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HQ 2.0/9 AIRFOIL (hq209-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/9 AIRFOIL (hq209-il)
Reynolds number: 1,000,000
Max Cl/Cd: 105.68 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq209-il-1000000.txt
Download as CSV file: xf-hq209-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/9 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4575   0.08311   0.08153  -0.0291   1.0000   0.0079
  -8.750  -0.4586   0.07872   0.07716  -0.0314   1.0000   0.0079
  -8.500  -0.4611   0.07412   0.07259  -0.0339   1.0000   0.0079
  -7.000  -0.4765   0.02073   0.01727  -0.0636   0.9829   0.0060
  -6.750  -0.4477   0.01890   0.01519  -0.0646   0.9770   0.0066
  -6.500  -0.4181   0.01674   0.01271  -0.0656   0.9714   0.0070
  -6.250  -0.3896   0.01521   0.01093  -0.0661   0.9641   0.0073
  -6.000  -0.3620   0.01379   0.00929  -0.0663   0.9560   0.0074
  -5.750  -0.3364   0.01285   0.00819  -0.0659   0.9459   0.0076
  -5.500  -0.3095   0.01257   0.00782  -0.0657   0.9367   0.0079
  -5.250  -0.2863   0.01099   0.00600  -0.0648   0.9271   0.0083
  -5.000  -0.2624   0.00990   0.00475  -0.0640   0.9174   0.0086
  -4.750  -0.2373   0.00916   0.00388  -0.0635   0.9091   0.0092
  -4.500  -0.2112   0.00875   0.00339  -0.0631   0.9012   0.0104
  -4.250  -0.1844   0.00843   0.00300  -0.0628   0.8936   0.0117
  -4.000  -0.1575   0.00822   0.00270  -0.0626   0.8865   0.0127
  -3.750  -0.1308   0.00778   0.00221  -0.0623   0.8791   0.0187
  -3.250  -0.0766   0.00732   0.00181  -0.0619   0.8648   0.0512
  -2.750  -0.0225   0.00688   0.00150  -0.0617   0.8494   0.1071
  -2.500   0.0038   0.00645   0.00133  -0.0616   0.8420   0.1951
  -2.250   0.0294   0.00583   0.00116  -0.0615   0.8339   0.3379
  -2.000   0.0551   0.00531   0.00106  -0.0614   0.8253   0.4819
  -1.750   0.0819   0.00512   0.00100  -0.0612   0.8159   0.5453
  -1.500   0.1093   0.00502   0.00096  -0.0610   0.8060   0.5832
  -1.250   0.1369   0.00496   0.00093  -0.0609   0.7966   0.6108
  -1.000   0.1644   0.00492   0.00091  -0.0607   0.7874   0.6399
  -0.750   0.1919   0.00490   0.00089  -0.0606   0.7770   0.6637
  -0.500   0.2194   0.00487   0.00089  -0.0604   0.7663   0.6861
  -0.250   0.2469   0.00486   0.00089  -0.0602   0.7553   0.7068
   0.000   0.2743   0.00487   0.00089  -0.0600   0.7438   0.7233
   0.250   0.3017   0.00488   0.00091  -0.0599   0.7330   0.7392
   0.500   0.3292   0.00489   0.00093  -0.0597   0.7218   0.7556
   0.750   0.3567   0.00491   0.00094  -0.0596   0.7094   0.7677
   1.000   0.3843   0.00494   0.00096  -0.0594   0.6965   0.7775
   1.250   0.4118   0.00499   0.00099  -0.0593   0.6829   0.7882
   1.500   0.4389   0.00503   0.00102  -0.0591   0.6678   0.7990
   2.000   0.4929   0.00514   0.00110  -0.0586   0.6333   0.8232
   2.250   0.5194   0.00521   0.00116  -0.0583   0.6120   0.8377
   2.500   0.5453   0.00529   0.00123  -0.0579   0.5862   0.8548
   2.750   0.5698   0.00542   0.00131  -0.0572   0.5475   0.8785
