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HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/9 AIRFOIL (hq109-il)
Reynolds number: 200,000
Max Cl/Cd: 62.87 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq109-il-200000.txt
Download as CSV file: xf-hq109-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/9 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5644   0.09701   0.09356  -0.0203   1.0000   0.0438
  -9.500  -0.5710   0.09061   0.08719  -0.0261   1.0000   0.0438
  -9.250  -0.5819   0.08530   0.08185  -0.0309   1.0000   0.0439
  -9.000  -0.5804   0.07909   0.07577  -0.0292   1.0000   0.0452
  -8.750  -0.5749   0.07664   0.07335  -0.0278   1.0000   0.0464
  -8.500  -0.5903   0.07115   0.06784  -0.0326   1.0000   0.0463
  -8.250  -0.5946   0.06735   0.06401  -0.0338   1.0000   0.0471
  -8.000  -0.5975   0.06327   0.05987  -0.0351   1.0000   0.0480
  -7.750  -0.5979   0.05927   0.05577  -0.0360   1.0000   0.0495
  -7.500  -0.5967   0.05510   0.05144  -0.0367   1.0000   0.0510
  -7.000  -0.5959   0.03950   0.03465  -0.0353   1.0000   0.0305
  -6.750  -0.5885   0.03444   0.02921  -0.0338   1.0000   0.0281
  -6.500  -0.5777   0.02948   0.02365  -0.0317   1.0000   0.0259
  -6.250  -0.5605   0.02752   0.02140  -0.0302   1.0000   0.0280
  -6.000  -0.5428   0.02523   0.01873  -0.0285   1.0000   0.0293
  -5.750  -0.5247   0.02268   0.01581  -0.0266   1.0000   0.0291
  -5.500  -0.5056   0.02065   0.01347  -0.0247   1.0000   0.0299
  -5.250  -0.4864   0.01913   0.01173  -0.0229   1.0000   0.0311
  -5.000  -0.4686   0.01729   0.00975  -0.0210   1.0000   0.0334
  -4.750  -0.4515   0.01639   0.00888  -0.0193   1.0000   0.0389
  -4.500  -0.4338   0.01536   0.00773  -0.0175   1.0000   0.0454
  -4.250  -0.4162   0.01449   0.00684  -0.0158   1.0000   0.0570
  -4.000  -0.3985   0.01363   0.00608  -0.0145   1.0000   0.0762
  -3.750  -0.3794   0.01306   0.00556  -0.0134   1.0000   0.0989
  -3.500  -0.3448   0.01201   0.00495  -0.0156   0.9956   0.1759
  -3.250  -0.3138   0.01036   0.00457  -0.0177   0.9901   0.4460
  -3.000  -0.2790   0.00994   0.00466  -0.0192   0.9840   0.6034
  -2.750  -0.2435   0.00989   0.00469  -0.0206   0.9773   0.6648
  -2.500  -0.2062   0.00990   0.00473  -0.0223   0.9712   0.7093
  -2.250  -0.1705   0.00992   0.00474  -0.0236   0.9647   0.7427
  -2.000  -0.1342   0.00994   0.00476  -0.0250   0.9584   0.7736
  -1.750  -0.0961   0.00995   0.00478  -0.0266   0.9536   0.8017
  -1.500  -0.0634   0.00990   0.00474  -0.0272   0.9458   0.8209
  -1.250  -0.0254   0.00984   0.00464  -0.0288   0.9411   0.8403
  -1.000   0.0032   0.00977   0.00458  -0.0286   0.9315   0.8586
  -0.750   0.0346   0.00967   0.00450  -0.0287   0.9239   0.8754
  -0.500   0.0644   0.00959   0.00441  -0.0285   0.9157   0.8928
  -0.250   0.0929   0.00954   0.00437  -0.0281   0.9069   0.9094
   0.000   0.1267   0.00946   0.00427  -0.0288   0.8997   0.9224
   0.250   0.1590   0.00939   0.00419  -0.0293   0.8882   0.9357
