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HQ 1.0/8 AIRFOIL (hq108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/8 AIRFOIL (hq108-il)
Reynolds number: 1,000,000
Max Cl/Cd: 72.19 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq108-il-1000000-n5.txt
Download as CSV file: xf-hq108-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.6066   0.08497   0.08343  -0.0103   1.0000   0.0015
  -9.500  -0.6209   0.07737   0.07587  -0.0150   1.0000   0.0015
  -9.250  -0.6368   0.06941   0.06794  -0.0213   1.0000   0.0015
  -8.750  -0.7702   0.02736   0.02455  -0.0342   1.0000   0.0015
  -8.500  -0.7603   0.02323   0.01994  -0.0330   1.0000   0.0015
  -8.250  -0.7415   0.02141   0.01788  -0.0323   1.0000   0.0016
  -8.000  -0.7219   0.01980   0.01603  -0.0315   1.0000   0.0017
  -7.750  -0.6999   0.01889   0.01498  -0.0308   1.0000   0.0017
  -7.500  -0.6854   0.01575   0.01135  -0.0292   1.0000   0.0019
  -7.250  -0.6640   0.01475   0.01022  -0.0283   1.0000   0.0021
  -7.000  -0.6352   0.01394   0.00928  -0.0289   0.9967   0.0022
  -6.750  -0.6047   0.01327   0.00852  -0.0299   0.9919   0.0024
  -6.500  -0.5736   0.01247   0.00760  -0.0309   0.9866   0.0025
  -6.250  -0.5427   0.01178   0.00679  -0.0318   0.9804   0.0027
  -6.000  -0.5109   0.01111   0.00601  -0.0329   0.9734   0.0030
  -5.750  -0.4801   0.01071   0.00555  -0.0338   0.9638   0.0034
  -5.500  -0.4502   0.01030   0.00508  -0.0343   0.9517   0.0037
  -5.250  -0.4225   0.00986   0.00454  -0.0343   0.9363   0.0039
  -5.000  -0.3972   0.00920   0.00370  -0.0338   0.9198   0.0046
  -4.500  -0.3453   0.00859   0.00291  -0.0330   0.8927   0.0066
  -4.250  -0.3188   0.00838   0.00260  -0.0327   0.8808   0.0076
  -4.000  -0.2921   0.00816   0.00230  -0.0324   0.8697   0.0099
  -3.750  -0.2654   0.00794   0.00206  -0.0322   0.8594   0.0142
  -3.500  -0.2386   0.00774   0.00185  -0.0320   0.8494   0.0248
  -3.250  -0.2116   0.00757   0.00168  -0.0318   0.8393   0.0356
  -3.000  -0.1845   0.00740   0.00152  -0.0317   0.8293   0.0504
  -2.750  -0.1576   0.00720   0.00135  -0.0316   0.8181   0.0752
  -2.500  -0.1311   0.00690   0.00120  -0.0314   0.8057   0.1238
  -2.250  -0.1043   0.00668   0.00107  -0.0313   0.7939   0.1689
  -1.750  -0.0503   0.00626   0.00085  -0.0312   0.7720   0.2621
  -1.500  -0.0244   0.00585   0.00072  -0.0311   0.7573   0.3668
  -1.250   0.0015   0.00550   0.00064  -0.0309   0.7410   0.4700
  -1.000   0.0285   0.00536   0.00059  -0.0308   0.7268   0.5198
  -0.750   0.0552   0.00518   0.00058  -0.0306   0.7124   0.5850
  -0.500   0.0822   0.00510   0.00057  -0.0304   0.6972   0.6290
  -0.250   0.1096   0.00510   0.00056  -0.0303   0.6800   0.6493
   0.000   0.1370   0.00513   0.00056  -0.0302   0.6624   0.6656
   0.250   0.1644   0.00514   0.00058  -0.0300   0.6471   0.6847
   0.500   0.1918   0.00515   0.00060  -0.0299   0.6309   0.7036
   0.750   0.2192   0.00517   0.00063  -0.0298   0.6135   0.7227
   1.000   0.2464   0.00523   0.00066  -0.0297   0.5912   0.7369
   1.250   0.2736   0.00534   0.00070  -0.0295   0.5626   0.7470
