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HQ 2.5/11 AIRFOIL (hq2511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/11 AIRFOIL (hq2511-il)
Reynolds number: 1,000,000
Max Cl/Cd: 92.19 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2511-il-1000000-n5.txt
Download as CSV file: xf-hq2511-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7087   0.04858   0.04659  -0.0641   1.0000   0.0041
 -11.500  -0.7316   0.04133   0.03916  -0.0703   1.0000   0.0041
 -11.250  -0.7559   0.03684   0.03452  -0.0719   1.0000   0.0040
 -11.000  -0.7662   0.03358   0.03105  -0.0721   0.9908   0.0041
 -10.750  -0.7493   0.02990   0.02707  -0.0761   0.9826   0.0041
 -10.500  -0.7273   0.02738   0.02428  -0.0787   0.9745   0.0042
 -10.250  -0.7054   0.02489   0.02150  -0.0808   0.9657   0.0042
 -10.000  -0.6815   0.02335   0.01976  -0.0819   0.9566   0.0043
  -9.750  -0.6629   0.02184   0.01802  -0.0817   0.9447   0.0043
  -9.500  -0.6432   0.02069   0.01670  -0.0812   0.9328   0.0044
  -9.250  -0.6236   0.01956   0.01537  -0.0806   0.9200   0.0044
  -9.000  -0.6026   0.01862   0.01426  -0.0800   0.9073   0.0044
  -8.750  -0.5816   0.01765   0.01310  -0.0793   0.8954   0.0044
  -8.250  -0.5361   0.01612   0.01126  -0.0783   0.8754   0.0045
  -8.000  -0.5121   0.01553   0.01054  -0.0779   0.8672   0.0045
  -7.750  -0.4891   0.01459   0.00945  -0.0774   0.8596   0.0046
  -7.500  -0.4660   0.01365   0.00835  -0.0769   0.8531   0.0047
  -7.250  -0.4413   0.01298   0.00758  -0.0766   0.8466   0.0048
  -6.750  -0.3906   0.01190   0.00633  -0.0761   0.8343   0.0048
  -6.500  -0.3649   0.01141   0.00575  -0.0759   0.8277   0.0049
  -6.250  -0.3388   0.01097   0.00524  -0.0757   0.8214   0.0049
  -6.000  -0.3124   0.01060   0.00479  -0.0755   0.8140   0.0049
  -5.750  -0.2859   0.01021   0.00434  -0.0753   0.8072   0.0050
  -5.500  -0.2590   0.00990   0.00397  -0.0752   0.7999   0.0051
  -5.250  -0.2321   0.00960   0.00360  -0.0751   0.7935   0.0052
  -5.000  -0.2048   0.00933   0.00328  -0.0750   0.7869   0.0053
  -4.750  -0.1776   0.00911   0.00300  -0.0749   0.7806   0.0054
  -4.500  -0.1500   0.00889   0.00273  -0.0749   0.7737   0.0057
  -4.000  -0.0947   0.00855   0.00227  -0.0748   0.7599   0.0064
  -3.750  -0.0670   0.00841   0.00209  -0.0748   0.7534   0.0068
  -3.500  -0.0391   0.00827   0.00192  -0.0748   0.7474   0.0079
  -3.250  -0.0116   0.00806   0.00174  -0.0748   0.7406   0.0181
  -3.000   0.0162   0.00790   0.00161  -0.0748   0.7345   0.0286
  -2.750   0.0439   0.00775   0.00150  -0.0748   0.7275   0.0420
  -2.500   0.0716   0.00762   0.00141  -0.0748   0.7199   0.0568
  -2.250   0.0995   0.00752   0.00132  -0.0748   0.7111   0.0709
  -2.000   0.1272   0.00737   0.00123  -0.0749   0.7030   0.0959
  -1.750   0.1543   0.00706   0.00112  -0.0749   0.6952   0.1668
  -1.500   0.1818   0.00681   0.00104  -0.0750   0.6880   0.2292
  -1.250   0.2079   0.00623   0.00093  -0.0751   0.6809   0.3851
  -1.000   0.2354   0.00603   0.00089  -0.0752   0.6732   0.4496
  -0.750   0.2627   0.00590   0.00087  -0.0751   0.6626   0.5017
  -0.500   0.2902   0.00581   0.00087  -0.0751   0.6517   0.5467
  -0.250   0.3179   0.00575   0.00090  -0.0750   0.6415   0.5885
   0.000   0.3454   0.00573   0.00093  -0.0750   0.6309   0.6218
   0.250   0.3732   0.00577   0.00096  -0.0749   0.6194   0.6373
   0.500   0.4011   0.00582   0.00098  -0.0749   0.6065   0.6479
   0.750   0.4289   0.00588   0.00101  -0.0749   0.5926   0.6568
   1.000   0.4566   0.00596   0.00105  -0.0748   0.5775   0.6643
   1.250   0.4835   0.00609   0.00110  -0.0746   0.5505   0.6717
   1.500   0.5087   0.00639   0.00119  -0.0742   0.5002   0.6783
   1.750   0.5336   0.00671   0.00133  -0.0737   0.4545   0.6858
   2.000   0.5599   0.00692   0.00144  -0.0735   0.4291   0.6926
   2.250   0.5869   0.00706   0.00153  -0.0734   0.4120   0.6984
   2.500   0.6137   0.00723   0.00163  -0.0732   0.3903   0.7038
   2.750   0.6396   0.00747   0.00176  -0.0729   0.3559   0.7092
   3.000   0.6650   0.00776   0.00191  -0.0726   0.3203   0.7152
