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HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il)
Reynolds number: 200,000
Max Cl/Cd: 70.57 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2512-il-200000-n5.txt
Download as CSV file: xf-hq2512-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4650   0.08870   0.08516  -0.0450   1.0000   0.0138
 -10.750  -0.4860   0.08001   0.07653  -0.0492   1.0000   0.0137
 -10.250  -0.5735   0.05314   0.04955  -0.0673   1.0000   0.0128
 -10.000  -0.6087   0.04811   0.04441  -0.0682   1.0000   0.0121
  -9.750  -0.6380   0.04561   0.04183  -0.0648   1.0000   0.0121
  -9.500  -0.6541   0.04074   0.03659  -0.0651   0.9944   0.0123
  -9.250  -0.6439   0.03515   0.03036  -0.0688   0.9847   0.0129
  -9.000  -0.6275   0.03093   0.02555  -0.0706   0.9765   0.0133
  -8.750  -0.6025   0.02778   0.02189  -0.0726   0.9716   0.0138
  -8.500  -0.5795   0.02543   0.01920  -0.0733   0.9644   0.0144
  -8.250  -0.5510   0.02397   0.01758  -0.0747   0.9592   0.0153
  -8.000  -0.5230   0.02282   0.01628  -0.0756   0.9533   0.0162
  -7.750  -0.4945   0.02190   0.01516  -0.0764   0.9470   0.0180
  -7.500  -0.4641   0.02065   0.01367  -0.0775   0.9425   0.0196
  -7.250  -0.4394   0.01965   0.01262  -0.0775   0.9344   0.0212
  -7.000  -0.4095   0.01881   0.01166  -0.0783   0.9293   0.0234
  -6.750  -0.3835   0.01801   0.01070  -0.0782   0.9218   0.0262
  -6.500  -0.3554   0.01726   0.00992  -0.0787   0.9160   0.0301
  -6.250  -0.3279   0.01684   0.00937  -0.0788   0.9092   0.0351
  -6.000  -0.3012   0.01619   0.00867  -0.0789   0.9029   0.0395
  -5.750  -0.2736   0.01585   0.00825  -0.0790   0.8965   0.0451
  -5.500  -0.2478   0.01535   0.00771  -0.0788   0.8895   0.0505
  -5.250  -0.2209   0.01496   0.00725  -0.0787   0.8834   0.0559
  -5.000  -0.1951   0.01459   0.00676  -0.0784   0.8762   0.0606
  -4.750  -0.1688   0.01408   0.00624  -0.0783   0.8705   0.0668
  -4.500  -0.1431   0.01377   0.00585  -0.0779   0.8631   0.0740
  -4.250  -0.1165   0.01335   0.00542  -0.0778   0.8575   0.0838
  -4.000  -0.0909   0.01301   0.00507  -0.0775   0.8503   0.0975
  -3.750  -0.0646   0.01263   0.00473  -0.0773   0.8444   0.1213
  -3.500  -0.0392   0.01219   0.00446  -0.0771   0.8379   0.1695
  -3.250  -0.0142   0.01166   0.00419  -0.0769   0.8314   0.2463
  -3.000   0.0095   0.01097   0.00396  -0.0766   0.8253   0.3701
  -2.750   0.0334   0.01056   0.00393  -0.0759   0.8184   0.4810
  -2.500   0.0598   0.01042   0.00391  -0.0755   0.8130   0.5408
  -2.250   0.0859   0.01038   0.00392  -0.0750   0.8058   0.5788
  -2.000   0.1131   0.01036   0.00388  -0.0746   0.8000   0.6099
  -1.750   0.1392   0.01038   0.00393  -0.0740   0.7929   0.6401
  -1.500   0.1659   0.01040   0.00394  -0.0735   0.7865   0.6645
  -1.250   0.1927   0.01041   0.00392  -0.0731   0.7794   0.6797
  -1.000   0.2199   0.01041   0.00389  -0.0727   0.7727   0.6928
  -0.750   0.2467   0.01043   0.00389  -0.0723   0.7656   0.7059
  -0.500   0.2738   0.01044   0.00386  -0.0720   0.7589   0.7173
  -0.250   0.3014   0.01045   0.00383  -0.0719   0.7523   0.7267
   0.000   0.3285   0.01044   0.00381  -0.0716   0.7447   0.7334
   0.250   0.3558   0.01045   0.00377  -0.0714   0.7358   0.7414
   0.500   0.3828   0.01043   0.00371  -0.0710   0.7261   0.7483
   0.750   0.4096   0.01043   0.00367  -0.0706   0.7143   0.7564
   1.000   0.4359   0.01042   0.00367  -0.0702   0.7027   0.7638
   1.250   0.4628   0.01044   0.00366  -0.0699   0.6924   0.7720
   1.500   0.4896   0.01046   0.00366  -0.0695   0.6833   0.7801
   1.750   0.5160   0.01048   0.00370  -0.0691   0.6728   0.7884
   2.000   0.5425   0.01051   0.00374  -0.0688   0.6624   0.7976
