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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 100,000
Max Cl/Cd: 54.71 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2511-il-100000-n5.txt
Download as CSV file: xf-hq2511-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/11 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4277   0.09124   0.08619  -0.0425   1.0000   0.0209
  -9.750  -0.4305   0.08680   0.08181  -0.0444   1.0000   0.0208
  -9.500  -0.4336   0.08257   0.07764  -0.0461   1.0000   0.0206
  -9.250  -0.4411   0.07737   0.07252  -0.0487   1.0000   0.0205
  -9.000  -0.4508   0.07191   0.06714  -0.0517   1.0000   0.0202
  -8.750  -0.4681   0.06620   0.06150  -0.0550   1.0000   0.0200
  -8.500  -0.4926   0.06243   0.05778  -0.0553   1.0000   0.0198
  -8.250  -0.5136   0.05892   0.05424  -0.0543   1.0000   0.0196
  -8.000  -0.5319   0.05584   0.05109  -0.0524   1.0000   0.0194
  -7.750  -0.5483   0.05244   0.04754  -0.0502   1.0000   0.0194
  -7.500  -0.5368   0.04587   0.04048  -0.0548   0.9921   0.0192
  -7.250  -0.5177   0.03990   0.03388  -0.0586   0.9845   0.0192
  -7.000  -0.4963   0.03507   0.02838  -0.0607   0.9775   0.0195
  -6.750  -0.4690   0.03113   0.02378  -0.0625   0.9722   0.0200
  -6.500  -0.4412   0.02811   0.02016  -0.0635   0.9669   0.0211
  -6.250  -0.4116   0.02702   0.01899  -0.0649   0.9614   0.0230
  -6.000  -0.3784   0.02542   0.01709  -0.0666   0.9576   0.0255
  -5.750  -0.3502   0.02373   0.01513  -0.0669   0.9519   0.0284
  -5.500  -0.3196   0.02256   0.01388  -0.0679   0.9468   0.0323
  -5.250  -0.2860   0.02134   0.01255  -0.0694   0.9433   0.0399
  -5.000  -0.2580   0.02077   0.01189  -0.0698   0.9368   0.0509
  -4.750  -0.2268   0.02026   0.01128  -0.0709   0.9316   0.0633
  -4.500  -0.1931   0.01969   0.01065  -0.0724   0.9280   0.0762
  -4.250  -0.1680   0.01920   0.01003  -0.0720   0.9206   0.0846
  -4.000  -0.1373   0.01852   0.00936  -0.0729   0.9158   0.0951
  -3.750  -0.1083   0.01793   0.00872  -0.0734   0.9105   0.1073
  -3.500  -0.0813   0.01739   0.00822  -0.0735   0.9042   0.1287
  -3.250  -0.0507   0.01656   0.00772  -0.0746   0.9000   0.1972
  -3.000  -0.0292   0.01542   0.00745  -0.0742   0.8931   0.3896
  -2.750  -0.0038   0.01501   0.00755  -0.0735   0.8878   0.5374
  -2.500   0.0258   0.01496   0.00758  -0.0733   0.8837   0.6099
  -2.250   0.0489   0.01505   0.00768  -0.0720   0.8761   0.6563
  -2.000   0.0776   0.01505   0.00766  -0.0714   0.8710   0.6970
  -1.750   0.1004   0.01511   0.00772  -0.0698   0.8629   0.7311
  -1.500   0.1275   0.01506   0.00764  -0.0687   0.8564   0.7595
  -1.250   0.1513   0.01503   0.00755  -0.0674   0.8475   0.7802
  -1.000   0.1799   0.01493   0.00738  -0.0670   0.8415   0.7956
  -0.750   0.2046   0.01492   0.00732  -0.0662   0.8340   0.8073
  -0.500   0.2329   0.01486   0.00720  -0.0661   0.8282   0.8177
  -0.250   0.2600   0.01482   0.00712  -0.0658   0.8219   0.8286
   0.000   0.2865   0.01480   0.00706  -0.0654   0.8148   0.8403
   0.250   0.3155   0.01472   0.00695  -0.0654   0.8095   0.8520
   0.500   0.3399   0.01473   0.00697  -0.0647   0.8013   0.8646
   0.750   0.3701   0.01462   0.00684  -0.0647   0.7958   0.8777
   1.000   0.3957   0.01459   0.00684  -0.0642   0.7859   0.8934
   1.250   0.4265   0.01447   0.00674  -0.0645   0.7767   0.9112
   1.500   0.4623   0.01429   0.00654  -0.0656   0.7670   0.9312
   1.750   0.4996   0.01418   0.00646  -0.0675   0.7548   0.9578
   2.000   0.5370   0.01410   0.00639  -0.0695   0.7427   1.0000
   2.250   0.5631   0.01412   0.00637  -0.0692   0.7311   1.0000
   2.500   0.5902   0.01414   0.00635  -0.0691   0.7193   1.0000
