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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 200,000
Max Cl/Cd: 70.48 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2511-il-200000-n5.txt
Download as CSV file: xf-hq2511-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4586   0.08077   0.07725  -0.0451   1.0000   0.0121
  -9.750  -0.4690   0.07488   0.07142  -0.0481   1.0000   0.0120
  -9.500  -0.4814   0.06848   0.06510  -0.0519   1.0000   0.0119
  -9.250  -0.5097   0.05855   0.05518  -0.0591   1.0000   0.0117
  -9.000  -0.5392   0.05465   0.05128  -0.0592   1.0000   0.0116
  -8.750  -0.5623   0.04970   0.04619  -0.0596   0.9974   0.0115
  -8.500  -0.5632   0.03932   0.03511  -0.0675   0.9843   0.0112
  -8.250  -0.5516   0.03239   0.02740  -0.0709   0.9750   0.0111
  -8.000  -0.5273   0.02797   0.02232  -0.0734   0.9704   0.0111
  -7.750  -0.5043   0.02516   0.01904  -0.0741   0.9630   0.0112
  -7.500  -0.4753   0.02299   0.01650  -0.0754   0.9583   0.0113
  -7.250  -0.4479   0.02139   0.01461  -0.0761   0.9525   0.0115
  -7.000  -0.4200   0.02004   0.01304  -0.0767   0.9465   0.0117
  -6.750  -0.3892   0.01887   0.01166  -0.0777   0.9422   0.0120
  -6.500  -0.3644   0.01794   0.01062  -0.0775   0.9340   0.0125
  -6.250  -0.3350   0.01714   0.00972  -0.0782   0.9289   0.0133
  -6.000  -0.3089   0.01647   0.00892  -0.0781   0.9216   0.0141
  -5.750  -0.2808   0.01579   0.00811  -0.0783   0.9155   0.0159
  -5.500  -0.2540   0.01518   0.00747  -0.0783   0.9088   0.0185
  -5.250  -0.2267   0.01468   0.00695  -0.0784   0.9023   0.0257
  -5.000  -0.1984   0.01433   0.00657  -0.0785   0.8968   0.0360
  -4.750  -0.1716   0.01405   0.00626  -0.0784   0.8899   0.0449
  -4.500  -0.1432   0.01370   0.00588  -0.0786   0.8848   0.0516
  -4.250  -0.1166   0.01346   0.00554  -0.0784   0.8778   0.0573
  -4.000  -0.0892   0.01314   0.00520  -0.0784   0.8722   0.0656
  -3.750  -0.0619   0.01287   0.00489  -0.0784   0.8665   0.0753
  -3.500  -0.0354   0.01256   0.00460  -0.0782   0.8598   0.0911
  -3.250  -0.0083   0.01216   0.00427  -0.0782   0.8540   0.1194
  -3.000   0.0165   0.01156   0.00399  -0.0780   0.8462   0.2043
  -2.500   0.0653   0.01032   0.00365  -0.0774   0.8318   0.4662
  -2.250   0.0911   0.01009   0.00363  -0.0767   0.8257   0.5468
  -2.000   0.1168   0.01003   0.00366  -0.0761   0.8180   0.5971
  -1.750   0.1438   0.01001   0.00363  -0.0757   0.8114   0.6321
  -1.500   0.1699   0.01002   0.00365  -0.0751   0.8036   0.6623
  -1.250   0.1964   0.01003   0.00366  -0.0745   0.7973   0.6904
  -1.000   0.2226   0.01004   0.00369  -0.0739   0.7908   0.7108
  -0.750   0.2497   0.01004   0.00367  -0.0736   0.7846   0.7245
  -0.500   0.2771   0.01005   0.00363  -0.0733   0.7791   0.7367
  -0.250   0.3038   0.01004   0.00362  -0.0729   0.7714   0.7469
   0.000   0.3309   0.01002   0.00357  -0.0726   0.7635   0.7557
   0.250   0.3581   0.01001   0.00352  -0.0723   0.7544   0.7643
   0.500   0.3848   0.01000   0.00350  -0.0720   0.7453   0.7720
   1.000   0.4387   0.00999   0.00347  -0.0713   0.7267   0.7885
   1.250   0.4654   0.00999   0.00346  -0.0709   0.7156   0.7974
   1.500   0.4918   0.01000   0.00345  -0.0704   0.7040   0.8068
   1.750   0.5183   0.01000   0.00345  -0.0700   0.6930   0.8165
   2.000   0.5446   0.01002   0.00350  -0.0696   0.6819   0.8273
   2.250   0.5705   0.01003   0.00354  -0.0691   0.6702   0.8399
   2.500   0.5960   0.01004   0.00359  -0.0684   0.6581   0.8547
   2.750   0.6214   0.01005   0.00365  -0.0677   0.6437   0.8726
   3.000   0.6470   0.01006   0.00368  -0.0670   0.6244   0.8954
   3.250   0.6759   0.01009   0.00369  -0.0670   0.5978   0.9275
   3.500   0.7109   0.01019   0.00371  -0.0686   0.5633   1.0000
   3.750   0.7355   0.01044   0.00382  -0.0680   0.5278   1.0000
