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HQ 3.5/18 AIRFOIL (hq3518-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/18 AIRFOIL (hq3518-il)
Reynolds number: 50,000
Max Cl/Cd: 21.39 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3518-il-50000-n5.txt
Download as CSV file: xf-hq3518-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/18 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3973   0.11187   0.10474  -0.0540   1.0000   0.0889
 -11.500  -0.4192   0.10760   0.10056  -0.0538   1.0000   0.0889
 -11.250  -0.4401   0.09912   0.09211  -0.0589   0.9965   0.0886
 -11.000  -0.4908   0.08411   0.07699  -0.0706   0.9887   0.0878
 -10.750  -0.5483   0.07274   0.06535  -0.0800   0.9781   0.0868
 -10.500  -0.5805   0.06685   0.05916  -0.0841   0.9676   0.0868
 -10.250  -0.6014   0.06325   0.05530  -0.0845   0.9568   0.0872
 -10.000  -0.6112   0.06013   0.05192  -0.0844   0.9473   0.0884
  -9.750  -0.6108   0.05679   0.04819  -0.0853   0.9402   0.0902
  -9.500  -0.6169   0.05434   0.04538  -0.0836   0.9309   0.0918
  -9.250  -0.6096   0.05142   0.04190  -0.0840   0.9251   0.0938
  -9.000  -0.6024   0.04970   0.04005  -0.0823   0.9181   0.0953
  -8.750  -0.5828   0.04814   0.03844  -0.0823   0.9131   0.0979
  -8.500  -0.5586   0.04646   0.03655  -0.0833   0.9093   0.1015
  -8.250  -0.5515   0.04519   0.03502  -0.0811   0.9021   0.1042
  -8.000  -0.5322   0.04364   0.03304  -0.0809   0.8972   0.1074
  -7.750  -0.5024   0.04240   0.03193  -0.0818   0.8942   0.1115
  -7.500  -0.4885   0.04160   0.03105  -0.0802   0.8886   0.1153
  -7.250  -0.4687   0.04067   0.02989  -0.0793   0.8835   0.1198
  -7.000  -0.4406   0.03976   0.02903  -0.0797   0.8799   0.1250
  -6.750  -0.4092   0.03896   0.02816  -0.0807   0.8771   0.1318
  -6.500  -0.4033   0.03861   0.02773  -0.0774   0.8703   0.1361
  -6.250  -0.3831   0.03808   0.02727  -0.0766   0.8658   0.1426
  -6.000  -0.3557   0.03747   0.02662  -0.0769   0.8624   0.1516
  -5.750  -0.3425   0.03710   0.02626  -0.0751   0.8569   0.1595
  -5.500  -0.3300   0.03674   0.02591  -0.0732   0.8514   0.1689
  -5.250  -0.3080   0.03620   0.02538  -0.0728   0.8473   0.1836
  -5.000  -0.2813   0.03544   0.02470  -0.0733   0.8442   0.2050
  -4.750  -0.2813   0.03514   0.02452  -0.0696   0.8367   0.2216
  -4.500  -0.2639   0.03439   0.02401  -0.0689   0.8320   0.2560
  -4.250  -0.2399   0.03350   0.02347  -0.0692   0.8284   0.3183
  -4.000  -0.2344   0.03333   0.02396  -0.0657   0.8215   0.3787
  -3.750  -0.2156   0.03363   0.02454  -0.0636   0.8152   0.4753
  -3.500  -0.1835   0.03389   0.02470  -0.0636   0.8108   0.5312
  -3.250  -0.1760   0.03442   0.02521  -0.0598   0.8015   0.5603
  -3.000  -0.1503   0.03494   0.02567  -0.0583   0.7959   0.5923
  -2.750  -0.1306   0.03543   0.02605  -0.0563   0.7897   0.6194
  -2.500  -0.1176   0.03601   0.02657  -0.0533   0.7823   0.6398
  -2.250  -0.0922   0.03648   0.02696  -0.0516   0.7778   0.6611
  -2.000  -0.0780   0.03693   0.02733  -0.0491   0.7714   0.6779
  -1.750  -0.0621   0.03724   0.02755  -0.0472   0.7646   0.6928
  -1.500  -0.0348   0.03739   0.02759  -0.0465   0.7602   0.7060
  -1.250  -0.0209   0.03773   0.02787  -0.0442   0.7533   0.7176
  -1.000  -0.0042   0.03797   0.02804  -0.0424   0.7463   0.7313
  -0.750   0.0241   0.03799   0.02795  -0.0420   0.7420   0.7460
  -0.500   0.0327   0.03842   0.02837  -0.0390   0.7340   0.7564
  -0.250   0.0524   0.03860   0.02849  -0.0379   0.7278   0.7681
   0.000   0.0818   0.03858   0.02837  -0.0379   0.7239   0.7788
   0.250   0.0905   0.03904   0.02880  -0.0357   0.7149   0.7872
