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HQ 3.0/9 AIRFOIL (hq309-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/9 AIRFOIL (hq309-il)
Reynolds number: 100,000
Max Cl/Cd: 61.33 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq309-il-100000.txt
Download as CSV file: xf-hq309-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3689   0.09414   0.08941  -0.0348   1.0000   0.0756
  -8.000  -0.3755   0.09171   0.08708  -0.0356   1.0000   0.0779
  -7.750  -0.3904   0.08996   0.08547  -0.0361   1.0000   0.0792
  -7.500  -0.4090   0.08819   0.08384  -0.0373   1.0000   0.0798
  -7.250  -0.4251   0.08557   0.08129  -0.0414   1.0000   0.0802
  -7.000  -0.4393   0.08336   0.07900  -0.0439   1.0000   0.0805
  -6.750  -0.4254   0.07891   0.07478  -0.0348   1.0000   0.0831
  -6.500  -0.4264   0.07661   0.07252  -0.0324   1.0000   0.0853
  -6.250  -0.4300   0.07386   0.06980  -0.0324   1.0000   0.0879
  -6.000  -0.4331   0.07047   0.06636  -0.0358   1.0000   0.0920
  -5.750  -0.4339   0.06606   0.06176  -0.0408   1.0000   0.0955
  -5.500  -0.4288   0.06336   0.05919  -0.0372   1.0000   0.0983
  -5.250  -0.4199   0.06032   0.05602  -0.0390   1.0000   0.1059
  -5.000  -0.4108   0.05639   0.05199  -0.0404   1.0000   0.1113
  -4.750  -0.3955   0.05318   0.04848  -0.0433   1.0000   0.1233
  -4.500  -0.3849   0.05042   0.04585  -0.0414   1.0000   0.1298
  -4.250  -0.3681   0.04741   0.04262  -0.0435   1.0000   0.1520
  -4.000  -0.3546   0.04505   0.04032  -0.0426   1.0000   0.1704
  -3.750  -0.3389   0.04276   0.03796  -0.0425   1.0000   0.1997
  -3.250  -0.2329   0.03005   0.02257  -0.0499   1.0000   0.0647
  -3.000  -0.2050   0.02731   0.01943  -0.0500   1.0000   0.0605
  -2.750  -0.1773   0.02527   0.01691  -0.0497   1.0000   0.0586
  -2.500  -0.1432   0.02371   0.01503  -0.0506   0.9976   0.0611
  -2.250  -0.1033   0.02239   0.01349  -0.0528   0.9932   0.0710
  -2.000  -0.0660   0.02099   0.01211  -0.0543   0.9883   0.0855
  -1.750  -0.0268   0.01996   0.01123  -0.0568   0.9836   0.1353
  -1.500   0.0043   0.01740   0.01099  -0.0578   0.9801   0.6352
  -1.250   0.0215   0.01730   0.01131  -0.0536   0.9722   0.8265
  -1.000   0.0627   0.01704   0.01107  -0.0556   0.9649   1.0000
  -0.750   0.1061   0.01742   0.01111  -0.0595   0.9574   1.0000
  -0.500   0.1441   0.01774   0.01115  -0.0622   0.9487   1.0000
  -0.250   0.1904   0.01812   0.01128  -0.0664   0.9420   1.0000
   0.000   0.2237   0.01839   0.01138  -0.0681   0.9322   1.0000
   0.250   0.2627   0.01869   0.01151  -0.0707   0.9238   1.0000
   0.500   0.3046   0.01893   0.01163  -0.0737   0.9159   1.0000
   0.750   0.3376   0.01919   0.01179  -0.0751   0.9058   1.0000
   1.000   0.3788   0.01938   0.01190  -0.0778   0.8978   1.0000
   1.250   0.4193   0.01947   0.01195  -0.0802   0.8887   1.0000
   1.500   0.4572   0.01947   0.01193  -0.0819   0.8772   1.0000
   1.750   0.4995   0.01933   0.01179  -0.0843   0.8664   1.0000
   2.000   0.5523   0.01891   0.01139  -0.0881   0.8597   1.0000
   2.250   0.5856   0.01880   0.01131  -0.0887   0.8477   1.0000
   2.500   0.6196   0.01863   0.01117  -0.0892   0.8359   1.0000
