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HQ 2.5/10 AIRFOIL (hq2510-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/10 AIRFOIL (hq2510-il)
Reynolds number: 200,000
Max Cl/Cd: 79.06 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2510-il-200000.txt
Download as CSV file: xf-hq2510-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/10 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3948   0.08891   0.08552  -0.0372   1.0000   0.0436
  -8.500  -0.3984   0.08520   0.08187  -0.0389   1.0000   0.0450
  -8.250  -0.4049   0.08156   0.07831  -0.0409   1.0000   0.0461
  -8.000  -0.4193   0.07789   0.07474  -0.0431   1.0000   0.0468
  -7.750  -0.4384   0.07428   0.07124  -0.0448   1.0000   0.0470
  -7.500  -0.4562   0.07136   0.06832  -0.0447   1.0000   0.0471
  -6.750  -0.4338   0.04646   0.04341  -0.0498   0.9905   0.0500
  -6.500  -0.4136   0.04196   0.03888  -0.0525   0.9861   0.0516
  -6.250  -0.3902   0.03682   0.03358  -0.0570   0.9823   0.0540
  -6.000  -0.3715   0.03209   0.02852  -0.0604   0.9754   0.0580
  -5.750  -0.3861   0.04533   0.04067  -0.0599   0.9793   0.0614
  -5.500  -0.3646   0.03156   0.02637  -0.0615   0.9751   0.0322
  -5.250  -0.3316   0.02530   0.01914  -0.0630   0.9716   0.0280
  -5.000  -0.2943   0.02272   0.01614  -0.0651   0.9690   0.0290
  -4.750  -0.2647   0.02159   0.01477  -0.0657   0.9628   0.0325
  -4.500  -0.2286   0.01986   0.01269  -0.0669   0.9591   0.0350
  -4.250  -0.1923   0.01766   0.01032  -0.0685   0.9565   0.0387
  -4.000  -0.1594   0.01695   0.00953  -0.0695   0.9515   0.0489
  -3.750  -0.1274   0.01563   0.00827  -0.0706   0.9465   0.0653
  -3.500  -0.0885   0.01505   0.00765  -0.0731   0.9434   0.0866
  -3.250  -0.0480   0.01418   0.00687  -0.0759   0.9412   0.1106
  -3.000  -0.0223   0.01338   0.00631  -0.0758   0.9333   0.1587
  -2.750   0.0064   0.01156   0.00611  -0.0770   0.9295   0.5521
  -2.500   0.0354   0.01148   0.00619  -0.0768   0.9237   0.6422
  -2.250   0.0660   0.01145   0.00615  -0.0768   0.9179   0.6855
  -2.000   0.1010   0.01139   0.00607  -0.0777   0.9143   0.7194
  -1.750   0.1257   0.01143   0.00609  -0.0766   0.9061   0.7452
  -1.500   0.1569   0.01134   0.00599  -0.0766   0.9013   0.7709
  -1.250   0.1796   0.01135   0.00604  -0.0748   0.8933   0.7998
  -1.000   0.2064   0.01122   0.00593  -0.0737   0.8876   0.8244
  -0.750   0.2299   0.01116   0.00586  -0.0724   0.8794   0.8437
  -0.500   0.2577   0.01098   0.00565  -0.0718   0.8735   0.8590
  -0.250   0.2819   0.01090   0.00557  -0.0708   0.8652   0.8730
   0.000   0.3101   0.01073   0.00537  -0.0704   0.8592   0.8871
   0.250   0.3344   0.01061   0.00527  -0.0693   0.8497   0.9033
   0.500   0.3636   0.01040   0.00504  -0.0690   0.8406   0.9206
   0.750   0.3978   0.01018   0.00478  -0.0697   0.8312   0.9404
   1.000   0.4377   0.01007   0.00467  -0.0721   0.8212   0.9615
   1.250   0.4819   0.00995   0.00453  -0.0755   0.8127   0.9850
   1.500   0.5152   0.00988   0.00440  -0.0769   0.8033   1.0000
   1.750   0.5393   0.00990   0.00438  -0.0764   0.7917   1.0000
   2.000   0.5655   0.00992   0.00434  -0.0761   0.7801   1.0000
   2.250   0.5923   0.00992   0.00433  -0.0758   0.7681   1.0000
   2.500   0.6191   0.00994   0.00430  -0.0754   0.7557   1.0000
