -9.750  -0.5764   0.08739   0.08055  -0.0250   1.0000   0.0424
  -9.500  -0.5884   0.08006   0.07327  -0.0304   1.0000   0.0417
  -9.250  -0.6055   0.07371   0.06694  -0.0350   1.0000   0.0410
  -9.000  -0.6258   0.06856   0.06174  -0.0374   1.0000   0.0405
  -8.750  -0.6408   0.06382   0.05686  -0.0385   1.0000   0.0400
  -8.500  -0.6500   0.05933   0.05215  -0.0388   1.0000   0.0400
  -8.250  -0.6537   0.05512   0.04765  -0.0386   1.0000   0.0402
  -8.000  -0.6522   0.05129   0.04350  -0.0380   1.0000   0.0411
  -7.750  -0.6468   0.04782   0.03967  -0.0371   1.0000   0.0429
  -7.500  -0.6389   0.04435   0.03570  -0.0361   1.0000   0.0454
  -7.250  -0.6280   0.04094   0.03160  -0.0347   1.0000   0.0480
  -7.000  -0.6130   0.03785   0.02828  -0.0336   1.0000   0.0502
  -6.750  -0.5956   0.03545   0.02565  -0.0324   1.0000   0.0532
  -6.500  -0.5771   0.03340   0.02319  -0.0311   1.0000   0.0596
  -6.250  -0.5581   0.03138   0.02106  -0.0299   1.0000   0.0657
  -6.000  -0.5370   0.02953   0.01891  -0.0284   1.0000   0.0731
  -5.750  -0.5182   0.02810   0.01741  -0.0271   1.0000   0.0840
  -5.500  -0.4987   0.02666   0.01592  -0.0255   1.0000   0.0943
  -5.250  -0.4805   0.02548   0.01469  -0.0240   1.0000   0.1095
  -5.000  -0.4627   0.02426   0.01345  -0.0222   1.0000   0.1230
  -4.750  -0.4459   0.02317   0.01240  -0.0206   1.0000   0.1444
  -4.500  -0.4299   0.02204   0.01145  -0.0191   1.0000   0.1763
  -4.250  -0.4138   0.02078   0.01050  -0.0178   1.0000   0.2325
  -4.000  -0.4016   0.01942   0.00978  -0.0159   1.0000   0.3365
  -3.750  -0.3904   0.01862   0.00972  -0.0128   1.0000   0.4807
  -3.500  -0.3778   0.01847   0.00985  -0.0092   1.0000   0.5832
  -3.250  -0.3647   0.01851   0.00993  -0.0057   1.0000   0.6519
  -3.000  -0.3521   0.01860   0.01001  -0.0020   1.0000   0.7058
  -2.750  -0.3399   0.01870   0.01008   0.0018   1.0000   0.7505
  -2.500  -0.3268   0.01874   0.01005   0.0052   1.0000   0.7891
  -2.250  -0.3113   0.01873   0.00993   0.0081   1.0000   0.8210
  -2.000  -0.2834   0.01878   0.00983   0.0083   0.9952   0.8510
  -1.750  -0.2448   0.01890   0.00980   0.0068   0.9880   0.8842
  -1.500  -0.1955   0.01910   0.00978   0.0029   0.9830   0.9160
  -1.250  -0.1420   0.01921   0.00969  -0.0024   0.9774   0.9366
  -1.000  -0.0875   0.01931   0.00960  -0.0084   0.9719   0.9527
  -0.750  -0.0350   0.01935   0.00945  -0.0141   0.9650   0.9676
  -0.500   0.0204   0.01940   0.00938  -0.0204   0.9589   0.9817
  -0.250   0.0717   0.01941   0.00929  -0.0261   0.9512   0.9982
   0.000   0.1079   0.01946   0.00927  -0.0290   0.9407   1.0000
   0.250   0.1437   0.01951   0.00928  -0.0317   0.9300   1.0000
   0.500   0.1752   0.01957   0.00932  -0.0333   0.9181   1.0000
   0.750   0.2064   0.01965   0.00938  -0.0348   0.9063   1.0000
   1.000   0.2367   0.01976   0.00947  -0.0359   0.8945   1.0000
