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HQ 3.0/13 AIRFOIL (hq3013-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/13 AIRFOIL (hq3013-il)
Reynolds number: 50,000
Max Cl/Cd: 35.17 at α=7.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3013-il-50000-n5.txt
Download as CSV file: xf-hq3013-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/13 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3741   0.10403   0.09689  -0.0501   1.0000   0.0540
 -10.250  -0.3785   0.09992   0.09287  -0.0513   1.0000   0.0539
 -10.000  -0.3854   0.09558   0.08863  -0.0525   1.0000   0.0539
  -9.750  -0.3935   0.09127   0.08444  -0.0537   1.0000   0.0537
  -9.500  -0.4047   0.08673   0.08001  -0.0549   1.0000   0.0534
  -9.250  -0.4206   0.08192   0.07531  -0.0563   1.0000   0.0530
  -9.000  -0.4423   0.07783   0.07134  -0.0568   1.0000   0.0526
  -8.750  -0.4705   0.07482   0.06844  -0.0555   1.0000   0.0520
  -8.500  -0.4991   0.07236   0.06606  -0.0534   1.0000   0.0513
  -8.250  -0.5252   0.06936   0.06306  -0.0516   1.0000   0.0510
  -8.000  -0.5467   0.06618   0.05981  -0.0499   1.0000   0.0507
  -7.750  -0.5632   0.06278   0.05627  -0.0485   1.0000   0.0507
  -7.500  -0.5744   0.05920   0.05247  -0.0473   1.0000   0.0510
  -7.250  -0.5646   0.05392   0.04669  -0.0505   0.9941   0.0518
  -7.000  -0.5477   0.04887   0.04096  -0.0534   0.9870   0.0538
  -6.750  -0.5260   0.04493   0.03643  -0.0557   0.9811   0.0571
  -6.500  -0.5013   0.04277   0.03409  -0.0571   0.9752   0.0608
  -6.250  -0.4726   0.03992   0.03062  -0.0590   0.9702   0.0665
  -6.000  -0.4483   0.03770   0.02808  -0.0596   0.9642   0.0716
  -5.750  -0.4184   0.03602   0.02605  -0.0609   0.9591   0.0791
  -5.500  -0.3896   0.03436   0.02414  -0.0617   0.9541   0.0860
  -5.250  -0.3619   0.03312   0.02262  -0.0620   0.9482   0.0944
  -5.000  -0.3304   0.03184   0.02127  -0.0629   0.9439   0.1012
  -4.750  -0.3029   0.03098   0.02015  -0.0629   0.9382   0.1110
  -4.500  -0.2760   0.03006   0.01926  -0.0630   0.9325   0.1194
  -4.250  -0.2439   0.02923   0.01838  -0.0641   0.9281   0.1319
  -4.000  -0.2211   0.02855   0.01769  -0.0636   0.9213   0.1468
  -3.750  -0.1913   0.02779   0.01695  -0.0646   0.9159   0.1704
  -3.500  -0.1619   0.02683   0.01622  -0.0659   0.9109   0.2151
  -3.250  -0.1401   0.02557   0.01569  -0.0660   0.9042   0.3239
  -3.000  -0.1161   0.02528   0.01629  -0.0646   0.8991   0.5332
  -2.750  -0.0976   0.02558   0.01657  -0.0623   0.8916   0.6024
  -2.500  -0.0726   0.02591   0.01682  -0.0609   0.8856   0.6561
  -2.250  -0.0541   0.02626   0.01715  -0.0581   0.8788   0.6978
  -2.000  -0.0364   0.02656   0.01744  -0.0550   0.8718   0.7380
  -1.750  -0.0157   0.02675   0.01757  -0.0523   0.8660   0.7739
  -1.500   0.0000   0.02684   0.01760  -0.0494   0.8580   0.8014
  -1.250   0.0299   0.02681   0.01745  -0.0490   0.8533   0.8263
  -1.000   0.0462   0.02684   0.01740  -0.0470   0.8444   0.8447
  -0.750   0.0816   0.02677   0.01717  -0.0484   0.8393   0.8584
  -0.500   0.1044   0.02682   0.01713  -0.0480   0.8308   0.8722
  -0.250   0.1412   0.02678   0.01696  -0.0498   0.8251   0.8858
   0.000   0.1717   0.02687   0.01698  -0.0507   0.8174   0.9011
   0.250   0.2131   0.02689   0.01692  -0.0535   0.8112   0.9162
   0.500   0.2578   0.02694   0.01690  -0.0571   0.8050   0.9334
   0.750   0.3008   0.02706   0.01697  -0.0607   0.7974   0.9559
   1.000   0.3547   0.02694   0.01676  -0.0658   0.7929   0.9823
   1.250   0.3718   0.02724   0.01699  -0.0652   0.7817   1.0000
   1.500   0.3956   0.02745   0.01711  -0.0653   0.7727   1.0000
   1.750   0.4278   0.02752   0.01711  -0.0665   0.7652   1.0000
