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HQ 2.0/8 AIRFOIL (hq208-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.0/8 AIRFOIL (hq208-il)
Reynolds number: 500,000
Max Cl/Cd: 83.39 at α=2.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq208-il-500000-n5.txt
Download as CSV file: xf-hq208-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/8 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4561   0.07970   0.07752  -0.0270   1.0000   0.0060
  -8.000  -0.4608   0.07553   0.07338  -0.0290   1.0000   0.0058
  -7.750  -0.4681   0.07165   0.06956  -0.0309   1.0000   0.0057
  -7.500  -0.4701   0.06630   0.06423  -0.0368   1.0000   0.0056
  -7.250  -0.4713   0.06068   0.05858  -0.0414   1.0000   0.0054
  -7.000  -0.4684   0.05549   0.05331  -0.0445   0.9991   0.0052
  -6.750  -0.4465   0.04802   0.04563  -0.0519   0.9903   0.0049
  -6.500  -0.4216   0.04062   0.03791  -0.0577   0.9836   0.0047
  -6.250  -0.3964   0.03309   0.02994  -0.0614   0.9756   0.0043
  -6.000  -0.3729   0.02265   0.01859  -0.0632   0.9663   0.0039
  -5.750  -0.3444   0.01828   0.01358  -0.0641   0.9600   0.0039
  -5.500  -0.3170   0.01605   0.01097  -0.0643   0.9516   0.0040
  -5.250  -0.2881   0.01449   0.00912  -0.0646   0.9446   0.0042
  -5.000  -0.2604   0.01330   0.00772  -0.0646   0.9361   0.0046
  -4.750  -0.2331   0.01232   0.00656  -0.0645   0.9278   0.0053
  -4.250  -0.1789   0.01110   0.00505  -0.0641   0.9112   0.0064
  -4.000  -0.1531   0.01027   0.00412  -0.0639   0.9032   0.0085
  -3.750  -0.1263   0.00981   0.00356  -0.0636   0.8951   0.0098
  -3.500  -0.0994   0.00943   0.00307  -0.0633   0.8874   0.0112
  -3.250  -0.0723   0.00916   0.00268  -0.0631   0.8799   0.0123
  -3.000  -0.0452   0.00881   0.00228  -0.0629   0.8723   0.0193
  -2.500   0.0091   0.00836   0.00185  -0.0626   0.8574   0.0560
  -2.250   0.0362   0.00816   0.00168  -0.0625   0.8500   0.0821
  -2.000   0.0625   0.00766   0.00152  -0.0625   0.8416   0.1835
  -1.750   0.0878   0.00686   0.00134  -0.0625   0.8333   0.3831
  -1.500   0.1140   0.00652   0.00124  -0.0623   0.8245   0.4862
  -1.250   0.1406   0.00635   0.00120  -0.0621   0.8130   0.5451
  -1.000   0.1668   0.00621   0.00118  -0.0616   0.7992   0.6077
  -0.750   0.1927   0.00609   0.00118  -0.0611   0.7849   0.6684
  -0.500   0.2190   0.00603   0.00117  -0.0606   0.7717   0.7060
  -0.250   0.2457   0.00602   0.00116  -0.0602   0.7580   0.7298
   0.000   0.2724   0.00602   0.00114  -0.0599   0.7436   0.7481
   0.250   0.2994   0.00605   0.00113  -0.0596   0.7276   0.7600
   0.500   0.3265   0.00608   0.00113  -0.0594   0.7111   0.7714
   0.750   0.3535   0.00612   0.00114  -0.0591   0.6964   0.7835
   1.250   0.4069   0.00621   0.00118  -0.0585   0.6635   0.8096
   1.500   0.4332   0.00625   0.00123  -0.0581   0.6457   0.8245
   1.750   0.4592   0.00630   0.00128  -0.0576   0.6250   0.8418
   2.000   0.4844   0.00636   0.00134  -0.0570   0.6004   0.8634