   0.500   0.1945   0.00932   0.00410  -0.0304   0.8763   0.9482
   0.750   0.2324   0.00924   0.00399  -0.0321   0.8636   0.9597
   1.000   0.2718   0.00917   0.00390  -0.0342   0.8508   0.9707
   1.250   0.3136   0.00912   0.00385  -0.0369   0.8388   0.9806
   1.500   0.3567   0.00905   0.00378  -0.0401   0.8264   0.9902
   1.750   0.3956   0.00899   0.00371  -0.0425   0.8126   1.0000
   2.000   0.4114   0.00897   0.00368  -0.0404   0.7975   1.0000
   2.250   0.4294   0.00898   0.00369  -0.0386   0.7819   1.0000
   2.500   0.4500   0.00901   0.00369  -0.0371   0.7656   1.0000
   2.750   0.4721   0.00904   0.00368  -0.0357   0.7478   1.0000
   3.000   0.4951   0.00908   0.00372  -0.0346   0.7266   1.0000
   3.250   0.5187   0.00913   0.00373  -0.0334   0.7035   1.0000
   3.500   0.5424   0.00920   0.00379  -0.0323   0.6745   1.0000
   3.750   0.5660   0.00931   0.00384  -0.0312   0.6396   1.0000
   4.000   0.5896   0.00947   0.00392  -0.0301   0.5984   1.0000
   4.250   0.6124   0.00974   0.00404  -0.0289   0.5434   1.0000
   4.500   0.6335   0.01022   0.00421  -0.0275   0.4687   1.0000
   4.750   0.6536   0.01091   0.00456  -0.0262   0.3862   1.0000
   5.000   0.6741   0.01167   0.00498  -0.0251   0.3128   1.0000
   5.250   0.6954   0.01241   0.00549  -0.0243   0.2587   1.0000
   5.500   0.7171   0.01315   0.00601  -0.0235   0.2023   1.0000
   5.750   0.7377   0.01408   0.00660  -0.0226   0.1408   1.0000
   6.000   0.7575   0.01520   0.00750  -0.0216   0.0996   1.0000
   6.250   0.7776   0.01633   0.00852  -0.0205   0.0723   1.0000
   6.500   0.7984   0.01739   0.00956  -0.0194   0.0534   1.0000
   6.750   0.8184   0.01858   0.01074  -0.0183   0.0402   1.0000
   7.000   0.8381   0.01998   0.01220  -0.0170   0.0317   1.0000
   7.250   0.8550   0.02255   0.01478  -0.0154   0.0271   1.0000
   7.500   0.8777   0.02421   0.01664  -0.0143   0.0255   1.0000
   7.750   0.8999   0.02607   0.01874  -0.0133   0.0235   1.0000
   8.000   0.9204   0.02717   0.01999  -0.0124   0.0206   1.0000
   8.250   0.9393   0.02935   0.02236  -0.0114   0.0194   1.0000
   8.500   0.9547   0.03283   0.02618  -0.0100   0.0187   1.0000
   8.750   0.9674   0.03631   0.03006  -0.0084   0.0186   1.0000
   9.000   0.9770   0.03969   0.03387  -0.0065   0.0187   1.0000
   9.250   0.9831   0.04308   0.03771  -0.0044   0.0191   1.0000
   9.500   0.9627   0.05065   0.04619  -0.0003   0.0219   1.0000
   9.750   0.9452   0.05588   0.05179   0.0021   0.0231   1.0000
  10.000   0.9261   0.05971   0.05582   0.0045   0.0238   1.0000
  10.250   0.9046   0.06391   0.06019   0.0052   0.0242   1.0000
  10.500   0.8842   0.06860   0.06503   0.0039   0.0246   1.0000
  10.750   0.8609   0.07468   0.07124   0.0004   0.0246   1.0000
  11.000   0.8391   0.08210   0.07877  -0.0052   0.0248   1.0000
  11.250   0.8181   0.09180   0.08854  -0.0128   0.0251   1.0000
  11.500   0.7994   0.10269   0.09938  -0.0197   0.0260   1.0000
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