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HQ 3.5/8 AIRFOIL (hq358-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/8 AIRFOIL (hq358-il)
Reynolds number: 1,000,000
Max Cl/Cd: 109.61 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq358-il-1000000-n5.txt
Download as CSV file: xf-hq358-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3380   0.10767   0.10600  -0.0312   1.0000   0.0033
  -9.250  -0.3351   0.10472   0.10307  -0.0316   1.0000   0.0033
  -9.000  -0.3327   0.10196   0.10033  -0.0319   1.0000   0.0034
  -8.750  -0.3214   0.09796   0.09633  -0.0351   0.9987   0.0034
  -8.500  -0.3106   0.09430   0.09267  -0.0379   0.9934   0.0034
  -8.250  -0.2989   0.09051   0.08890  -0.0412   0.9888   0.0034
  -8.000  -0.2857   0.08668   0.08507  -0.0450   0.9845   0.0034
  -7.750  -0.2717   0.08268   0.08107  -0.0492   0.9790   0.0034
  -7.500  -0.2532   0.07834   0.07673  -0.0548   0.9749   0.0034
  -7.250  -0.2337   0.07375   0.07214  -0.0612   0.9678   0.0034
  -7.000  -0.2112   0.06903   0.06740  -0.0687   0.9594   0.0034
  -6.750  -0.1889   0.06413   0.06247  -0.0767   0.9470   0.0034
  -6.500  -0.1712   0.05976   0.05804  -0.0833   0.9318   0.0034
  -6.250  -0.1560   0.05503   0.05323  -0.0893   0.9170   0.0034
  -6.000  -0.1400   0.05101   0.04911  -0.0934   0.9051   0.0034
  -5.500  -0.1041   0.04308   0.04093  -0.0995   0.8857   0.0034
  -5.250  -0.0836   0.03912   0.03680  -0.1018   0.8778   0.0034
  -5.000  -0.0613   0.03546   0.03297  -0.1036   0.8702   0.0034
  -4.750  -0.0376   0.03188   0.02919  -0.1049   0.8635   0.0034
  -4.500  -0.0129   0.02852   0.02562  -0.1059   0.8568   0.0034
  -4.250   0.0129   0.02534   0.02221  -0.1065   0.8507   0.0034
  -4.000   0.0393   0.02221   0.01881  -0.1069   0.8443   0.0033
  -3.750   0.0660   0.01842   0.01464  -0.1073   0.8385   0.0030
  -3.500   0.0939   0.01531   0.01116  -0.1072   0.8324   0.0027
  -3.250   0.1221   0.01296   0.00846  -0.1069   0.8267   0.0024
  -3.000   0.1503   0.01121   0.00643  -0.1066   0.8196   0.0023
  -2.750   0.1778   0.00994   0.00492  -0.1062   0.8095   0.0023
  -2.500   0.2050   0.00904   0.00383  -0.1058   0.7957   0.0023
  -2.250   0.2320   0.00840   0.00302  -0.1054   0.7801   0.0026
  -2.000   0.2594   0.00810   0.00261  -0.1052   0.7678   0.0032
  -1.750   0.2867   0.00767   0.00206  -0.1051   0.7560   0.0041
  -1.500   0.3142   0.00737   0.00168  -0.1051   0.7444   0.0049
  -1.250   0.3417   0.00722   0.00148  -0.1050   0.7332   0.0066
  -1.000   0.3694   0.00706   0.00121  -0.1049   0.7210   0.0066
  -0.750   0.3969   0.00699   0.00102  -0.1048   0.7052   0.0064
  -0.500   0.4242   0.00698   0.00088  -0.1046   0.6877   0.0062
  -0.250   0.4517   0.00698   0.00080  -0.1044   0.6728   0.0061
   0.000   0.4790   0.00700   0.00076  -0.1043   0.6579   0.0061
   0.250   0.5061   0.00706   0.00073  -0.1042   0.6412   0.0062
   0.500   0.5333   0.00711   0.00069  -0.1041   0.6248   0.0058
   0.750   0.5602   0.00719   0.00067  -0.1039   0.6057   0.0065
   1.000   0.5865   0.00628   0.00079  -0.1044   0.5810   0.4746
   1.250   0.6116   0.00603   0.00097  -0.1042   0.5533   0.6686