   3.500   0.7168   0.00823   0.00222  -0.0720   0.2768   0.7265
   3.750   0.7431   0.00841   0.00238  -0.0718   0.2616   0.7328
   4.000   0.7694   0.00859   0.00253  -0.0716   0.2483   0.7395
   4.250   0.7956   0.00877   0.00269  -0.0714   0.2344   0.7485
   4.500   0.8213   0.00896   0.00287  -0.0711   0.2191   0.7594
   4.750   0.8465   0.00919   0.00307  -0.0707   0.2016   0.7717
   5.000   0.8712   0.00945   0.00328  -0.0703   0.1816   0.7845
   5.250   0.8947   0.00982   0.00356  -0.0696   0.1527   0.7974
   5.500   0.9183   0.01017   0.00383  -0.0690   0.1302   0.8111
   5.750   0.9421   0.01045   0.00409  -0.0684   0.1154   0.8272
   6.000   0.9663   0.01066   0.00434  -0.0678   0.1061   0.8467
   6.250   0.9890   0.01085   0.00459  -0.0669   0.0961   0.8774
   6.500   1.0168   0.01105   0.00489  -0.0671   0.0812   1.0000
   6.750   1.0404   0.01144   0.00521  -0.0666   0.0681   1.0000
   7.000   1.0595   0.01222   0.00576  -0.0654   0.0344   1.0000
   7.250   1.0797   0.01288   0.00633  -0.0643   0.0170   1.0000
   7.500   1.1027   0.01329   0.00673  -0.0636   0.0136   1.0000
   7.750   1.1256   0.01368   0.00713  -0.0629   0.0120   1.0000
   8.000   1.1478   0.01411   0.00758  -0.0621   0.0105   1.0000
   8.250   1.1706   0.01447   0.00798  -0.0614   0.0098   1.0000
   8.500   1.1927   0.01487   0.00841  -0.0606   0.0091   1.0000
   8.750   1.2140   0.01531   0.00887  -0.0597   0.0085   1.0000
   9.000   1.2344   0.01581   0.00940  -0.0586   0.0079   1.0000
   9.250   1.2537   0.01638   0.01001  -0.0574   0.0074   1.0000
   9.500   1.2736   0.01685   0.01054  -0.0563   0.0072   1.0000
   9.750   1.2928   0.01733   0.01107  -0.0551   0.0070   1.0000
  10.000   1.3105   0.01783   0.01160  -0.0536   0.0067   1.0000
  10.250   1.3265   0.01833   0.01215  -0.0519   0.0063   1.0000
  10.500   1.3416   0.01886   0.01272  -0.0500   0.0060   1.0000
  10.750   1.3556   0.01946   0.01336  -0.0481   0.0058   1.0000
  11.000   1.3686   0.02013   0.01409  -0.0461   0.0056   1.0000
  11.250   1.3801   0.02092   0.01494  -0.0439   0.0054   1.0000
  11.500   1.3886   0.02193   0.01604  -0.0415   0.0051   1.0000
  11.750   1.3997   0.02278   0.01696  -0.0396   0.0050   1.0000
  12.000   1.4112   0.02363   0.01787  -0.0379   0.0050   1.0000
  12.250   1.4228   0.02450   0.01881  -0.0362   0.0048   1.0000
  12.500   1.4313   0.02561   0.02001  -0.0344   0.0047   1.0000
  12.750   1.4407   0.02670   0.02117  -0.0328   0.0046   1.0000
  13.000   1.4496   0.02787   0.02242  -0.0313   0.0045   1.0000
  13.250   1.4581   0.02911   0.02374  -0.0298   0.0043   1.0000
  13.500   1.4632   0.03066   0.02539  -0.0283   0.0042   1.0000
  13.750   1.4708   0.03207   0.02687  -0.0271   0.0041   1.0000
  14.000   1.4794   0.03344   0.02829  -0.0261   0.0039   1.0000
  14.250   1.4844   0.03518   0.03011  -0.0251   0.0038   1.0000
  14.500   1.4882   0.03710   0.03212  -0.0242   0.0037   1.0000
  14.750   1.4901   0.03929   0.03439  -0.0234   0.0037   1.0000
  15.000   1.4911   0.04165   0.03685  -0.0228   0.0036   1.0000
  15.250   1.4879   0.04459   0.03990  -0.0224   0.0035   1.0000
  15.500   1.4829   0.04788   0.04330  -0.0222   0.0034   1.0000
  15.750   1.4746   0.05177   0.04732  -0.0225   0.0033   1.0000
  16.000   1.4656   0.05601   0.05169  -0.0232   0.0033   1.0000
  16.250   1.4624   0.05968   0.05547  -0.0241   0.0032   1.0000
  16.500   1.4549   0.06419   0.06011  -0.0254   0.0032   1.0000
  16.750   1.4471   0.06900   0.06506  -0.0272   0.0032   1.0000
  17.000   1.4341   0.07491   0.07111  -0.0296   0.0032   1.0000
  17.250   1.4177   0.08171   0.07805  -0.0327   0.0032   1.0000
  17.500   1.4065   0.08784   0.08432  -0.0357   0.0032   1.0000
  17.750   1.3874   0.09564   0.09226  -0.0396   0.0032   1.0000
  18.000   1.3710   0.10317   0.09993  -0.0436   0.0032   1.0000
  18.250   1.3533   0.11121   0.10811  -0.0479   0.0031   1.0000
  18.500   1.3348   0.11954   0.11657  -0.0525   0.0031   1.0000
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