   2.750   0.6546   0.01833   0.01096  -0.0897   0.8238   1.0000
   3.000   0.6892   0.01795   0.01063  -0.0899   0.8110   1.0000
   3.250   0.7224   0.01755   0.01029  -0.0897   0.7974   1.0000
   3.500   0.7542   0.01717   0.00998  -0.0893   0.7828   1.0000
   3.750   0.7853   0.01677   0.00970  -0.0888   0.7672   1.0000
   4.000   0.8165   0.01636   0.00934  -0.0881   0.7506   1.0000
   4.250   0.8426   0.01614   0.00921  -0.0868   0.7291   1.0000
   4.500   0.8711   0.01583   0.00894  -0.0858   0.7066   1.0000
   4.750   0.8972   0.01564   0.00883  -0.0844   0.6793   1.0000
   5.000   0.9216   0.01557   0.00879  -0.0828   0.6461   1.0000
   5.250   0.9454   0.01560   0.00878  -0.0812   0.6070   1.0000
   5.500   0.9678   0.01578   0.00886  -0.0794   0.5605   1.0000
   5.750   0.9882   0.01621   0.00909  -0.0775   0.5078   1.0000
   6.000   1.0072   0.01689   0.00956  -0.0756   0.4545   1.0000
   6.250   1.0252   0.01775   0.01013  -0.0737   0.4056   1.0000
   6.500   1.0428   0.01863   0.01084  -0.0720   0.3603   1.0000
   6.750   1.0601   0.01954   0.01158  -0.0703   0.3203   1.0000
   7.000   1.0772   0.02050   0.01240  -0.0687   0.2838   1.0000
   7.250   1.0940   0.02151   0.01332  -0.0670   0.2488   1.0000
   7.500   1.1094   0.02261   0.01438  -0.0652   0.2146   1.0000
   7.750   1.1228   0.02385   0.01552  -0.0632   0.1769   1.0000
   8.000   1.1351   0.02544   0.01690  -0.0610   0.1434   1.0000
   8.250   1.1481   0.02696   0.01833  -0.0590   0.1167   1.0000
   8.500   1.1588   0.02826   0.01954  -0.0570   0.0938   1.0000
   8.750   1.1698   0.02960   0.02094  -0.0550   0.0721   1.0000
   9.000   1.1763   0.03207   0.02336  -0.0522   0.0533   1.0000
   9.250   1.1887   0.03524   0.02654  -0.0501   0.0425   1.0000
   9.500   1.2074   0.03799   0.02948  -0.0487   0.0373   1.0000
   9.750   1.2310   0.04278   0.03434  -0.0487   0.0340   1.0000
  10.000   1.2415   0.04550   0.03751  -0.0465   0.0325   1.0000
  10.250   1.2472   0.04828   0.04080  -0.0440   0.0308   1.0000
  10.500   1.2484   0.05124   0.04415  -0.0412   0.0294   1.0000
  10.750   1.2443   0.05439   0.04765  -0.0382   0.0288   1.0000
  11.000   1.2355   0.05775   0.05135  -0.0352   0.0285   1.0000
  11.250   1.2222   0.06150   0.05544  -0.0326   0.0287   1.0000
  11.500   1.2057   0.06556   0.05982  -0.0306   0.0288   1.0000
  11.750   1.1872   0.06999   0.06454  -0.0296   0.0290   1.0000
  12.000   1.1669   0.07496   0.06977  -0.0297   0.0293   1.0000
  12.250   1.1451   0.08053   0.07558  -0.0309   0.0295   1.0000
  12.500   1.1228   0.08674   0.08201  -0.0333   0.0299   1.0000
  12.750   1.0994   0.09388   0.08933  -0.0371   0.0303   1.0000
  13.000   1.0756   0.10207   0.09761  -0.0422   0.0309   1.0000
  13.250   1.0530   0.11118   0.10683  -0.0481   0.0319   1.0000
  13.500   1.0338   0.12052   0.11622  -0.0541   0.0328   1.0000
  13.750   1.0198   0.12926   0.12498  -0.0588   0.0336   1.0000
  14.000   0.9757   0.15404   0.14974  -0.0741   0.0434   1.0000
  14.250   0.9754   0.16110   0.15680  -0.0771   0.0460   1.0000
  14.500   0.9707   0.17217   0.16780  -0.0811   0.0560   1.0000
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