   4.000   0.7591   0.01077   0.00397  -0.0674   0.4924   1.0000
   4.500   0.8052   0.01156   0.00445  -0.0659   0.4309   1.0000
   4.750   0.8285   0.01195   0.00474  -0.0652   0.4015   1.0000
   5.000   0.8517   0.01235   0.00505  -0.0646   0.3692   1.0000
   5.250   0.8736   0.01283   0.00539  -0.0637   0.3330   1.0000
   5.500   0.8951   0.01335   0.00577  -0.0629   0.3040   1.0000
   5.750   0.9170   0.01386   0.00619  -0.0621   0.2816   1.0000
   6.000   0.9395   0.01431   0.00661  -0.0613   0.2623   1.0000
   6.250   0.9618   0.01478   0.00706  -0.0606   0.2440   1.0000
   6.500   0.9836   0.01527   0.00752  -0.0598   0.2248   1.0000
   6.750   1.0043   0.01583   0.00800  -0.0589   0.2006   1.0000
   7.000   1.0244   0.01645   0.00850  -0.0579   0.1746   1.0000
   7.250   1.0439   0.01709   0.00905  -0.0568   0.1526   1.0000
   7.500   1.0637   0.01771   0.00962  -0.0558   0.1345   1.0000
   7.750   1.0834   0.01831   0.01020  -0.0548   0.1204   1.0000
   8.000   1.1021   0.01899   0.01082  -0.0536   0.1038   1.0000
   8.250   1.1205   0.01967   0.01147  -0.0524   0.0874   1.0000
   8.500   1.1361   0.02057   0.01225  -0.0509   0.0581   1.0000
   8.750   1.1447   0.02201   0.01341  -0.0485   0.0295   1.0000
   9.000   1.1563   0.02305   0.01447  -0.0463   0.0240   1.0000
   9.250   1.1676   0.02411   0.01559  -0.0441   0.0210   1.0000
   9.500   1.1782   0.02521   0.01680  -0.0419   0.0194   1.0000
   9.750   1.1898   0.02622   0.01795  -0.0399   0.0185   1.0000
  10.000   1.1999   0.02734   0.01921  -0.0379   0.0175   1.0000
  10.250   1.2085   0.02859   0.02061  -0.0359   0.0168   1.0000
  10.500   1.2155   0.02997   0.02212  -0.0339   0.0161   1.0000
  10.750   1.2204   0.03155   0.02381  -0.0319   0.0154   1.0000
  11.000   1.2208   0.03355   0.02590  -0.0298   0.0147   1.0000
  11.250   1.2242   0.03541   0.02788  -0.0282   0.0142   1.0000
  11.500   1.2297   0.03715   0.02976  -0.0268   0.0137   1.0000
  11.750   1.2335   0.03913   0.03188  -0.0255   0.0133   1.0000
  12.000   1.2360   0.04131   0.03419  -0.0243   0.0130   1.0000
  12.250   1.2383   0.04362   0.03664  -0.0234   0.0127   1.0000
  12.500   1.2400   0.04607   0.03921  -0.0226   0.0124   1.0000
  12.750   1.2411   0.04867   0.04197  -0.0219   0.0121   1.0000
  13.000   1.2419   0.05140   0.04483  -0.0215   0.0119   1.0000
  13.250   1.2418   0.05432   0.04787  -0.0212   0.0116   1.0000
  13.500   1.2410   0.05743   0.05111  -0.0212   0.0114   1.0000
  13.750   1.2396   0.06068   0.05448  -0.0213   0.0112   1.0000
  14.000   1.2371   0.06417   0.05808  -0.0217   0.0109   1.0000
  14.250   1.2334   0.06799   0.06201  -0.0223   0.0107   1.0000
  14.500   1.2283   0.07218   0.06633  -0.0231   0.0104   1.0000
  14.750   1.2230   0.07653   0.07088  -0.0245   0.0103   1.0000
  15.000   1.2158   0.08140   0.07597  -0.0264   0.0101   1.0000
  15.250   1.2074   0.08671   0.08150  -0.0288   0.0099   1.0000
  15.500   1.1985   0.09234   0.08733  -0.0315   0.0098   1.0000
  15.750   1.1885   0.09842   0.09361  -0.0346   0.0097   1.0000
  16.000   1.1773   0.10494   0.10031  -0.0381   0.0097   1.0000
  16.250   1.1648   0.11200   0.10757  -0.0421   0.0096   1.0000
  16.500   1.1520   0.11941   0.11517  -0.0465   0.0096   1.0000
  16.750   1.1385   0.12729   0.12322  -0.0513   0.0096   1.0000
  17.000   1.1247   0.13549   0.13159  -0.0565   0.0096   1.0000
  17.250   1.1094   0.14441   0.14068  -0.0621   0.0097   1.0000
  17.500   1.0934   0.15398   0.15040  -0.0683   0.0097   1.0000
  17.750   1.0770   0.16408   0.16063  -0.0747   0.0098   1.0000
  18.000   1.0564   0.17618   0.17286  -0.0822   0.0100   1.0000
  18.250   1.0324   0.19052   0.18729  -0.0907   0.0102   1.0000
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