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HQ 2.5/9 B AIRFOIL (hq259b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/9 B AIRFOIL (hq259b-il)
Reynolds number: 500,000
Max Cl/Cd: 84.56 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq259b-il-500000-n5.txt
Download as CSV file: xf-hq259b-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/9 B AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4920   0.07286   0.07063  -0.0414   1.0000   0.0086
  -8.750  -0.5650   0.04192   0.03932  -0.0683   0.9875   0.0085
  -8.500  -0.5523   0.03297   0.02986  -0.0742   0.9800   0.0089
  -8.250  -0.5315   0.02760   0.02401  -0.0773   0.9736   0.0094
  -8.000  -0.5066   0.02305   0.01887  -0.0798   0.9686   0.0102
  -7.750  -0.4812   0.02038   0.01573  -0.0808   0.9617   0.0112
  -7.500  -0.4514   0.01862   0.01361  -0.0821   0.9567   0.0118
  -7.250  -0.4238   0.01733   0.01215  -0.0829   0.9499   0.0124
  -7.000  -0.3941   0.01661   0.01132  -0.0837   0.9435   0.0128
  -6.750  -0.3657   0.01588   0.01046  -0.0842   0.9366   0.0134
  -6.500  -0.3377   0.01514   0.00957  -0.0845   0.9292   0.0142
  -6.250  -0.3102   0.01452   0.00880  -0.0846   0.9216   0.0150
  -6.000  -0.2828   0.01393   0.00806  -0.0846   0.9139   0.0156
  -5.750  -0.2566   0.01311   0.00710  -0.0844   0.9059   0.0161
  -5.500  -0.2304   0.01232   0.00622  -0.0843   0.8981   0.0168
  -5.250  -0.2039   0.01187   0.00571  -0.0842   0.8902   0.0175
  -4.750  -0.1500   0.01115   0.00487  -0.0839   0.8760   0.0194
  -4.500  -0.1231   0.01075   0.00438  -0.0838   0.8695   0.0201
  -4.250  -0.0960   0.01040   0.00396  -0.0836   0.8631   0.0207
  -4.000  -0.0687   0.01011   0.00358  -0.0835   0.8569   0.0212
  -3.750  -0.0416   0.00968   0.00310  -0.0835   0.8511   0.0226
  -3.500  -0.0142   0.00943   0.00283  -0.0834   0.8449   0.0245
  -3.250   0.0134   0.00924   0.00258  -0.0834   0.8395   0.0265
  -3.000   0.0410   0.00905   0.00234  -0.0833   0.8322   0.0284
  -2.750   0.0683   0.00885   0.00210  -0.0831   0.8232   0.0334
  -2.500   0.0956   0.00870   0.00192  -0.0829   0.8129   0.0414
  -2.250   0.1231   0.00853   0.00177  -0.0828   0.8046   0.0570
  -2.000   0.1505   0.00832   0.00164  -0.0828   0.7969   0.0881
  -1.750   0.1779   0.00803   0.00152  -0.0828   0.7895   0.1495
  -1.500   0.2043   0.00732   0.00135  -0.0831   0.7819   0.3315
  -1.250   0.2305   0.00676   0.00134  -0.0831   0.7740   0.5117
  -0.750   0.2846   0.00653   0.00137  -0.0826   0.7576   0.6233
  -0.500   0.3118   0.00650   0.00139  -0.0823   0.7498   0.6590
  -0.250   0.3391   0.00647   0.00142  -0.0821   0.7422   0.6900
   0.000   0.3667   0.00648   0.00142  -0.0819   0.7350   0.7024
   0.250   0.3946   0.00650   0.00142  -0.0818   0.7268   0.7114
   0.500   0.4222   0.00651   0.00143  -0.0817   0.7181   0.7206
   0.750   0.4497   0.00654   0.00145  -0.0815   0.7085   0.7296
   1.250   0.5044   0.00659   0.00151  -0.0811   0.6839   0.7488
   1.500   0.5313   0.00664   0.00155  -0.0808   0.6670   0.7594
   1.750   0.5577   0.00671   0.00159  -0.0804   0.6418   0.7707
   2.250   0.6043   0.00731   0.00176  -0.0785   0.5213   0.7967
   2.500   0.6260   0.00782   0.00200  -0.0773   0.4523   0.8122
   2.750   0.6486   0.00824   0.00221  -0.0764   0.3990   0.8288
   3.000   0.6725   0.00853   0.00239  -0.0757   0.3638   0.8468
   3.250   0.6969   0.00871   0.00255  -0.0750   0.3423   0.8674
   3.500   0.7209   0.00886   0.00270  -0.0742   0.3225   0.8915
   3.750   0.7454   0.00897   0.00284  -0.0734   0.3046   0.9291
   4.000   0.7771   0.00919   0.00301  -0.0744   0.2840   1.0000