   1.500   0.3002   0.00551   0.00076  -0.0293   0.5201   0.7573
   1.750   0.3266   0.00574   0.00084  -0.0291   0.4699   0.7679
   2.000   0.3524   0.00604   0.00095  -0.0289   0.4087   0.7788
   2.250   0.3780   0.00638   0.00108  -0.0286   0.3413   0.7904
   2.500   0.4040   0.00665   0.00121  -0.0283   0.2921   0.8028
   2.750   0.4299   0.00692   0.00138  -0.0281   0.2492   0.8163
   3.000   0.4561   0.00711   0.00151  -0.0278   0.2207   0.8310
   3.250   0.4819   0.00734   0.00166  -0.0275   0.1860   0.8476
   3.500   0.5070   0.00759   0.00183  -0.0271   0.1469   0.8667
   3.750   0.5317   0.00778   0.00201  -0.0265   0.1192   0.8943
   4.000   0.5572   0.00797   0.00224  -0.0260   0.0900   0.9441
   4.250   0.5952   0.00839   0.00252  -0.0286   0.0535   1.0000
   4.500   0.6214   0.00867   0.00274  -0.0284   0.0402   1.0000
   4.750   0.6473   0.00899   0.00300  -0.0281   0.0261   1.0000
   5.000   0.6729   0.00936   0.00329  -0.0278   0.0141   1.0000
   5.250   0.6988   0.00968   0.00360  -0.0276   0.0077   1.0000
   5.500   0.7245   0.01005   0.00396  -0.0273   0.0046   1.0000
   5.750   0.7499   0.01049   0.00447  -0.0269   0.0030   1.0000
   6.000   0.7752   0.01097   0.00503  -0.0264   0.0027   1.0000
   6.250   0.8005   0.01141   0.00554  -0.0260   0.0026   1.0000
   6.500   0.8253   0.01193   0.00615  -0.0256   0.0025   1.0000
   6.750   0.8497   0.01254   0.00684  -0.0250   0.0024   1.0000
   7.000   0.8737   0.01318   0.00759  -0.0244   0.0023   1.0000
   7.250   0.8972   0.01391   0.00841  -0.0238   0.0022   1.0000
   7.500   0.9210   0.01455   0.00914  -0.0233   0.0020   1.0000
   7.750   0.9450   0.01510   0.00975  -0.0228   0.0018   1.0000
   8.000   0.9675   0.01595   0.01075  -0.0221   0.0017   1.0000
   8.250   0.9894   0.01689   0.01182  -0.0213   0.0017   1.0000
   8.500   1.0114   0.01778   0.01282  -0.0206   0.0016   1.0000
   8.750   1.0319   0.01892   0.01412  -0.0197   0.0015   1.0000
   9.000   1.0524   0.02001   0.01534  -0.0189   0.0015   1.0000
   9.250   1.0723   0.02111   0.01658  -0.0180   0.0014   1.0000
   9.500   1.0918   0.02220   0.01781  -0.0171   0.0014   1.0000
   9.750   1.1099   0.02344   0.01921  -0.0161   0.0013   1.0000
  10.000   1.1259   0.02492   0.02087  -0.0149   0.0012   1.0000
  10.250   1.1383   0.02683   0.02300  -0.0134   0.0012   1.0000
  10.500   1.1413   0.02983   0.02635  -0.0111   0.0011   1.0000
  10.750   1.1440   0.03246   0.02929  -0.0088   0.0011   1.0000
  11.000   1.1116   0.03779   0.03507  -0.0034   0.0010   1.0000
  11.250   1.1087   0.03963   0.03707  -0.0011   0.0010   1.0000
  11.500   1.0791   0.04438   0.04205   0.0008   0.0010   1.0000
  11.750   1.0554   0.04958   0.04746  -0.0001   0.0010   1.0000
  12.250   1.0289   0.06057   0.05871  -0.0066   0.0010   1.0000
  12.500   1.0121   0.06943   0.06771  -0.0136   0.0010   1.0000
  12.750   1.0156   0.07437   0.07270  -0.0172   0.0011   1.0000
  13.000   0.9969   0.08594   0.08437  -0.0243   0.0011   1.0000
  13.250   0.9762   0.09655   0.09503  -0.0297   0.0011   1.0000
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