   2.250   0.5686   0.01053   0.00378  -0.0683   0.6511   0.8063
   2.500   0.5948   0.01056   0.00381  -0.0679   0.6389   0.8161
   2.750   0.6206   0.01061   0.00387  -0.0674   0.6252   0.8267
   3.000   0.6458   0.01064   0.00393  -0.0667   0.6105   0.8380
   3.250   0.6709   0.01069   0.00400  -0.0660   0.5940   0.8508
   3.500   0.6959   0.01074   0.00407  -0.0654   0.5757   0.8660
   4.000   0.7481   0.01092   0.00426  -0.0645   0.5293   0.9133
   4.250   0.7840   0.01111   0.00437  -0.0663   0.4959   0.9995
   4.500   0.8070   0.01144   0.00457  -0.0656   0.4636   1.0000
   4.750   0.8293   0.01183   0.00480  -0.0647   0.4314   1.0000
   5.000   0.8512   0.01225   0.00508  -0.0638   0.4001   1.0000
   5.250   0.8726   0.01271   0.00539  -0.0629   0.3695   1.0000
   5.500   0.8939   0.01317   0.00575  -0.0620   0.3408   1.0000
   5.750   0.9151   0.01365   0.00612  -0.0610   0.3154   1.0000
   6.000   0.9359   0.01415   0.00651  -0.0600   0.2930   1.0000
   6.250   0.9569   0.01463   0.00693  -0.0591   0.2739   1.0000
   6.500   0.9778   0.01513   0.00736  -0.0581   0.2565   1.0000
   6.750   0.9989   0.01560   0.00782  -0.0572   0.2416   1.0000
   7.000   1.0202   0.01605   0.00827  -0.0563   0.2285   1.0000
   7.250   1.0412   0.01650   0.00874  -0.0553   0.2162   1.0000
   7.500   1.0615   0.01698   0.00922  -0.0543   0.2034   1.0000
   7.750   1.0811   0.01749   0.00972  -0.0532   0.1896   1.0000
   8.000   1.0996   0.01805   0.01027  -0.0520   0.1732   1.0000
   8.250   1.1171   0.01865   0.01082  -0.0506   0.1569   1.0000
   8.500   1.1330   0.01930   0.01142  -0.0490   0.1407   1.0000
   8.750   1.1487   0.01990   0.01201  -0.0473   0.1283   1.0000
   9.000   1.1634   0.02057   0.01267  -0.0455   0.1158   1.0000
   9.250   1.1781   0.02125   0.01336  -0.0438   0.1051   1.0000
   9.500   1.1921   0.02198   0.01411  -0.0421   0.0955   1.0000
   9.750   1.2043   0.02285   0.01496  -0.0402   0.0806   1.0000
  10.000   1.2143   0.02391   0.01590  -0.0383   0.0640   1.0000
  10.250   1.2243   0.02500   0.01693  -0.0364   0.0511   1.0000
  10.500   1.2336   0.02616   0.01806  -0.0346   0.0371   1.0000
  10.750   1.2384   0.02772   0.01952  -0.0324   0.0221   1.0000
  11.000   1.2425   0.02937   0.02115  -0.0304   0.0142   1.0000
  11.250   1.2476   0.03101   0.02283  -0.0285   0.0116   1.0000
  11.500   1.2545   0.03252   0.02448  -0.0269   0.0104   1.0000
  11.750   1.2604   0.03417   0.02625  -0.0255   0.0095   1.0000
  12.000   1.2648   0.03599   0.02824  -0.0241   0.0089   1.0000
  12.250   1.2666   0.03812   0.03051  -0.0227   0.0084   1.0000
  12.500   1.2674   0.04041   0.03295  -0.0216   0.0081   1.0000
  12.750   1.2690   0.04270   0.03540  -0.0207   0.0079   1.0000
  13.000   1.2696   0.04517   0.03802  -0.0200   0.0077   1.0000
  13.250   1.2696   0.04781   0.04082  -0.0196   0.0073   1.0000
  13.500   1.2678   0.05074   0.04392  -0.0193   0.0070   1.0000
  13.750   1.2653   0.05389   0.04721  -0.0194   0.0067   1.0000
  14.000   1.2619   0.05728   0.05075  -0.0197   0.0064   1.0000
  14.250   1.2557   0.06121   0.05484  -0.0204   0.0063   1.0000
  14.500   1.2488   0.06546   0.05925  -0.0214   0.0062   1.0000
  14.750   1.2411   0.07007   0.06402  -0.0229   0.0061   1.0000
  15.000   1.2308   0.07532   0.06944  -0.0248   0.0061   1.0000
  15.250   1.2211   0.08075   0.07502  -0.0270   0.0060   1.0000
  15.500   1.2072   0.08717   0.08160  -0.0300   0.0058   1.0000
  15.750   1.1968   0.09321   0.08780  -0.0328   0.0058   1.0000
  16.000   1.1845   0.09983   0.09458  -0.0361   0.0058   1.0000
  16.250   1.1711   0.10685   0.10176  -0.0397   0.0058   1.0000
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