Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 3.0/14 AIRFOIL (hq3014-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.0/14 AIRFOIL (hq3014-il)
Reynolds number: 100,000
Max Cl/Cd: 53.38 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3014-il-100000-n5.txt
Download as CSV file: xf-hq3014-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/14 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.5219   0.06521   0.06003  -0.0737   1.0000   0.0281
 -10.750  -0.5508   0.06042   0.05521  -0.0751   1.0000   0.0279
 -10.500  -0.5792   0.05744   0.05220  -0.0739   1.0000   0.0278
 -10.250  -0.6125   0.05572   0.05051  -0.0701   1.0000   0.0277
 -10.000  -0.6329   0.05206   0.04663  -0.0710   0.9924   0.0277
  -9.500  -0.6214   0.04317   0.03691  -0.0772   0.9727   0.0290
  -9.250  -0.6013   0.04135   0.03493  -0.0788   0.9659   0.0303
  -9.000  -0.5825   0.03891   0.03215  -0.0803   0.9589   0.0323
  -8.750  -0.5658   0.03552   0.02805  -0.0812   0.9520   0.0348
  -8.500  -0.5419   0.03405   0.02655  -0.0822   0.9459   0.0366
  -8.250  -0.5127   0.03241   0.02468  -0.0839   0.9420   0.0394
  -8.000  -0.4911   0.03070   0.02249  -0.0838   0.9350   0.0432
  -7.750  -0.4637   0.02973   0.02156  -0.0848   0.9299   0.0465
  -7.500  -0.4323   0.02856   0.02005  -0.0862   0.9263   0.0519
  -7.250  -0.4110   0.02749   0.01893  -0.0858   0.9190   0.0555
  -7.000  -0.3818   0.02660   0.01791  -0.0866   0.9144   0.0602
  -6.750  -0.3493   0.02555   0.01660  -0.0878   0.9111   0.0653
  -6.500  -0.3283   0.02472   0.01582  -0.0870   0.9037   0.0689
  -6.250  -0.2992   0.02394   0.01494  -0.0876   0.8991   0.0739
  -6.000  -0.2673   0.02305   0.01390  -0.0884   0.8959   0.0783
  -5.750  -0.2477   0.02240   0.01328  -0.0873   0.8881   0.0821
  -5.500  -0.2195   0.02177   0.01259  -0.0875   0.8834   0.0883
  -5.250  -0.1911   0.02109   0.01190  -0.0879   0.8793   0.0955
  -5.000  -0.1704   0.02067   0.01144  -0.0868   0.8719   0.1031
  -4.750  -0.1427   0.02006   0.01083  -0.0870   0.8674   0.1136
  -4.500  -0.1178   0.01954   0.01036  -0.0868   0.8620   0.1305
  -4.250  -0.0954   0.01903   0.00998  -0.0861   0.8555   0.1569
  -4.000  -0.0682   0.01831   0.00950  -0.0865   0.8513   0.2158
  -3.750  -0.0474   0.01765   0.00918  -0.0858   0.8449   0.2971
  -3.500  -0.0273   0.01700   0.00921  -0.0846   0.8389   0.4378
  -3.250   0.0010   0.01687   0.00923  -0.0843   0.8351   0.5183
  -3.000   0.0228   0.01698   0.00935  -0.0829   0.8281   0.5586
  -2.750   0.0491   0.01706   0.00941  -0.0822   0.8227   0.5925
  -2.500   0.0786   0.01712   0.00942  -0.0819   0.8190   0.6233
  -2.250   0.0987   0.01736   0.00964  -0.0801   0.8113   0.6494
  -2.000   0.1249   0.01748   0.00974  -0.0792   0.8063   0.6710
  -1.750   0.1529   0.01750   0.00969  -0.0787   0.8017   0.6863
  -1.500   0.1751   0.01761   0.00975  -0.0776   0.7941   0.6985
  -1.250   0.2042   0.01757   0.00962  -0.0774   0.7895   0.7118
  -1.000   0.2272   0.01765   0.00968  -0.0762   0.7827   0.7233
  -0.750   0.2531   0.01764   0.00964  -0.0756   0.7767   0.7335
  -0.500   0.2845   0.01752   0.00942  -0.0760   0.7726   0.7430
  -0.250   0.3054   0.01761   0.00951  -0.0747   0.7643   0.7493
   0.000   0.3355   0.01751   0.00934  -0.0751   0.7593   0.7570
   0.250   0.3607   0.01752   0.00934  -0.0745   0.7527   0.7637
   0.500   0.3872   0.01751   0.00929  -0.0742   0.7461   0.7718