   2.250   0.5087   0.00642   0.00140  -0.0561   0.5722   0.8968
   2.500   0.5429   0.00654   0.00147  -0.0575   0.5325   0.9705
   2.750   0.5704   0.00684   0.00161  -0.0576   0.4874   1.0000
   3.000   0.5945   0.00730   0.00179  -0.0571   0.4225   1.0000
   3.250   0.6172   0.00796   0.00204  -0.0564   0.3332   1.0000
   3.500   0.6412   0.00851   0.00229  -0.0560   0.2707   1.0000
   3.750   0.6667   0.00886   0.00252  -0.0557   0.2407   1.0000
   4.000   0.6923   0.00920   0.00277  -0.0555   0.2113   1.0000
   4.250   0.7178   0.00955   0.00301  -0.0552   0.1805   1.0000
   4.500   0.7427   0.00997   0.00327  -0.0549   0.1440   1.0000
   4.750   0.7659   0.01064   0.00366  -0.0544   0.0886   1.0000
   5.000   0.7893   0.01129   0.00409  -0.0539   0.0492   1.0000
   5.250   0.8138   0.01177   0.00446  -0.0535   0.0313   1.0000
   5.500   0.8387   0.01218   0.00485  -0.0531   0.0201   1.0000
   5.750   0.8636   0.01260   0.00524  -0.0527   0.0117   1.0000
   6.000   0.8879   0.01311   0.00574  -0.0522   0.0058   1.0000
   6.250   0.9121   0.01364   0.00631  -0.0516   0.0043   1.0000
   6.500   0.9363   0.01416   0.00693  -0.0511   0.0033   1.0000
   6.750   0.9603   0.01469   0.00756  -0.0505   0.0031   1.0000
   7.000   0.9838   0.01529   0.00828  -0.0499   0.0028   1.0000
   7.250   1.0067   0.01599   0.00913  -0.0491   0.0025   1.0000
   7.500   1.0285   0.01683   0.01011  -0.0482   0.0022   1.0000
   7.750   1.0499   0.01769   0.01109  -0.0473   0.0021   1.0000
   8.000   1.0703   0.01868   0.01222  -0.0463   0.0020   1.0000
   8.250   1.0897   0.01980   0.01349  -0.0451   0.0019   1.0000
   8.500   1.1080   0.02105   0.01490  -0.0438   0.0019   1.0000
   8.750   1.1255   0.02239   0.01641  -0.0424   0.0018   1.0000
   9.000   1.1418   0.02390   0.01810  -0.0410   0.0018   1.0000
   9.250   1.1567   0.02556   0.01997  -0.0394   0.0017   1.0000
   9.500   1.1703   0.02732   0.02196  -0.0377   0.0017   1.0000
   9.750   1.1812   0.02936   0.02425  -0.0357   0.0017   1.0000
  10.000   1.1900   0.03146   0.02661  -0.0336   0.0017   1.0000
  10.250   1.1948   0.03381   0.02929  -0.0312   0.0017   1.0000
  10.500   1.1924   0.03627   0.03202  -0.0279   0.0017   1.0000
  10.750   1.1861   0.03878   0.03478  -0.0245   0.0017   1.0000
  11.000   1.1776   0.04153   0.03778  -0.0217   0.0017   1.0000
  11.250   1.1654   0.04486   0.04135  -0.0197   0.0017   1.0000
  11.500   1.1523   0.04861   0.04533  -0.0187   0.0017   1.0000
  11.750   1.1360   0.05317   0.05012  -0.0189   0.0017   1.0000
  12.000   1.1192   0.05846   0.05562  -0.0204   0.0018   1.0000
  12.250   1.1008   0.06483   0.06218  -0.0235   0.0018   1.0000
  12.500   1.0813   0.07261   0.07016  -0.0284   0.0018   1.0000
  12.750   1.0602   0.08236   0.08009  -0.0353   0.0018   1.0000
  13.000   1.0395   0.09363   0.09149  -0.0429   0.0018   1.0000
  13.250   1.0161   0.10609   0.10403  -0.0502   0.0018   1.0000
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