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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 50,000
Max Cl/Cd: 40.61 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq308-il-50000.txt
Download as CSV file: xf-hq308-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/8 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3185   0.10440   0.09805  -0.0282   1.0000   0.1763
  -8.750  -0.3071   0.09994   0.09363  -0.0272   1.0000   0.1845
  -8.500  -0.3215   0.09861   0.09242  -0.0282   1.0000   0.1905
  -8.250  -0.3093   0.09417   0.08801  -0.0267   1.0000   0.2017
  -8.000  -0.3071   0.09079   0.08471  -0.0260   1.0000   0.2101
  -7.750  -0.3234   0.08953   0.08359  -0.0259   1.0000   0.2178
  -7.500  -0.3176   0.08589   0.08001  -0.0243   1.0000   0.2305
  -7.250  -0.3174   0.08287   0.07709  -0.0226   1.0000   0.2436
  -7.000  -0.3205   0.08025   0.07457  -0.0207   1.0000   0.2573
  -6.750  -0.3272   0.07798   0.07242  -0.0184   1.0000   0.2715
  -6.500  -0.4021   0.08579   0.07987  -0.0177   1.0000   0.2561
  -6.250  -0.4093   0.08382   0.07802  -0.0165   1.0000   0.2715
  -6.000  -0.4035   0.08087   0.07514  -0.0127   1.0000   0.2943
  -5.750  -0.4179   0.07959   0.07400  -0.0120   1.0000   0.3137
  -5.500  -0.4203   0.07756   0.07206  -0.0085   1.0000   0.3414
  -5.250  -0.4160   0.07536   0.06994  -0.0022   1.0000   0.3820
  -3.500  -0.3325   0.04775   0.04200  -0.0301   1.0000   0.3423
  -3.250  -0.2135   0.03661   0.02779  -0.0549   1.0000   0.1227
  -3.000  -0.1858   0.03326   0.02421  -0.0552   1.0000   0.1141
  -2.750  -0.1546   0.03110   0.02134  -0.0552   1.0000   0.1073
  -2.500  -0.1260   0.02897   0.01875  -0.0549   1.0000   0.1061
  -2.250  -0.0985   0.02725   0.01667  -0.0545   1.0000   0.1112
  -2.000  -0.0731   0.02591   0.01511  -0.0537   1.0000   0.1232
  -1.750  -0.0488   0.02447   0.01360  -0.0523   1.0000   0.1358
  -1.500  -0.0217   0.02286   0.01218  -0.0519   1.0000   0.1818
  -1.250  -0.0034   0.01898   0.01138  -0.0479   1.0000   0.7850
  -1.000   0.0131   0.01852   0.01040  -0.0447   1.0000   1.0000
  -0.750   0.0372   0.01883   0.01017  -0.0447   1.0000   1.0000
  -0.500   0.0605   0.01918   0.01005  -0.0448   1.0000   1.0000
  -0.250   0.0834   0.01957   0.01009  -0.0449   1.0000   1.0000
   0.000   0.1058   0.01999   0.01022  -0.0449   1.0000   1.0000
   0.250   0.1278   0.02046   0.01044  -0.0449   1.0000   1.0000
   0.500   0.1493   0.02096   0.01073  -0.0449   1.0000   1.0000
   0.750   0.1704   0.02151   0.01106  -0.0449   1.0000   1.0000
   1.000   0.1911   0.02209   0.01150  -0.0449   1.0000   1.0000
   1.250   0.2114   0.02273   0.01201  -0.0449   1.0000   1.0000
   1.500   0.2312   0.02341   0.01260  -0.0449   1.0000   1.0000
   1.750   0.2506   0.02415   0.01326  -0.0449   1.0000   1.0000
   2.000   0.2696   0.02495   0.01399  -0.0450   1.0000   1.0000
   2.250   0.2879   0.02582   0.01481  -0.0451   1.0000   1.0000
   2.500   0.3247   0.02711   0.01609  -0.0488   0.9899   1.0000
   2.750   0.3822   0.02873   0.01774  -0.0560   0.9696   1.0000
   3.000   0.4310   0.02994   0.01905  -0.0612   0.9473   1.0000
   3.250   0.4825   0.03104   0.02026  -0.0665   0.9250   1.0000
   3.500   0.5352   0.03192   0.02128  -0.0715   0.9022   1.0000
   3.750   0.5802   0.03253   0.02208  -0.0748   0.8773   1.0000
   4.000   0.6284   0.03288   0.02272  -0.0780   0.8514   1.0000
   4.250   0.6812   0.03275   0.02287  -0.0811   0.8240   1.0000
   4.500   0.7395   0.03197   0.02245  -0.0840   0.7959   1.0000
   4.750   0.7989   0.03055   0.02153  -0.0859   0.7679   1.0000
   5.000   0.8453   0.02915   0.02049  -0.0855   0.7363   1.0000
   5.250   0.8939   0.02721   0.01891  -0.0844   0.7008   1.0000
   5.500   0.9334   0.02561   0.01765  -0.0820   0.6562   1.0000
   5.750   0.9651   0.02463   0.01673  -0.0789   0.6012   1.0000
   6.000   0.9912   0.02441   0.01636  -0.0757   0.5388   1.0000
   6.250   1.0120   0.02500   0.01669  -0.0726   0.4747   1.0000
   6.500   1.0305   0.02604   0.01737  -0.0698   0.4129   1.0000
   6.750   1.0455   0.02740   0.01847  -0.0670   0.3531   1.0000
   7.000   1.0603   0.02908   0.01981  -0.0644   0.2949   1.0000
   7.250   1.0742   0.03114   0.02147  -0.0619   0.2381   1.0000
   7.500   1.0927   0.03388   0.02424  -0.0598   0.1918   1.0000
   7.750   1.1094   0.03630   0.02646  -0.0580   0.1562   1.0000
   8.000   1.1335   0.04018   0.03039  -0.0566   0.1309   1.0000
   8.250   1.1422   0.04246   0.03274  -0.0542   0.1040   1.0000
   8.500   1.1540   0.04573   0.03637  -0.0519   0.0876   1.0000
   8.750   1.1680   0.04957   0.04042  -0.0502   0.0782   1.0000
   9.000   1.1759   0.05325   0.04464  -0.0479   0.0722   1.0000
   9.250   1.1890   0.05807   0.04947  -0.0469   0.0678   1.0000
   9.500   1.1893   0.06270   0.05467  -0.0445   0.0674   1.0000
   9.750   1.1855   0.06750   0.05993  -0.0422   0.0674   1.0000
  10.000   1.1800   0.07242   0.06521  -0.0402   0.0676   1.0000
  10.250   1.1724   0.07751   0.07056  -0.0385   0.0679   1.0000
  10.500   1.1314   0.08032   0.07396  -0.0351   0.0700   1.0000
  10.750   1.0929   0.08560   0.07953  -0.0350   0.0722   1.0000
  11.000   1.0626   0.09197   0.08606  -0.0373   0.0743   1.0000
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