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HQ 1.5/8 AIRFOIL (hq158-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.5/8 AIRFOIL (hq158-il)
Reynolds number: 1,000,000
Max Cl/Cd: 77.48 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq158-il-1000000-n5.txt
Download as CSV file: xf-hq158-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.5/8 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5263   0.08272   0.08116  -0.0183   1.0000   0.0025
  -8.750  -0.5322   0.07736   0.07583  -0.0215   1.0000   0.0024
  -8.500  -0.5365   0.07266   0.07116  -0.0246   1.0000   0.0024
  -8.250  -0.5485   0.06703   0.06556  -0.0296   1.0000   0.0024
  -8.000  -0.5557   0.05923   0.05769  -0.0377   1.0000   0.0023
  -7.750  -0.5590   0.05263   0.05097  -0.0411   1.0000   0.0023
  -7.500  -0.5525   0.04459   0.04269  -0.0454   0.9887   0.0022
  -7.250  -0.5526   0.02411   0.02108  -0.0505   0.9647   0.0020
  -7.000  -0.5347   0.01797   0.01413  -0.0504   0.9476   0.0020
  -6.750  -0.5130   0.01528   0.01096  -0.0497   0.9304   0.0020
  -6.500  -0.4901   0.01375   0.00912  -0.0490   0.9146   0.0020
  -6.250  -0.4667   0.01254   0.00764  -0.0482   0.9005   0.0021
  -6.000  -0.4425   0.01163   0.00652  -0.0475   0.8877   0.0023
  -5.750  -0.4176   0.01096   0.00568  -0.0470   0.8760   0.0025
  -5.500  -0.3918   0.01056   0.00517  -0.0466   0.8648   0.0026
  -5.250  -0.3668   0.00980   0.00425  -0.0461   0.8543   0.0031
  -5.000  -0.3405   0.00948   0.00384  -0.0459   0.8447   0.0037
  -4.750  -0.3141   0.00919   0.00348  -0.0456   0.8352   0.0042
  -4.500  -0.2874   0.00890   0.00310  -0.0454   0.8258   0.0049
  -4.250  -0.2604   0.00870   0.00284  -0.0452   0.8167   0.0055
  -4.000  -0.2337   0.00840   0.00246  -0.0450   0.8077   0.0072
  -3.750  -0.2067   0.00817   0.00218  -0.0448   0.7983   0.0088
  -3.500  -0.1795   0.00799   0.00194  -0.0447   0.7892   0.0100
  -3.250  -0.1523   0.00782   0.00169  -0.0445   0.7781   0.0141
  -3.000  -0.1255   0.00762   0.00150  -0.0443   0.7639   0.0287
  -2.750  -0.0987   0.00753   0.00135  -0.0441   0.7446   0.0379
  -2.500  -0.0718   0.00743   0.00122  -0.0440   0.7244   0.0516
  -2.250  -0.0448   0.00733   0.00110  -0.0438   0.7074   0.0691
  -2.000  -0.0180   0.00707   0.00096  -0.0437   0.6950   0.1209
  -1.750   0.0083   0.00667   0.00084  -0.0437   0.6851   0.2164
  -1.500   0.0351   0.00644   0.00074  -0.0436   0.6719   0.2781
  -1.250   0.0614   0.00618   0.00066  -0.0435   0.6532   0.3594
  -1.000   0.0877   0.00595   0.00060  -0.0433   0.6341   0.4420
  -0.750   0.1139   0.00571   0.00057  -0.0432   0.6189   0.5312
  -0.500   0.1404   0.00559   0.00058  -0.0429   0.5999   0.5945
  -0.250   0.1669   0.00557   0.00060  -0.0427   0.5769   0.6404
   0.000   0.1938   0.00561   0.00062  -0.0425   0.5520   0.6653
   0.250   0.2206   0.00571   0.00065  -0.0423   0.5203   0.6843
   0.500   0.2472   0.00581   0.00069  -0.0421   0.4887   0.7041
   0.750   0.2738   0.00593   0.00075  -0.0419   0.4579   0.7222