   3.000   0.5918   0.00560   0.00142  -0.0559   0.4893   0.9290
   3.250   0.6273   0.00604   0.00158  -0.0579   0.4144   1.0000
   3.500   0.6523   0.00642   0.00176  -0.0575   0.3639   1.0000
   3.750   0.6772   0.00682   0.00195  -0.0572   0.3138   1.0000
   4.000   0.7021   0.00722   0.00216  -0.0568   0.2710   1.0000
   4.250   0.7278   0.00752   0.00235  -0.0565   0.2457   1.0000
   4.500   0.7538   0.00779   0.00254  -0.0563   0.2247   1.0000
   4.750   0.7799   0.00804   0.00273  -0.0561   0.2047   1.0000
   5.000   0.8049   0.00841   0.00295  -0.0557   0.1712   1.0000
   5.250   0.8286   0.00894   0.00324  -0.0552   0.1261   1.0000
   5.500   0.8516   0.00955   0.00362  -0.0546   0.0818   1.0000
   5.750   0.8758   0.01002   0.00398  -0.0541   0.0584   1.0000
   6.000   0.9005   0.01040   0.00430  -0.0537   0.0454   1.0000
   6.250   0.9257   0.01073   0.00460  -0.0534   0.0375   1.0000
   6.500   0.9506   0.01109   0.00493  -0.0530   0.0304   1.0000
   6.750   0.9756   0.01143   0.00523  -0.0526   0.0235   1.0000
   7.000   0.9988   0.01199   0.00569  -0.0520   0.0106   1.0000
   7.250   1.0219   0.01257   0.00624  -0.0513   0.0059   1.0000
   7.500   1.0459   0.01303   0.00676  -0.0507   0.0049   1.0000
   7.750   1.0696   0.01350   0.00729  -0.0501   0.0046   1.0000
   8.000   1.0930   0.01401   0.00787  -0.0494   0.0044   1.0000
   8.250   1.1157   0.01457   0.00851  -0.0486   0.0042   1.0000
   8.500   1.1378   0.01518   0.00921  -0.0478   0.0039   1.0000
   8.750   1.1591   0.01588   0.00999  -0.0469   0.0037   1.0000
   9.000   1.1793   0.01667   0.01087  -0.0458   0.0034   1.0000
   9.250   1.1973   0.01770   0.01203  -0.0444   0.0031   1.0000
   9.500   1.2136   0.01884   0.01331  -0.0428   0.0030   1.0000
   9.750   1.2229   0.02074   0.01542  -0.0402   0.0028   1.0000
  10.000   1.2363   0.02208   0.01690  -0.0382   0.0028   1.0000
  10.250   1.2453   0.02385   0.01887  -0.0358   0.0028   1.0000
  10.500   1.2525   0.02573   0.02093  -0.0331   0.0028   1.0000
  10.750   1.2582   0.02735   0.02271  -0.0303   0.0028   1.0000
  11.000   1.2607   0.02894   0.02446  -0.0270   0.0028   1.0000
  11.250   1.2643   0.03037   0.02602  -0.0242   0.0028   1.0000
  11.500   1.2651   0.03209   0.02789  -0.0214   0.0028   1.0000
  11.750   1.2637   0.03410   0.03006  -0.0188   0.0028   1.0000
  12.000   1.2590   0.03652   0.03266  -0.0165   0.0029   1.0000
  12.250   1.2569   0.03877   0.03506  -0.0149   0.0029   1.0000
  12.500   1.2517   0.04149   0.03795  -0.0135   0.0029   1.0000
  12.750   1.2479   0.04425   0.04086  -0.0128   0.0030   1.0000
  13.000   1.2362   0.04820   0.04503  -0.0125   0.0030   1.0000
  13.250   1.2262   0.05228   0.04928  -0.0130   0.0030   1.0000
  13.500   1.2094   0.05779   0.05501  -0.0146   0.0031   1.0000
  13.750   1.1712   0.06766   0.06523  -0.0188   0.0034   1.0000
  14.000   1.1406   0.07756   0.07536  -0.0245   0.0035   1.0000
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