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HQ 2.0/10 AIRFOIL (hq2010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/10 AIRFOIL (hq2010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.8 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2010-il-1000000-n5.txt
Download as CSV file: xf-hq2010-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/10 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
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.8680   0.04566   0.04362  -0.0594   1.0000   0.0023
 -12.500  -0.9011   0.03830   0.03603  -0.0645   1.0000   0.0023
 -12.250  -0.9252   0.03456   0.03209  -0.0639   1.0000   0.0022
 -12.000  -0.9308   0.03187   0.02922  -0.0625   1.0000   0.0023
 -11.750  -0.9296   0.02940   0.02652  -0.0613   1.0000   0.0023
 -11.500  -0.9211   0.02758   0.02454  -0.0602   1.0000   0.0024
 -11.250  -0.9078   0.02630   0.02315  -0.0591   1.0000   0.0025
 -11.000  -0.8944   0.02498   0.02170  -0.0580   1.0000   0.0025
 -10.750  -0.8790   0.02390   0.02051  -0.0568   1.0000   0.0026
 -10.500  -0.8589   0.02242   0.01885  -0.0569   0.9979   0.0027
 -10.250  -0.8324   0.02124   0.01754  -0.0579   0.9922   0.0028
 -10.000  -0.8039   0.02010   0.01625  -0.0592   0.9878   0.0029
  -9.750  -0.7749   0.01873   0.01469  -0.0606   0.9832   0.0030
  -9.500  -0.7457   0.01780   0.01361  -0.0617   0.9767   0.0032
  -9.250  -0.7158   0.01672   0.01237  -0.0630   0.9704   0.0033
  -9.000  -0.6873   0.01586   0.01136  -0.0638   0.9607   0.0035
  -8.750  -0.6596   0.01511   0.01049  -0.0643   0.9494   0.0036
  -8.500  -0.6336   0.01445   0.00969  -0.0643   0.9360   0.0037
  -8.250  -0.6083   0.01396   0.00909  -0.0640   0.9228   0.0038
  -8.000  -0.5851   0.01313   0.00809  -0.0635   0.9105   0.0040
  -7.750  -0.5609   0.01252   0.00736  -0.0630   0.9002   0.0043
  -7.500  -0.5357   0.01210   0.00684  -0.0627   0.8910   0.0046
  -7.250  -0.5099   0.01177   0.00645  -0.0624   0.8826   0.0050
  -6.750  -0.4580   0.01114   0.00567  -0.0619   0.8661   0.0058
  -6.500  -0.4320   0.01083   0.00527  -0.0616   0.8585   0.0061
  -6.250  -0.4055   0.01052   0.00489  -0.0614   0.8509   0.0063
  -6.000  -0.3796   0.01007   0.00434  -0.0611   0.8443   0.0068
  -5.750  -0.3531   0.00970   0.00389  -0.0609   0.8381   0.0075
  -5.500  -0.3263   0.00942   0.00356  -0.0608   0.8327   0.0082
  -5.250  -0.2991   0.00918   0.00328  -0.0607   0.8274   0.0091
  -5.000  -0.2719   0.00896   0.00301  -0.0606   0.8216   0.0098
  -4.750  -0.2447   0.00871   0.00273  -0.0605   0.8160   0.0121
  -4.500  -0.2173   0.00848   0.00249  -0.0604   0.8097   0.0160
  -4.250  -0.1901   0.00829   0.00229  -0.0604   0.8036   0.0222
  -4.000  -0.1625   0.00809   0.00212  -0.0603   0.7970   0.0297
  -3.750  -0.1350   0.00797   0.00196  -0.0603   0.7902   0.0342
  -3.500  -0.1073   0.00781   0.00181  -0.0603   0.7833   0.0418
  -3.250  -0.0797   0.00767   0.00167  -0.0602   0.7766   0.0500
  -3.000  -0.0519   0.00752   0.00154  -0.0602   0.7693   0.0622
  -2.750  -0.0246   0.00736   0.00141  -0.0602   0.7617   0.0830
  -2.500   0.0029   0.00715   0.00129  -0.0602   0.7530   0.1157
  -2.250   0.0301   0.00695   0.00117  -0.0601   0.7421   0.1552
  -2.000   0.0570   0.00672   0.00106  -0.0601   0.7291   0.2098
  -1.750   0.0841   0.00653   0.00097  -0.0600   0.7163   0.2578
  -1.500   0.1111   0.00631   0.00088  -0.0600   0.7041   0.3162
  -1.250   0.1376   0.00600   0.00080  -0.0599   0.6925   0.4093
  -1.000   0.1643   0.00576   0.00076  -0.0598   0.6793   0.4908
  -0.750   0.1915   0.00564   0.00076  -0.0597   0.6663   0.5425
  -0.500   0.2188   0.00557   0.00077  -0.0596   0.6537   0.5871
  -0.250   0.2462   0.00558   0.00078  -0.0595   0.6388   0.6121
   0.000   0.2737   0.00562   0.00079  -0.0594   0.6227   0.6284
   0.250   0.3015   0.00565   0.00081  -0.0593   0.6094   0.6422
   0.500   0.3291   0.00569   0.00084  -0.0593   0.5948   0.6563
