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HQ 3.0/8 AIRFOIL (hq308-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/8 AIRFOIL (hq308-il)
Reynolds number: 1,000,000
Max Cl/Cd: 135.39 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq308-il-1000000.txt
Download as CSV file: xf-hq308-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3668   0.08788   0.08631  -0.0322   1.0000   0.0056
  -8.000  -0.3682   0.08500   0.08346  -0.0323   1.0000   0.0056
  -7.750  -0.3744   0.08266   0.08117  -0.0312   1.0000   0.0056
  -7.500  -0.3717   0.07917   0.07770  -0.0334   0.9986   0.0056
  -7.250  -0.3515   0.07357   0.07211  -0.0417   0.9939   0.0056
  -7.000  -0.3288   0.06762   0.06615  -0.0513   0.9887   0.0057
  -6.750  -0.2989   0.06020   0.05869  -0.0646   0.9845   0.0057
  -6.500  -0.2669   0.05305   0.05142  -0.0756   0.9821   0.0057
  -6.250  -0.2403   0.04707   0.04530  -0.0826   0.9755   0.0057
  -6.000  -0.2144   0.03644   0.03434  -0.0920   0.9686   0.0060
  -5.750  -0.1945   0.03191   0.02957  -0.0940   0.9583   0.0063
  -5.500  -0.1723   0.02901   0.02646  -0.0949   0.9499   0.0066
  -5.250  -0.1494   0.02633   0.02357  -0.0954   0.9422   0.0070
  -5.000  -0.1264   0.02381   0.02082  -0.0953   0.9336   0.0079
  -4.750  -0.1010   0.02139   0.01815  -0.0949   0.9265   0.0092
  -3.500   0.0288   0.01062   0.00587  -0.0928   0.8920   0.0117
  -3.250   0.0561   0.00985   0.00499  -0.0923   0.8857   0.0099
  -3.000   0.0825   0.00862   0.00360  -0.0918   0.8786   0.0093
  -2.750   0.1094   0.00789   0.00272  -0.0915   0.8714   0.0091
  -2.500   0.1366   0.00740   0.00210  -0.0912   0.8629   0.0094
  -2.250   0.1642   0.00711   0.00171  -0.0910   0.8544   0.0104
  -2.000   0.1920   0.00682   0.00130  -0.0908   0.8472   0.0160
  -1.750   0.2197   0.00653   0.00115  -0.0908   0.8396   0.0602
  -1.500   0.2469   0.00615   0.00103  -0.0908   0.8316   0.1611
  -1.250   0.2729   0.00536   0.00091  -0.0910   0.8216   0.4114
  -1.000   0.2992   0.00493   0.00091  -0.0909   0.8110   0.5750
  -0.750   0.3264   0.00484   0.00090  -0.0907   0.8018   0.6289
  -0.500   0.3538   0.00481   0.00088  -0.0906   0.7931   0.6571
  -0.250   0.3812   0.00478   0.00089  -0.0904   0.7835   0.6863
   0.000   0.4082   0.00475   0.00091  -0.0901   0.7726   0.7237
   0.250   0.4345   0.00472   0.00094  -0.0897   0.7588   0.7636
   0.500   0.4614   0.00473   0.00094  -0.0894   0.7448   0.7816
   0.750   0.4886   0.00475   0.00095  -0.0892   0.7324   0.7948
   1.000   0.5156   0.00477   0.00097  -0.0890   0.7194   0.8092
   1.250   0.5424   0.00479   0.00099  -0.0887   0.7060   0.8262
   1.500   0.5687   0.00481   0.00102  -0.0884   0.6903   0.8473
   1.750   0.5936   0.00479   0.00106  -0.0876   0.6734   0.8816
   2.000   0.6248   0.00470   0.00107  -0.0883   0.6542   1.0000
   2.250   0.6516   0.00484   0.00112  -0.0881   0.6324   1.0000
   2.500   0.6783   0.00501   0.00119  -0.0879   0.6062   1.0000
   2.750   0.7044   0.00522   0.00130  -0.0876   0.5747   1.0000
   3.000   0.7300   0.00548   0.00141  -0.0873   0.5371   1.0000
   3.250   0.7541   0.00590   0.00158  -0.0867   0.4760   1.0000
   3.500   0.7776   0.00641   0.00179  -0.0860   0.4101   1.0000
   3.750   0.8024   0.00680   0.00198  -0.0856   0.3645   1.0000
   4.000   0.8264   0.00728   0.00223  -0.0851   0.3098   1.0000
   4.250   0.8501   0.00779   0.00249  -0.0846   0.2566   1.0000
   4.500   0.8738   0.00831   0.00276  -0.0841   0.2050   1.0000
   4.750   0.8982   0.00874   0.00302  -0.0836   0.1709   1.0000
   5.000   0.9227   0.00915   0.00330  -0.0832   0.1396   1.0000
   5.250   0.9463   0.00967   0.00364  -0.0827   0.1022   1.0000
   5.500   0.9680   0.01043   0.00410  -0.0819   0.0526   1.0000
   5.750   0.9904   0.01109   0.00458  -0.0811   0.0220   1.0000
   6.000   1.0134   0.01172   0.00508  -0.0804   0.0060   1.0000
   6.250   1.0378   0.01217   0.00560  -0.0797   0.0039   1.0000
   6.500   1.0621   0.01262   0.00614  -0.0791   0.0037   1.0000
   6.750   1.0858   0.01314   0.00675  -0.0784   0.0035   1.0000
   7.000   1.1089   0.01374   0.00748  -0.0776   0.0035   1.0000
   7.250   1.1309   0.01446   0.00832  -0.0766   0.0035   1.0000
   7.500   1.1515   0.01535   0.00935  -0.0753   0.0035   1.0000
   7.750   1.1708   0.01637   0.01051  -0.0739   0.0036   1.0000
   8.000   1.1878   0.01767   0.01196  -0.0721   0.0037   1.0000
   8.250   1.2017   0.01947   0.01395  -0.0698   0.0038   1.0000
   8.500   1.2158   0.02144   0.01607  -0.0677   0.0040   1.0000
   8.750   1.2336   0.02278   0.01753  -0.0662   0.0041   1.0000
   9.000   1.2481   0.02490   0.01984  -0.0643   0.0041   1.0000
   9.250   1.2640   0.02660   0.02170  -0.0627   0.0041   1.0000
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