   4.250   0.8026   0.00951   0.00322  -0.0741   0.2575   1.0000
   4.500   0.8277   0.00986   0.00344  -0.0738   0.2266   1.0000
   4.750   0.8514   0.01036   0.00373  -0.0733   0.1829   1.0000
   5.000   0.8746   0.01093   0.00408  -0.0727   0.1411   1.0000
   5.250   0.8984   0.01144   0.00445  -0.0721   0.1110   1.0000
   5.750   0.9472   0.01229   0.00514  -0.0712   0.0777   1.0000
   6.250   0.9962   0.01307   0.00587  -0.0703   0.0576   1.0000
   6.500   1.0207   0.01346   0.00625  -0.0699   0.0502   1.0000
   6.750   1.0446   0.01390   0.00666  -0.0693   0.0418   1.0000
   7.000   1.0684   0.01434   0.00708  -0.0688   0.0345   1.0000
   7.250   1.0918   0.01481   0.00756  -0.0682   0.0295   1.0000
   7.500   1.1148   0.01532   0.00807  -0.0675   0.0259   1.0000
   7.750   1.1376   0.01584   0.00862  -0.0668   0.0237   1.0000
   8.000   1.1605   0.01631   0.00916  -0.0661   0.0224   1.0000
   8.250   1.1828   0.01683   0.00972  -0.0654   0.0209   1.0000
   8.500   1.2042   0.01743   0.01037  -0.0645   0.0194   1.0000
   8.750   1.2240   0.01819   0.01119  -0.0634   0.0180   1.0000
   9.000   1.2456   0.01870   0.01177  -0.0625   0.0173   1.0000
   9.250   1.2662   0.01929   0.01244  -0.0616   0.0164   1.0000
   9.500   1.2862   0.01990   0.01312  -0.0605   0.0155   1.0000
   9.750   1.3054   0.02056   0.01385  -0.0594   0.0146   1.0000
  10.000   1.3214   0.02148   0.01482  -0.0579   0.0134   1.0000
  10.250   1.3393   0.02217   0.01560  -0.0566   0.0128   1.0000
  10.500   1.3565   0.02286   0.01640  -0.0552   0.0122   1.0000
  10.750   1.3713   0.02360   0.01723  -0.0534   0.0115   1.0000
  11.000   1.3850   0.02434   0.01804  -0.0515   0.0108   1.0000
  11.250   1.3977   0.02512   0.01889  -0.0496   0.0102   1.0000
  11.500   1.4067   0.02617   0.02001  -0.0472   0.0097   1.0000
  11.750   1.4175   0.02711   0.02107  -0.0452   0.0092   1.0000
  12.000   1.4273   0.02814   0.02222  -0.0432   0.0088   1.0000
  12.250   1.4374   0.02917   0.02335  -0.0414   0.0082   1.0000
  12.500   1.4459   0.03035   0.02463  -0.0396   0.0078   1.0000
  12.750   1.4541   0.03159   0.02596  -0.0380   0.0075   1.0000
  13.000   1.4602   0.03305   0.02752  -0.0363   0.0072   1.0000
  13.250   1.4628   0.03488   0.02945  -0.0346   0.0069   1.0000
  13.500   1.4639   0.03694   0.03164  -0.0330   0.0067   1.0000
  13.750   1.4650   0.03909   0.03394  -0.0317   0.0065   1.0000
  14.000   1.4654   0.04143   0.03644  -0.0307   0.0063   1.0000
  14.250   1.4641   0.04405   0.03921  -0.0299   0.0061   1.0000
  14.500   1.4613   0.04700   0.04232  -0.0294   0.0060   1.0000
  14.750   1.4569   0.05029   0.04577  -0.0293   0.0058   1.0000
  15.000   1.4505   0.05403   0.04967  -0.0297   0.0057   1.0000
  15.250   1.4438   0.05809   0.05388  -0.0305   0.0056   1.0000
  15.500   1.4335   0.06296   0.05891  -0.0320   0.0055   1.0000
  15.750   1.4234   0.06823   0.06434  -0.0342   0.0054   1.0000
  16.000   1.4103   0.07449   0.07078  -0.0372   0.0054   1.0000
  16.250   1.3944   0.08170   0.07816  -0.0410   0.0054   1.0000
  16.500   1.3777   0.08945   0.08608  -0.0453   0.0053   1.0000
  16.750   1.3570   0.09821   0.09502  -0.0503   0.0053   1.0000
  17.000   1.3355   0.10738   0.10435  -0.0555   0.0054   1.0000
  17.250   1.3118   0.11724   0.11438  -0.0613   0.0054   1.0000
  17.500   1.2880   0.12739   0.12468  -0.0672   0.0054   1.0000
  17.750   1.2640   0.13807   0.13551  -0.0736   0.0055   1.0000
  18.000   1.2391   0.14939   0.14696  -0.0805   0.0055   1.0000
  18.250   1.2134   0.16141   0.15913  -0.0878   0.0056   1.0000
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