   1.250   0.3274   0.00622   0.00088  -0.0416   0.3987   0.7444
   1.500   0.3542   0.00639   0.00095  -0.0414   0.3677   0.7550
   2.000   0.4072   0.00674   0.00113  -0.0410   0.3118   0.7778
   2.250   0.4341   0.00684   0.00126  -0.0409   0.3042   0.7900
   2.500   0.4607   0.00697   0.00140  -0.0407   0.2966   0.8031
   2.750   0.4882   0.00697   0.00147  -0.0405   0.2823   0.8170
   3.000   0.5142   0.00715   0.00155  -0.0403   0.2440   0.8323
   3.250   0.5399   0.00734   0.00169  -0.0399   0.2161   0.8491
   3.500   0.5648   0.00754   0.00186  -0.0394   0.1846   0.8702
   3.750   0.5890   0.00766   0.00202  -0.0387   0.1549   0.9146
   4.000   0.6284   0.00811   0.00230  -0.0416   0.1005   1.0000
   4.250   0.6528   0.00861   0.00259  -0.0412   0.0581   1.0000
   4.500   0.6787   0.00891   0.00282  -0.0409   0.0430   1.0000
   4.750   0.7044   0.00921   0.00306  -0.0406   0.0303   1.0000
   5.000   0.7302   0.00951   0.00334  -0.0404   0.0212   1.0000
   5.250   0.7556   0.00987   0.00364  -0.0400   0.0110   1.0000
   5.500   0.7805   0.01032   0.00404  -0.0396   0.0036   1.0000
   5.750   0.8063   0.01062   0.00438  -0.0393   0.0031   1.0000
   6.000   0.8317   0.01097   0.00476  -0.0389   0.0027   1.0000
   6.250   0.8569   0.01136   0.00521  -0.0385   0.0023   1.0000
   6.500   0.8806   0.01203   0.00601  -0.0378   0.0017   1.0000
   6.750   0.9054   0.01246   0.00652  -0.0373   0.0017   1.0000
   7.000   0.9295   0.01299   0.00712  -0.0368   0.0016   1.0000
   7.250   0.9531   0.01361   0.00783  -0.0361   0.0015   1.0000
   7.500   0.9759   0.01435   0.00867  -0.0354   0.0015   1.0000
   7.750   0.9979   0.01520   0.00964  -0.0345   0.0014   1.0000
   8.000   1.0193   0.01612   0.01070  -0.0335   0.0014   1.0000
   8.250   1.0397   0.01720   0.01193  -0.0324   0.0013   1.0000
   8.500   1.0593   0.01839   0.01328  -0.0313   0.0013   1.0000
   8.750   1.0778   0.01977   0.01484  -0.0300   0.0013   1.0000
   9.000   1.0954   0.02126   0.01652  -0.0286   0.0013   1.0000
   9.250   1.1114   0.02297   0.01849  -0.0271   0.0013   1.0000
   9.500   1.1248   0.02500   0.02077  -0.0253   0.0013   1.0000
   9.750   1.1356   0.02726   0.02332  -0.0234   0.0013   1.0000
  10.000   1.1432   0.02975   0.02608  -0.0211   0.0013   1.0000
  10.250   1.1479   0.03224   0.02885  -0.0188   0.0013   1.0000
  10.500   1.1433   0.03548   0.03240  -0.0156   0.0013   1.0000
  10.750   1.1332   0.03806   0.03520  -0.0117   0.0013   1.0000
  11.000   1.1199   0.04080   0.03813  -0.0084   0.0014   1.0000
  11.250   1.1040   0.04415   0.04168  -0.0063   0.0014   1.0000
  11.500   1.0838   0.04857   0.04630  -0.0058   0.0014   1.0000
  11.750   1.0644   0.05370   0.05161  -0.0071   0.0014   1.0000
  12.000   1.0432   0.06023   0.05831  -0.0106   0.0014   1.0000
  12.250   1.0246   0.06801   0.06624  -0.0161   0.0014   1.0000
  12.500   1.0047   0.07860   0.07697  -0.0242   0.0014   1.0000
  12.750   0.9888   0.08935   0.08782  -0.0312   0.0014   1.0000
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