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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 1,000,000
Max Cl/Cd: 107.54 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2511-il-1000000.txt
Download as CSV file: xf-hq2511-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4240   0.08987   0.08828  -0.0390   1.0000   0.0138
  -9.750  -0.4258   0.08550   0.08393  -0.0410   1.0000   0.0140
  -9.250  -0.6086   0.02848   0.02557  -0.0791   0.9836   0.0094
  -9.000  -0.5832   0.02652   0.02335  -0.0807   0.9773   0.0092
  -8.750  -0.5639   0.02153   0.01789  -0.0829   0.9707   0.0087
  -8.500  -0.5432   0.01925   0.01529  -0.0829   0.9607   0.0086
  -8.250  -0.5216   0.01755   0.01333  -0.0826   0.9512   0.0085
  -8.000  -0.4996   0.01622   0.01179  -0.0819   0.9419   0.0085
  -7.750  -0.4782   0.01504   0.01043  -0.0810   0.9314   0.0084
  -7.500  -0.4554   0.01406   0.00929  -0.0803   0.9221   0.0083
  -7.000  -0.4076   0.01257   0.00753  -0.0792   0.9036   0.0084
  -6.750  -0.3829   0.01198   0.00684  -0.0787   0.8952   0.0086
  -6.500  -0.3581   0.01138   0.00612  -0.0782   0.8866   0.0086
  -6.250  -0.3327   0.01084   0.00547  -0.0778   0.8785   0.0085
  -6.000  -0.3071   0.01041   0.00492  -0.0774   0.8706   0.0084
  -5.750  -0.2809   0.00998   0.00442  -0.0771   0.8629   0.0085
  -5.500  -0.2544   0.00966   0.00400  -0.0768   0.8558   0.0085
  -5.250  -0.2275   0.00934   0.00362  -0.0767   0.8490   0.0086
  -5.000  -0.2005   0.00908   0.00328  -0.0765   0.8426   0.0087
  -4.750  -0.1731   0.00885   0.00299  -0.0764   0.8364   0.0088
  -4.500  -0.1457   0.00864   0.00273  -0.0763   0.8297   0.0091
  -4.250  -0.1181   0.00846   0.00249  -0.0761   0.8234   0.0102
  -4.000  -0.0908   0.00817   0.00225  -0.0761   0.8167   0.0203
  -3.750  -0.0635   0.00797   0.00208  -0.0760   0.8107   0.0341
  -3.500  -0.0356   0.00780   0.00195  -0.0760   0.8043   0.0433
  -3.250  -0.0079   0.00768   0.00183  -0.0760   0.7979   0.0526
  -3.000   0.0201   0.00754   0.00172  -0.0760   0.7915   0.0643
  -2.750   0.0478   0.00738   0.00160  -0.0760   0.7846   0.0830
  -2.500   0.0750   0.00710   0.00146  -0.0761   0.7776   0.1278
  -2.250   0.1017   0.00668   0.00132  -0.0761   0.7699   0.2212
  -2.000   0.1276   0.00606   0.00117  -0.0761   0.7627   0.3697
  -1.750   0.1542   0.00568   0.00110  -0.0761   0.7555   0.4772
  -1.500   0.1815   0.00548   0.00108  -0.0760   0.7489   0.5465
  -1.250   0.2091   0.00538   0.00109  -0.0760   0.7421   0.5982
  -1.000   0.2371   0.00537   0.00109  -0.0759   0.7353   0.6212
  -0.750   0.2651   0.00536   0.00109  -0.0759   0.7269   0.6401
  -0.500   0.2932   0.00538   0.00110  -0.0759   0.7190   0.6551
  -0.250   0.3212   0.00539   0.00111  -0.0758   0.7111   0.6709
   0.000   0.3492   0.00541   0.00114  -0.0758   0.7036   0.6867
   0.250   0.3773   0.00544   0.00115  -0.0757   0.6957   0.6964
   0.500   0.4056   0.00547   0.00117  -0.0758   0.6878   0.7049
   0.750   0.4334   0.00549   0.00119  -0.0757   0.6797   0.7121
   1.000   0.4617   0.00552   0.00121  -0.0758   0.6716   0.7195
   1.250   0.4894   0.00556   0.00123  -0.0757   0.6610   0.7262
   1.500   0.5170   0.00562   0.00126  -0.0756   0.6463   0.7335
   1.750   0.5442   0.00568   0.00130  -0.0754   0.6282   0.7407
   2.000   0.5715   0.00576   0.00134  -0.0753   0.6100   0.7484
   2.250   0.5985   0.00585   0.00139  -0.0751   0.5914   0.7549
   2.500   0.6252   0.00597   0.00145  -0.0749   0.5658   0.7621
   2.750   0.6510   0.00616   0.00155  -0.0745   0.5323   0.7695
   3.000   0.6765   0.00639   0.00166  -0.0741   0.4972   0.7779
   3.250   0.7017   0.00664   0.00180  -0.0737   0.4651   0.7864
   3.500   0.7272   0.00687   0.00196  -0.0733   0.4395   0.7960
   3.750   0.7529   0.00706   0.00211  -0.0729   0.4175   0.8070
   4.000   0.7786   0.00724   0.00226  -0.0726   0.3941   0.8196
   4.250   0.8031   0.00748   0.00242  -0.0720   0.3588   0.8357