   0.750   0.3565   0.00575   0.00087  -0.0592   0.5773   0.6722
   1.000   0.3838   0.00582   0.00091  -0.0590   0.5589   0.6845
   1.250   0.4113   0.00592   0.00096  -0.0590   0.5409   0.6924
   1.500   0.4384   0.00603   0.00102  -0.0588   0.5204   0.7003
   1.750   0.4655   0.00617   0.00109  -0.0587   0.4971   0.7076
   2.000   0.4921   0.00634   0.00117  -0.0585   0.4639   0.7158
   2.250   0.5178   0.00662   0.00129  -0.0582   0.4198   0.7237
   2.500   0.5441   0.00684   0.00142  -0.0579   0.3900   0.7324
   2.750   0.5699   0.00709   0.00156  -0.0577   0.3548   0.7410
   3.000   0.5952   0.00741   0.00173  -0.0573   0.3090   0.7499
   3.250   0.6203   0.00774   0.00191  -0.0569   0.2705   0.7593
   3.500   0.6460   0.00800   0.00208  -0.0566   0.2434   0.7689
   3.750   0.6723   0.00818   0.00222  -0.0564   0.2264   0.7787
   4.250   0.7254   0.00847   0.00253  -0.0560   0.2040   0.8007
   4.500   0.7512   0.00866   0.00269  -0.0557   0.1876   0.8129
   4.750   0.7760   0.00894   0.00290  -0.0553   0.1602   0.8266
   5.000   0.7993   0.00935   0.00317  -0.0546   0.1219   0.8432
   5.250   0.8219   0.00974   0.00349  -0.0538   0.0903   0.8643
   5.500   0.8429   0.01001   0.00378  -0.0525   0.0675   0.9107
   5.750   0.8755   0.01041   0.00413  -0.0539   0.0450   1.0000
   6.000   0.9004   0.01076   0.00442  -0.0535   0.0353   1.0000
   6.250   0.9256   0.01105   0.00468  -0.0531   0.0294   1.0000
   6.500   0.9503   0.01140   0.00501  -0.0527   0.0227   1.0000
   6.750   0.9749   0.01174   0.00533  -0.0523   0.0176   1.0000
   7.000   0.9983   0.01222   0.00573  -0.0517   0.0097   1.0000
   7.250   1.0214   0.01272   0.00621  -0.0510   0.0040   1.0000
   7.500   1.0453   0.01311   0.00663  -0.0505   0.0034   1.0000
   7.750   1.0688   0.01355   0.00711  -0.0499   0.0029   1.0000
   8.000   1.0920   0.01399   0.00762  -0.0492   0.0026   1.0000
   8.250   1.1149   0.01446   0.00815  -0.0485   0.0024   1.0000
   8.500   1.1379   0.01489   0.00862  -0.0479   0.0023   1.0000
   8.750   1.1603   0.01536   0.00914  -0.0471   0.0022   1.0000
   9.000   1.1823   0.01586   0.00970  -0.0464   0.0021   1.0000
   9.250   1.2037   0.01638   0.01027  -0.0455   0.0021   1.0000
   9.500   1.2244   0.01697   0.01092  -0.0445   0.0019   1.0000
   9.750   1.2445   0.01757   0.01161  -0.0435   0.0019   1.0000
  10.000   1.2637   0.01822   0.01233  -0.0424   0.0018   1.0000
  10.250   1.2822   0.01889   0.01307  -0.0411   0.0017   1.0000
  10.500   1.2995   0.01963   0.01388  -0.0398   0.0016   1.0000
  10.750   1.3157   0.02039   0.01472  -0.0382   0.0015   1.0000
  11.000   1.3300   0.02120   0.01562  -0.0364   0.0015   1.0000
  11.250   1.3411   0.02202   0.01652  -0.0341   0.0014   1.0000
  11.500   1.3493   0.02300   0.01759  -0.0314   0.0013   1.0000
  11.750   1.3559   0.02409   0.01878  -0.0288   0.0013   1.0000
  12.000   1.3597   0.02541   0.02021  -0.0260   0.0012   1.0000
  12.250   1.3651   0.02667   0.02160  -0.0237   0.0012   1.0000
  12.500   1.3663   0.02830   0.02336  -0.0212   0.0012   1.0000
  12.750   1.3694   0.02988   0.02505  -0.0192   0.0012   1.0000
  13.000   1.3498   0.03347   0.02888  -0.0161   0.0011   1.0000
  13.250   1.3439   0.03615   0.03171  -0.0145   0.0011   1.0000
  13.750   1.3385   0.04144   0.03725  -0.0129   0.0011   1.0000
  14.000   1.3334   0.04462   0.04057  -0.0126   0.0011   1.0000
  14.250   1.3283   0.04803   0.04411  -0.0128   0.0011   1.0000
  14.500   1.3199   0.05209   0.04830  -0.0136   0.0011   1.0000
  14.750   1.3091   0.05679   0.05316  -0.0149   0.0011   1.0000
  15.000   1.3002   0.06160   0.05810  -0.0168   0.0011   1.0000
  15.250   1.2791   0.06876   0.06544  -0.0201   0.0011   1.0000
  15.500   1.2708   0.07434   0.07114  -0.0229   0.0011   1.0000
  15.750   1.2474   0.08311   0.08008  -0.0278   0.0011   1.0000
  16.000   1.2296   0.09135   0.08847  -0.0324   0.0011   1.0000
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