   0.500   0.1158   0.03911   0.02880  -0.0357   0.7089   0.7943
   0.750   0.1521   0.03895   0.02851  -0.0374   0.7052   0.8004
   1.000   0.1575   0.03962   0.02918  -0.0351   0.6946   0.8064
   1.250   0.1865   0.03968   0.02918  -0.0357   0.6897   0.8130
   1.500   0.2229   0.03952   0.02894  -0.0371   0.6865   0.8201
   1.750   0.2256   0.04032   0.02975  -0.0346   0.6741   0.8279
   2.000   0.2641   0.03992   0.02927  -0.0360   0.6696   0.8356
   2.250   0.2728   0.04047   0.02983  -0.0340   0.6572   0.8435
   2.500   0.3116   0.03991   0.02922  -0.0351   0.6522   0.8517
   2.750   0.3222   0.04039   0.02972  -0.0334   0.6395   0.8613
   3.000   0.3588   0.03987   0.02918  -0.0342   0.6346   0.8714
   3.250   0.3684   0.04067   0.03003  -0.0328   0.6229   0.8838
   3.500   0.4033   0.04039   0.02978  -0.0337   0.6178   0.8962
   3.750   0.4197   0.04121   0.03067  -0.0335   0.6068   0.9120
   4.000   0.4596   0.04103   0.03052  -0.0356   0.6011   0.9293
   4.500   0.5218   0.04161   0.03115  -0.0392   0.5839   1.0000
   5.000   0.5690   0.04242   0.03191  -0.0400   0.5669   1.0000
   5.500   0.6172   0.04316   0.03261  -0.0406   0.5498   1.0000
   5.750   0.6299   0.04433   0.03377  -0.0401   0.5376   1.0000
   6.000   0.6660   0.04373   0.03315  -0.0407   0.5328   1.0000
   6.250   0.6769   0.04506   0.03450  -0.0401   0.5202   1.0000
   6.500   0.7145   0.04427   0.03369  -0.0406   0.5158   1.0000
   6.750   0.7247   0.04563   0.03506  -0.0398   0.5029   1.0000
   7.000   0.7656   0.04443   0.03386  -0.0402   0.4987   1.0000
   7.250   0.7765   0.04560   0.03503  -0.0392   0.4852   1.0000
   7.750   0.8344   0.04473   0.03415  -0.0385   0.4665   1.0000
   8.000   0.8510   0.04540   0.03483  -0.0377   0.4544   1.0000
   8.250   0.8917   0.04404   0.03342  -0.0378   0.4473   1.0000
   8.500   0.9002   0.04553   0.03495  -0.0368   0.4345   1.0000
   8.750   0.9434   0.04410   0.03347  -0.0370   0.4277   1.0000
   9.000   0.9441   0.04624   0.03567  -0.0357   0.4142   1.0000
   9.250   0.9754   0.04583   0.03524  -0.0354   0.4057   1.0000
   9.500   0.9815   0.04754   0.03701  -0.0343   0.3936   1.0000
   9.750   0.9845   0.04960   0.03913  -0.0333   0.3817   1.0000
  10.000   1.0164   0.04900   0.03849  -0.0329   0.3732   1.0000
  10.250   1.0090   0.05201   0.04162  -0.0317   0.3607   1.0000
  10.500   1.0202   0.05338   0.04302  -0.0310   0.3508   1.0000
  10.750   1.0448   0.05337   0.04299  -0.0304   0.3421   1.0000
  11.000   1.0490   0.05546   0.04515  -0.0296   0.3319   1.0000
  11.250   1.0864   0.05426   0.04387  -0.0293   0.3245   1.0000
  11.500   1.0823   0.05727   0.04699  -0.0284   0.3144   1.0000
  11.750   1.1234   0.05586   0.04545  -0.0282   0.3073   1.0000
  12.000   1.1096   0.05991   0.04968  -0.0273   0.2975   1.0000
  12.250   1.1461   0.05903   0.04871  -0.0270   0.2904   1.0000
  12.500   1.1279   0.06369   0.05358  -0.0264   0.2818   1.0000
  12.750   1.1458   0.06470   0.05462  -0.0259   0.2749   1.0000
  13.000   1.1492   0.06732   0.05732  -0.0256   0.2682   1.0000
  13.250   1.1258   0.07302   0.06322  -0.0257   0.2605   1.0000
  13.500   1.1625   0.07183   0.06200  -0.0250   0.2555   1.0000
  13.750   1.0729   0.08673   0.07724  -0.0277   0.2457   1.0000
  14.000   1.0830   0.08879   0.07936  -0.0277   0.2409   1.0000
  14.250   1.1295   0.08573   0.07630  -0.0262   0.2382   1.0000
  14.500   0.9972   0.11063   0.10144  -0.0349   0.2243   1.0000
  14.750   1.0290   0.10887   0.09973  -0.0335   0.2223   1.0000
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