   2.000   0.4500   0.02785   0.01737  -0.0662   0.7548   1.0000
   2.250   0.4892   0.02770   0.01717  -0.0679   0.7485   1.0000
   2.500   0.5109   0.02798   0.01741  -0.0673   0.7363   1.0000
   2.750   0.5368   0.02811   0.01751  -0.0670   0.7248   1.0000
   3.000   0.5733   0.02786   0.01724  -0.0680   0.7164   1.0000
   3.250   0.6004   0.02791   0.01729  -0.0677   0.7049   1.0000
   3.500   0.6242   0.02808   0.01747  -0.0671   0.6925   1.0000
   3.750   0.6504   0.02817   0.01758  -0.0667   0.6808   1.0000
   4.000   0.6832   0.02797   0.01742  -0.0669   0.6710   1.0000
   4.250   0.7134   0.02782   0.01731  -0.0668   0.6596   1.0000
   4.750   0.7634   0.02786   0.01746  -0.0652   0.6317   1.0000
   5.000   0.7894   0.02779   0.01744  -0.0644   0.6169   1.0000
   5.250   0.8159   0.02768   0.01738  -0.0636   0.6014   1.0000
   5.500   0.8428   0.02754   0.01731  -0.0628   0.5853   1.0000
   5.750   0.8674   0.02751   0.01732  -0.0618   0.5676   1.0000
   6.000   0.8883   0.02769   0.01756  -0.0604   0.5481   1.0000
   6.250   0.9129   0.02770   0.01763  -0.0594   0.5285   1.0000
   6.500   0.9389   0.02770   0.01762  -0.0585   0.5084   1.0000
   6.750   0.9592   0.02801   0.01796  -0.0571   0.4861   1.0000
   7.000   0.9839   0.02816   0.01805  -0.0561   0.4644   1.0000
   7.250   1.0022   0.02868   0.01859  -0.0546   0.4415   1.0000
   7.500   1.0238   0.02911   0.01894  -0.0534   0.4199   1.0000
   7.750   1.0396   0.02984   0.01968  -0.0517   0.3983   1.0000
   8.000   1.0566   0.03056   0.02035  -0.0501   0.3782   1.0000
   8.250   1.0732   0.03133   0.02108  -0.0486   0.3594   1.0000
   8.500   1.0875   0.03227   0.02206  -0.0469   0.3413   1.0000
   8.750   1.1017   0.03323   0.02304  -0.0453   0.3242   1.0000
   9.000   1.1164   0.03424   0.02405  -0.0438   0.3082   1.0000
   9.250   1.1309   0.03530   0.02513  -0.0423   0.2931   1.0000
   9.500   1.1447   0.03642   0.02629  -0.0409   0.2786   1.0000
   9.750   1.1585   0.03760   0.02754  -0.0395   0.2649   1.0000
  10.000   1.1711   0.03883   0.02882  -0.0381   0.2516   1.0000
  10.250   1.1832   0.04010   0.03012  -0.0366   0.2391   1.0000
  10.500   1.1946   0.04140   0.03146  -0.0352   0.2271   1.0000
  10.750   1.2009   0.04298   0.03321  -0.0336   0.2154   1.0000
  11.000   1.2085   0.04460   0.03495  -0.0321   0.2045   1.0000
  11.250   1.2158   0.04620   0.03666  -0.0307   0.1942   1.0000
  11.500   1.2234   0.04780   0.03829  -0.0294   0.1844   1.0000
  11.750   1.2263   0.04992   0.04062  -0.0281   0.1748   1.0000
  12.000   1.2311   0.05186   0.04263  -0.0269   0.1660   1.0000
  12.250   1.2344   0.05396   0.04484  -0.0258   0.1575   1.0000
  12.500   1.2359   0.05647   0.04754  -0.0249   0.1498   1.0000
  12.750   1.2403   0.05856   0.04967  -0.0240   0.1424   1.0000
  13.000   1.2366   0.06172   0.05309  -0.0234   0.1357   1.0000
  13.250   1.2394   0.06420   0.05564  -0.0228   0.1295   1.0000
  13.500   1.2367   0.06752   0.05917  -0.0225   0.1242   1.0000
  13.750   1.2305   0.07127   0.06319  -0.0225   0.1192   1.0000
  14.000   1.2371   0.07335   0.06520  -0.0221   0.1139   1.0000
  14.250   1.2192   0.07891   0.07114  -0.0231   0.1106   1.0000
  14.500   1.2035   0.08441   0.07690  -0.0245   0.1073   1.0000
  14.750   1.1969   0.08872   0.08134  -0.0255   0.1038   1.0000
  15.000   1.1988   0.09191   0.08456  -0.0259   0.1003   1.0000
  15.250   1.1665   0.10099   0.09395  -0.0300   0.0993   1.0000
  15.500   1.1231   0.11322   0.10643  -0.0365   0.0989   1.0000
  15.750   1.0419   0.13660   0.12984  -0.0505   0.0990   1.0000
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