   1.250   0.2672   0.01989   0.00960  -0.0369   0.8830   1.0000
   1.500   0.2988   0.02001   0.00976  -0.0380   0.8715   1.0000
   1.750   0.3292   0.02009   0.00987  -0.0385   0.8574   1.0000
   2.000   0.3579   0.02010   0.00991  -0.0383   0.8395   1.0000
   2.250   0.3880   0.02002   0.00991  -0.0381   0.8210   1.0000
   2.500   0.4178   0.01995   0.00989  -0.0377   0.8035   1.0000
   2.750   0.4409   0.02005   0.01006  -0.0365   0.7855   1.0000
   3.000   0.4657   0.02012   0.01021  -0.0356   0.7679   1.0000
   3.250   0.4916   0.02015   0.01037  -0.0346   0.7501   1.0000
   3.500   0.5165   0.02017   0.01050  -0.0334   0.7308   1.0000
   3.750   0.5403   0.02021   0.01065  -0.0320   0.7089   1.0000
   4.000   0.5641   0.02022   0.01077  -0.0306   0.6848   1.0000
   4.250   0.5877   0.02020   0.01086  -0.0290   0.6574   1.0000
   4.500   0.6108   0.02019   0.01098  -0.0272   0.6247   1.0000
   4.750   0.6331   0.02022   0.01107  -0.0253   0.5851   1.0000
   5.000   0.6550   0.02031   0.01113  -0.0233   0.5383   1.0000
   5.250   0.6757   0.02059   0.01128  -0.0213   0.4835   1.0000
   5.500   0.6950   0.02112   0.01157  -0.0193   0.4259   1.0000
   5.750   0.7129   0.02190   0.01216  -0.0175   0.3699   1.0000
   6.000   0.7304   0.02284   0.01289  -0.0159   0.3208   1.0000
   6.250   0.7476   0.02392   0.01378  -0.0145   0.2781   1.0000
   6.500   0.7647   0.02508   0.01482  -0.0132   0.2397   1.0000
   6.750   0.7819   0.02628   0.01596  -0.0119   0.2035   1.0000
   7.000   0.7989   0.02753   0.01712  -0.0107   0.1715   1.0000
   7.250   0.8165   0.02890   0.01850  -0.0095   0.1467   1.0000
   7.500   0.8344   0.03032   0.01993  -0.0083   0.1237   1.0000
   7.750   0.8524   0.03192   0.02151  -0.0072   0.1072   1.0000
   8.000   0.8698   0.03358   0.02314  -0.0062   0.0922   1.0000
   8.250   0.8891   0.03545   0.02516  -0.0051   0.0804   1.0000
   8.500   0.9070   0.03739   0.02733  -0.0040   0.0695   1.0000
   8.750   0.9255   0.03982   0.03000  -0.0030   0.0618   1.0000
   9.000   0.9419   0.04226   0.03259  -0.0019   0.0559   1.0000
   9.250   0.9539   0.04509   0.03579  -0.0006   0.0503   1.0000
   9.500   0.9634   0.04792   0.03897   0.0008   0.0459   1.0000
   9.750   0.9717   0.05056   0.04178   0.0019   0.0430   1.0000
  10.000   0.9715   0.05412   0.04575   0.0036   0.0409   1.0000
  10.250   0.9642   0.05775   0.04983   0.0055   0.0393   1.0000
  10.500   0.9519   0.06134   0.05374   0.0072   0.0382   1.0000
  10.750   0.9370   0.06534   0.05801   0.0079   0.0376   1.0000
  11.000   0.9192   0.06997   0.06287   0.0074   0.0375   1.0000
  11.250   0.8989   0.07542   0.06852   0.0054   0.0378   1.0000
  11.500   0.8767   0.08193   0.07519   0.0020   0.0384   1.0000
  11.750   0.8547   0.08954   0.08290  -0.0028   0.0394   1.0000
  12.000   0.8346   0.09792   0.09127  -0.0082   0.0403   1.0000
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