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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 200,000
Max Cl/Cd: 90.24 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq358-il-200000.txt
Download as CSV file: xf-hq358-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/8 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3610   0.09056   0.08736  -0.0300   1.0000   0.0275
  -7.250  -0.3766   0.08957   0.08646  -0.0270   1.0000   0.0276
  -7.000  -0.3922   0.08845   0.08542  -0.0246   1.0000   0.0278
  -6.750  -0.4010   0.08660   0.08363  -0.0245   1.0000   0.0280
  -6.500  -0.4056   0.08428   0.08135  -0.0259   1.0000   0.0282
  -6.250  -0.4045   0.08129   0.07838  -0.0294   0.9999   0.0284
  -6.000  -0.3667   0.07521   0.07216  -0.0418   0.9951   0.0287
  -5.750  -0.3350   0.06978   0.06656  -0.0502   0.9902   0.0289
  -5.500  -0.3240   0.06171   0.05856  -0.0540   0.9863   0.0303
  -5.250  -0.3008   0.05812   0.05497  -0.0568   0.9831   0.0330
  -5.000  -0.2696   0.05373   0.05043  -0.0629   0.9780   0.0373
  -4.750  -0.2171   0.04813   0.04413  -0.0737   0.9726   0.0422
  -4.500  -0.1916   0.04316   0.03928  -0.0769   0.9701   0.0444
  -4.250  -0.1618   0.03998   0.03595  -0.0798   0.9655   0.0477
  -3.750  -0.0869   0.03300   0.02827  -0.0872   0.9579   0.0585
  -3.500  -0.0430   0.03077   0.02543  -0.0910   0.9557   0.0696
  -3.250  -0.0188   0.02806   0.02275  -0.0917   0.9496   0.0736
  -3.000   0.0179   0.02588   0.02027  -0.0941   0.9461   0.0869
  -2.750   0.0673   0.02105   0.01429  -0.0936   0.9448   0.0299
  -2.500   0.1074   0.01924   0.01222  -0.0955   0.9429   0.0280
  -2.250   0.1369   0.01777   0.01054  -0.0955   0.9375   0.0280
  -2.000   0.1717   0.01626   0.00897  -0.0968   0.9337   0.0332
  -1.750   0.2112   0.01534   0.00797  -0.0989   0.9310   0.0395
  -1.500   0.2539   0.01391   0.00664  -0.1018   0.9292   0.0919
  -1.250   0.2725   0.01206   0.00688  -0.1005   0.9222   0.7005
  -1.000   0.3018   0.01168   0.00675  -0.0996   0.9179   0.8160
  -0.750   0.3295   0.01126   0.00646  -0.0985   0.9128   0.8931
  -0.500   0.3772   0.01091   0.00602  -0.1022   0.9073   1.0000
  -0.250   0.4193   0.01063   0.00558  -0.1048   0.9027   1.0000
   0.000   0.4495   0.01053   0.00536  -0.1051   0.8932   1.0000
   0.250   0.4846   0.01032   0.00503  -0.1062   0.8868   1.0000
   0.500   0.5145   0.01020   0.00482  -0.1063   0.8775   1.0000
   0.750   0.5430   0.01012   0.00466  -0.1061   0.8679   1.0000
   1.000   0.5741   0.00998   0.00445  -0.1064   0.8606   1.0000
   1.250   0.6013   0.00997   0.00440  -0.1060   0.8508   1.0000
   1.500   0.6287   0.00996   0.00437  -0.1057   0.8411   1.0000
   1.750   0.6571   0.00991   0.00427  -0.1055   0.8321   1.0000
   2.000   0.6851   0.00986   0.00419  -0.1052   0.8219   1.0000
   2.250   0.7116   0.00986   0.00418  -0.1047   0.8100   1.0000
   2.500   0.7383   0.00985   0.00417  -0.1042   0.7975   1.0000
   2.750   0.7650   0.00983   0.00419  -0.1036   0.7840   1.0000
   3.000   0.7918   0.00983   0.00418  -0.1031   0.7695   1.0000
   3.250   0.8183   0.00984   0.00418  -0.1025   0.7533   1.0000
   3.500   0.8438   0.00989   0.00424  -0.1017   0.7334   1.0000
   3.750   0.8697   0.00994   0.00427  -0.1010   0.7116   1.0000
   4.000   0.8947   0.01004   0.00440  -0.1001   0.6847   1.0000
   4.250   0.9189   0.01019   0.00450  -0.0991   0.6513   1.0000
   4.500   0.9421   0.01044   0.00464  -0.0979   0.6094   1.0000
   4.750   0.9637   0.01083   0.00483  -0.0965   0.5554   1.0000
   5.000   0.9831   0.01142   0.00514  -0.0948   0.4913   1.0000
   5.250   1.0016   0.01218   0.00564  -0.0931   0.4314   1.0000
   5.500   1.0213   0.01291   0.00616  -0.0917   0.3851   1.0000
   5.750   1.0418   0.01359   0.00670  -0.0906   0.3494   1.0000
   6.000   1.0616   0.01428   0.00721  -0.0894   0.3090   1.0000
   6.250   1.0820   0.01493   0.00776  -0.0883   0.2743   1.0000
   6.500   1.1017   0.01562   0.00831  -0.0872   0.2327   1.0000
   6.750   1.1207   0.01641   0.00887  -0.0860   0.1741   1.0000
   7.000   1.1222   0.01952   0.01074  -0.0826   0.0271   1.0000
   7.250   1.1384   0.02097   0.01239  -0.0805   0.0188   1.0000
   7.500   1.1506   0.02271   0.01433  -0.0780   0.0162   1.0000
   7.750   1.1612   0.02459   0.01637  -0.0753   0.0153   1.0000
   8.000   1.1750   0.02626   0.01818  -0.0731   0.0149   1.0000
   8.250   1.1900   0.02821   0.02028  -0.0711   0.0146   1.0000
   8.500   1.2078   0.03052   0.02274  -0.0695   0.0145   1.0000
   8.750   1.2279   0.03330   0.02574  -0.0683   0.0146   1.0000
   9.000   1.2471   0.03664   0.02938  -0.0671   0.0148   1.0000
   9.250   1.2619   0.04093   0.03405  -0.0655   0.0152   1.0000
   9.500   1.2764   0.04479   0.03822  -0.0640   0.0159   1.0000
   9.750   1.2897   0.04603   0.03971  -0.0617   0.0166   1.0000
  10.000   1.2870   0.05081   0.04531  -0.0571   0.0195   1.0000
  10.250   1.2757   0.05595   0.05091  -0.0531   0.0216   1.0000
  10.500   1.2605   0.06015   0.05539  -0.0494   0.0227   1.0000
  10.750   1.2423   0.06483   0.06029  -0.0464   0.0237   1.0000
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