   4.500   0.8259   0.00780   0.00264  -0.0712   0.3184   0.8579
   4.750   0.8474   0.00799   0.00285  -0.0699   0.2924   0.8981
   5.000   0.8789   0.00819   0.00307  -0.0709   0.2670   1.0000
   5.250   0.9036   0.00854   0.00330  -0.0705   0.2404   1.0000
   5.500   0.9280   0.00891   0.00353  -0.0701   0.2127   1.0000
   5.750   0.9526   0.00924   0.00377  -0.0697   0.1904   1.0000
   6.000   0.9767   0.00962   0.00404  -0.0692   0.1677   1.0000
   6.250   1.0002   0.01004   0.00434  -0.0686   0.1447   1.0000
   6.500   1.0237   0.01044   0.00464  -0.0681   0.1258   1.0000
   6.750   1.0475   0.01081   0.00495  -0.0675   0.1118   1.0000
   7.000   1.0711   0.01119   0.00527  -0.0669   0.0980   1.0000
   7.250   1.0930   0.01170   0.00565  -0.0661   0.0781   1.0000
   7.500   1.1064   0.01296   0.00653  -0.0641   0.0237   1.0000
   7.750   1.1272   0.01356   0.00711  -0.0630   0.0172   1.0000
   8.000   1.1479   0.01415   0.00774  -0.0619   0.0144   1.0000
   8.250   1.1701   0.01456   0.00820  -0.0611   0.0135   1.0000
   8.500   1.1914   0.01504   0.00872  -0.0601   0.0126   1.0000
   8.750   1.2115   0.01560   0.00932  -0.0590   0.0118   1.0000
   9.000   1.2287   0.01638   0.01016  -0.0574   0.0109   1.0000
   9.250   1.2443   0.01722   0.01110  -0.0556   0.0104   1.0000
   9.500   1.2634   0.01772   0.01164  -0.0543   0.0101   1.0000
   9.750   1.2800   0.01829   0.01228  -0.0527   0.0097   1.0000
  10.000   1.2945   0.01888   0.01292  -0.0506   0.0093   1.0000
  10.250   1.3074   0.01954   0.01364  -0.0484   0.0089   1.0000
  10.500   1.3199   0.02023   0.01437  -0.0463   0.0085   1.0000
  10.750   1.3307   0.02104   0.01524  -0.0440   0.0083   1.0000
  11.000   1.3380   0.02210   0.01637  -0.0414   0.0080   1.0000
  11.250   1.3378   0.02367   0.01805  -0.0381   0.0076   1.0000
  11.500   1.3316   0.02579   0.02031  -0.0345   0.0074   1.0000
  11.750   1.3426   0.02677   0.02137  -0.0329   0.0073   1.0000
  12.000   1.3519   0.02791   0.02258  -0.0313   0.0072   1.0000
  12.250   1.3614   0.02907   0.02382  -0.0299   0.0070   1.0000
  12.500   1.3656   0.03072   0.02557  -0.0281   0.0069   1.0000
  12.750   1.3749   0.03197   0.02689  -0.0270   0.0066   1.0000
  13.000   1.3800   0.03366   0.02867  -0.0257   0.0064   1.0000
  13.250   1.3856   0.03536   0.03044  -0.0246   0.0062   1.0000
  13.500   1.3866   0.03756   0.03275  -0.0235   0.0061   1.0000
  13.750   1.3907   0.03956   0.03482  -0.0228   0.0060   1.0000
  14.000   1.3946   0.04162   0.03697  -0.0222   0.0058   1.0000
  14.250   1.3940   0.04427   0.03971  -0.0218   0.0057   1.0000
  14.500   1.3917   0.04723   0.04277  -0.0215   0.0055   1.0000
  14.750   1.3874   0.05056   0.04620  -0.0216   0.0055   1.0000
  15.000   1.3794   0.05455   0.05030  -0.0219   0.0054   1.0000
  15.250   1.3641   0.05971   0.05561  -0.0227   0.0052   1.0000
  15.500   1.3480   0.06531   0.06137  -0.0239   0.0052   1.0000
  15.750   1.3326   0.07118   0.06741  -0.0256   0.0051   1.0000
  16.000   1.3256   0.07608   0.07243  -0.0276   0.0051   1.0000
  16.250   1.3215   0.08086   0.07733  -0.0299   0.0050   1.0000
  16.500   1.3120   0.08663   0.08324  -0.0326   0.0050   1.0000
  16.750   1.3046   0.09224   0.08898  -0.0355   0.0050   1.0000
  17.000   1.2928   0.09874   0.09561  -0.0388   0.0050   1.0000
  17.250   1.2788   0.10585   0.10287  -0.0425   0.0050   1.0000
  17.500   1.2686   0.11258   0.10972  -0.0464   0.0049   1.0000
  17.750   1.2564   0.11976   0.11703  -0.0504   0.0049   1.0000
  18.000   1.2444   0.12717   0.12457  -0.0548   0.0049   1.0000
  18.250   1.2327   0.13459   0.13210  -0.0593   0.0049   1.0000
  18.500   1.2204   0.14231   0.13994  -0.0640   0.0048   1.0000
  18.750   1.2055   0.15071   0.14848  -0.0692   0.0049   1.0000
  19.000   1.1937   0.15864   0.15652  -0.0742   0.0049   1.0000
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