   2.750   0.6175   0.01417   0.00636  -0.0689   0.7071   1.0000
   3.000   0.6439   0.01423   0.00642  -0.0686   0.6937   1.0000
   3.250   0.6701   0.01431   0.00650  -0.0682   0.6795   1.0000
   3.500   0.6964   0.01438   0.00656  -0.0678   0.6637   1.0000
   3.750   0.7213   0.01448   0.00670  -0.0671   0.6436   1.0000
   4.000   0.7467   0.01455   0.00674  -0.0664   0.6209   1.0000
   4.250   0.7709   0.01468   0.00683  -0.0656   0.5935   1.0000
   4.500   0.7950   0.01484   0.00694  -0.0647   0.5629   1.0000
   4.750   0.8185   0.01506   0.00708  -0.0638   0.5284   1.0000
   5.000   0.8414   0.01538   0.00725  -0.0627   0.4927   1.0000
   5.250   0.8635   0.01581   0.00752  -0.0616   0.4586   1.0000
   5.500   0.8850   0.01631   0.00791  -0.0606   0.4257   1.0000
   5.750   0.9061   0.01684   0.00835  -0.0595   0.3923   1.0000
   6.000   0.9265   0.01740   0.00883  -0.0584   0.3576   1.0000
   6.250   0.9463   0.01803   0.00933  -0.0572   0.3268   1.0000
   6.500   0.9656   0.01871   0.00993  -0.0560   0.3009   1.0000
   6.750   0.9852   0.01940   0.01057  -0.0549   0.2777   1.0000
   7.000   1.0046   0.02011   0.01125  -0.0537   0.2569   1.0000
   7.250   1.0242   0.02081   0.01196  -0.0526   0.2387   1.0000
   7.500   1.0437   0.02151   0.01273  -0.0515   0.2219   1.0000
   7.750   1.0618   0.02226   0.01347  -0.0503   0.2029   1.0000
   8.000   1.0783   0.02305   0.01419  -0.0489   0.1813   1.0000
   8.250   1.0948   0.02383   0.01494  -0.0476   0.1600   1.0000
   8.500   1.1105   0.02466   0.01576  -0.0462   0.1431   1.0000
   8.750   1.1262   0.02551   0.01664  -0.0448   0.1239   1.0000
   9.000   1.1398   0.02645   0.01755  -0.0432   0.1036   1.0000
   9.250   1.1519   0.02751   0.01857  -0.0413   0.0784   1.0000
   9.500   1.1597   0.02898   0.01986  -0.0391   0.0506   1.0000
   9.750   1.1659   0.03060   0.02140  -0.0367   0.0394   1.0000
  10.250   1.1766   0.03396   0.02490  -0.0323   0.0320   1.0000
  10.500   1.1812   0.03570   0.02679  -0.0303   0.0296   1.0000
  10.750   1.1833   0.03769   0.02892  -0.0284   0.0277   1.0000
  11.000   1.1820   0.04002   0.03134  -0.0266   0.0263   1.0000
  11.250   1.1849   0.04210   0.03363  -0.0251   0.0252   1.0000
  11.500   1.1861   0.04442   0.03614  -0.0238   0.0245   1.0000
  11.750   1.1869   0.04688   0.03877  -0.0227   0.0238   1.0000
  12.000   1.1871   0.04953   0.04158  -0.0218   0.0232   1.0000
  12.250   1.1871   0.05231   0.04453  -0.0211   0.0226   1.0000
  12.500   1.1868   0.05523   0.04760  -0.0205   0.0221   1.0000
  12.750   1.1860   0.05832   0.05084  -0.0202   0.0216   1.0000
  13.000   1.1846   0.06157   0.05423  -0.0202   0.0211   1.0000
  13.250   1.1816   0.06510   0.05787  -0.0204   0.0205   1.0000
  13.500   1.1786   0.06892   0.06180  -0.0205   0.0199   1.0000
  13.750   1.1743   0.07294   0.06605  -0.0212   0.0195   1.0000
  14.000   1.1682   0.07732   0.07068  -0.0224   0.0192   1.0000
  14.250   1.1601   0.08220   0.07580  -0.0242   0.0189   1.0000
  14.500   1.1510   0.08749   0.08133  -0.0263   0.0187   1.0000
  14.750   1.1408   0.09324   0.08730  -0.0289   0.0185   1.0000
  15.000   1.1287   0.09964   0.09392  -0.0321   0.0185   1.0000
  15.250   1.1150   0.10667   0.10118  -0.0360   0.0184   1.0000
  15.500   1.1004   0.11427   0.10897  -0.0404   0.0185   1.0000
  15.750   1.0843   0.12263   0.11752  -0.0456   0.0185   1.0000
  16.000   1.0669   0.13180   0.12687  -0.0514   0.0187   1.0000
  16.250   1.0480   0.14190   0.13709  -0.0578   0.0188   1.0000
  16.500   1.0285   0.15282   0.14814  -0.0647   0.0191   1.0000
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