   1.500   0.6366   0.00608   0.00111  -0.1036   0.5234   0.7456
   1.750   0.6622   0.00631   0.00122  -0.1033   0.4875   0.7569
   2.000   0.6876   0.00655   0.00135  -0.1029   0.4520   0.7689
   2.250   0.7132   0.00678   0.00148  -0.1026   0.4194   0.7818
   2.500   0.7384   0.00704   0.00162  -0.1022   0.3845   0.7964
   2.750   0.7632   0.00730   0.00177  -0.1018   0.3474   0.8138
   3.000   0.7876   0.00756   0.00194  -0.1012   0.3106   0.8372
   3.250   0.8105   0.00766   0.00212  -0.1003   0.2860   0.8872
   3.500   0.8391   0.00774   0.00226  -0.1005   0.2687   1.0000
   3.750   0.8653   0.00796   0.00241  -0.1004   0.2543   1.0000
   4.000   0.8913   0.00820   0.00258  -0.1002   0.2388   1.0000
   4.250   0.9174   0.00842   0.00275  -0.1000   0.2253   1.0000
   4.500   0.9437   0.00861   0.00295  -0.0998   0.2146   1.0000
   4.750   0.9666   0.00917   0.00323  -0.0992   0.1639   1.0000
   5.000   0.9877   0.00995   0.00366  -0.0983   0.1024   1.0000
   5.250   1.0086   0.01075   0.00415  -0.0974   0.0488   1.0000
   5.500   1.0302   0.01151   0.00469  -0.0965   0.0121   1.0000
   5.750   1.0540   0.01198   0.00512  -0.0959   0.0024   1.0000
   6.000   1.0786   0.01234   0.00552  -0.0955   0.0015   1.0000
   6.250   1.1033   0.01269   0.00591  -0.0950   0.0011   1.0000
   6.500   1.1278   0.01305   0.00633  -0.0945   0.0009   1.0000
   6.750   1.1519   0.01344   0.00678  -0.0940   0.0008   1.0000
   7.000   1.1757   0.01384   0.00723  -0.0935   0.0007   1.0000
   7.250   1.1989   0.01431   0.00776  -0.0928   0.0005   1.0000
   7.500   1.2211   0.01490   0.00844  -0.0919   0.0004   1.0000
   7.750   1.2427   0.01556   0.00920  -0.0910   0.0004   1.0000
   8.000   1.2632   0.01632   0.01007  -0.0898   0.0003   1.0000
   8.250   1.2826   0.01718   0.01109  -0.0885   0.0003   1.0000
   8.500   1.3011   0.01811   0.01215  -0.0871   0.0003   1.0000
   8.750   1.3175   0.01923   0.01341  -0.0853   0.0003   1.0000
   9.000   1.3322   0.02047   0.01480  -0.0833   0.0003   1.0000
   9.250   1.3457   0.02178   0.01627  -0.0812   0.0003   1.0000
   9.500   1.3561   0.02336   0.01804  -0.0786   0.0003   1.0000
   9.750   1.3651   0.02500   0.01986  -0.0759   0.0003   1.0000
  10.000   1.3700   0.02672   0.02177  -0.0725   0.0003   1.0000
  10.250   1.3713   0.02876   0.02402  -0.0687   0.0003   1.0000
  10.500   1.3714   0.03092   0.02640  -0.0651   0.0003   1.0000
  10.750   1.3691   0.03334   0.02906  -0.0616   0.0003   1.0000
  11.000   1.3639   0.03611   0.03207  -0.0582   0.0003   1.0000
  11.250   1.3553   0.03927   0.03548  -0.0550   0.0003   1.0000
  11.500   1.3468   0.04246   0.03890  -0.0524   0.0004   1.0000
  11.750   1.3343   0.04624   0.04291  -0.0503   0.0004   1.0000
  12.000   1.3192   0.05059   0.04749  -0.0488   0.0004   1.0000
  12.250   1.3039   0.05525   0.05236  -0.0483   0.0004   1.0000
  12.500   1.2868   0.06056   0.05787  -0.0487   0.0004   1.0000
  12.750   1.2699   0.06637   0.06387  -0.0502   0.0004   1.0000
  13.000   1.2525   0.07285   0.07053  -0.0528   0.0004   1.0000
  13.250   1.2363   0.07986   0.07769  -0.0563   0.0004   1.0000
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