   2.750   0.6458   0.00996   0.00429  -0.0751   0.7425   1.0000
   3.000   0.6722   0.00999   0.00430  -0.0746   0.7281   1.0000
   3.250   0.6983   0.01003   0.00434  -0.0741   0.7120   1.0000
   3.500   0.7244   0.01007   0.00435  -0.0735   0.6944   1.0000
   3.750   0.7501   0.01014   0.00439  -0.0728   0.6750   1.0000
   4.000   0.7755   0.01023   0.00446  -0.0721   0.6531   1.0000
   4.250   0.8004   0.01035   0.00458  -0.0714   0.6283   1.0000
   4.500   0.8248   0.01051   0.00469  -0.0705   0.5992   1.0000
   4.750   0.8483   0.01073   0.00482  -0.0695   0.5640   1.0000
   5.000   0.8704   0.01106   0.00500  -0.0683   0.5195   1.0000
   5.250   0.8910   0.01155   0.00526  -0.0670   0.4699   1.0000
   5.500   0.9109   0.01213   0.00565  -0.0656   0.4194   1.0000
   5.750   0.9304   0.01278   0.00609  -0.0642   0.3740   1.0000
   6.000   0.9506   0.01342   0.00657  -0.0630   0.3352   1.0000
   6.250   0.9704   0.01411   0.00711  -0.0618   0.3032   1.0000
   6.500   0.9906   0.01479   0.00768  -0.0607   0.2741   1.0000
   6.750   1.0107   0.01544   0.00824  -0.0596   0.2445   1.0000
   7.000   1.0308   0.01605   0.00880  -0.0586   0.2139   1.0000
   7.250   1.0508   0.01667   0.00934  -0.0576   0.1867   1.0000
   7.500   1.0705   0.01731   0.00990  -0.0565   0.1592   1.0000
   7.750   1.0898   0.01800   0.01047  -0.0555   0.1299   1.0000
   8.000   1.1080   0.01882   0.01114  -0.0543   0.0981   1.0000
   8.250   1.1141   0.02098   0.01269  -0.0514   0.0304   1.0000
   8.500   1.1271   0.02237   0.01415  -0.0491   0.0230   1.0000
   8.750   1.1354   0.02401   0.01594  -0.0463   0.0201   1.0000
   9.000   1.1457   0.02530   0.01742  -0.0438   0.0188   1.0000
   9.250   1.1555   0.02652   0.01876  -0.0413   0.0174   1.0000
   9.500   1.1646   0.02779   0.02013  -0.0389   0.0161   1.0000
   9.750   1.1719   0.02925   0.02168  -0.0364   0.0149   1.0000
  10.000   1.1770   0.03109   0.02363  -0.0339   0.0144   1.0000
  10.250   1.1834   0.03311   0.02577  -0.0316   0.0140   1.0000
  10.500   1.1903   0.03571   0.02850  -0.0296   0.0136   1.0000
  10.750   1.2004   0.03834   0.03132  -0.0280   0.0134   1.0000
  11.000   1.2094   0.04124   0.03445  -0.0264   0.0133   1.0000
  11.250   1.2147   0.04438   0.03784  -0.0247   0.0133   1.0000
  11.500   1.2180   0.04691   0.04061  -0.0230   0.0133   1.0000
  11.750   1.2154   0.05022   0.04418  -0.0212   0.0134   1.0000
  12.000   1.2121   0.05316   0.04737  -0.0197   0.0135   1.0000
  12.250   1.2061   0.05639   0.05084  -0.0186   0.0135   1.0000
  12.500   1.1988   0.05972   0.05442  -0.0178   0.0137   1.0000
  12.750   1.1877   0.06372   0.05869  -0.0177   0.0139   1.0000
  13.000   1.1727   0.06849   0.06374  -0.0183   0.0141   1.0000
  13.250   1.1545   0.07409   0.06963  -0.0198   0.0144   1.0000
  13.500   1.1345   0.08041   0.07621  -0.0223   0.0145   1.0000
  13.750   1.1127   0.08771   0.08376  -0.0260   0.0149   1.0000
  14.000   1.0905   0.09580   0.09207  -0.0309   0.0151   1.0000
  14.250   1.0663   0.10527   0.10175  -0.0372   0.0152   1.0000
  14.500   1.0396   0.11657   0.11325  -0.0450   0.0155   1.0000
  14.750   1.0088   0.13060   0.12743  -0.0544   0.0158   1.0000
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