   0.750   0.4182   0.01736   0.00911  -0.0745   0.7416   0.7787
   1.000   0.4395   0.01748   0.00924  -0.0734   0.7327   0.7873
   1.250   0.4699   0.01731   0.00904  -0.0735   0.7271   0.7948
   1.500   0.4930   0.01731   0.00904  -0.0726   0.7166   0.8040
   1.750   0.5207   0.01714   0.00886  -0.0722   0.7078   0.8121
   2.000   0.5473   0.01702   0.00873  -0.0717   0.6982   0.8217
   2.250   0.5715   0.01700   0.00875  -0.0709   0.6888   0.8316
   2.500   0.6003   0.01686   0.00861  -0.0707   0.6813   0.8416
   2.750   0.6230   0.01689   0.00870  -0.0697   0.6711   0.8534
   3.000   0.6500   0.01680   0.00863  -0.0693   0.6623   0.8660
   3.250   0.6757   0.01673   0.00862  -0.0687   0.6520   0.8804
   3.500   0.7015   0.01670   0.00867  -0.0682   0.6403   0.8981
   3.750   0.7334   0.01664   0.00867  -0.0688   0.6280   0.9199
   4.000   0.7711   0.01659   0.00868  -0.0708   0.6136   0.9583
   4.250   0.8006   0.01663   0.00870  -0.0714   0.5986   1.0000
   4.500   0.8255   0.01674   0.00878  -0.0710   0.5833   1.0000
   4.750   0.8500   0.01688   0.00889  -0.0705   0.5671   1.0000
   5.000   0.8741   0.01704   0.00901  -0.0699   0.5500   1.0000
   5.250   0.8977   0.01722   0.00914  -0.0692   0.5320   1.0000
   5.500   0.9211   0.01744   0.00928  -0.0685   0.5128   1.0000
   5.750   0.9425   0.01773   0.00954  -0.0674   0.4922   1.0000
   6.000   0.9635   0.01805   0.00978  -0.0663   0.4704   1.0000
   6.250   0.9836   0.01844   0.01007  -0.0651   0.4485   1.0000
   6.500   1.0026   0.01888   0.01044  -0.0637   0.4264   1.0000
   6.750   1.0207   0.01937   0.01083  -0.0622   0.4051   1.0000
   7.000   1.0379   0.01990   0.01130  -0.0607   0.3841   1.0000
   7.250   1.0543   0.02047   0.01180  -0.0590   0.3643   1.0000
   7.500   1.0696   0.02107   0.01234  -0.0572   0.3460   1.0000
   7.750   1.0837   0.02169   0.01290  -0.0552   0.3292   1.0000
   8.000   1.0974   0.02236   0.01351  -0.0532   0.3136   1.0000
   8.500   1.1248   0.02380   0.01490  -0.0496   0.2856   1.0000
   8.750   1.1385   0.02457   0.01566  -0.0478   0.2726   1.0000
   9.000   1.1521   0.02536   0.01647  -0.0461   0.2605   1.0000
   9.250   1.1652   0.02620   0.01730  -0.0445   0.2493   1.0000
   9.750   1.1898   0.02798   0.01913  -0.0412   0.2273   1.0000
  10.000   1.2017   0.02892   0.02013  -0.0396   0.2170   1.0000
  10.250   1.2120   0.02996   0.02117  -0.0380   0.2074   1.0000
  10.500   1.2227   0.03101   0.02228  -0.0365   0.1975   1.0000
  10.750   1.2330   0.03212   0.02346  -0.0350   0.1882   1.0000
  11.250   1.2507   0.03461   0.02606  -0.0322   0.1705   1.0000
  11.500   1.2583   0.03599   0.02747  -0.0308   0.1625   1.0000
  11.750   1.2658   0.03743   0.02899  -0.0295   0.1543   1.0000
  12.000   1.2732   0.03893   0.03057  -0.0283   0.1470   1.0000
  12.250   1.2792   0.04056   0.03228  -0.0272   0.1397   1.0000
  12.500   1.2855   0.04225   0.03406  -0.0261   0.1330   1.0000
  12.750   1.2902   0.04409   0.03599  -0.0252   0.1264   1.0000
  13.000   1.2943   0.04605   0.03803  -0.0243   0.1202   1.0000
  13.250   1.2979   0.04812   0.04023  -0.0235   0.1140   1.0000
  13.500   1.2991   0.05043   0.04257  -0.0228   0.1089   1.0000
  13.750   1.3026   0.05268   0.04499  -0.0223   0.1031   1.0000
  14.000   1.3025   0.05528   0.04765  -0.0219   0.0987   1.0000
  14.250   1.3033   0.05793   0.05041  -0.0216   0.0940   1.0000
  14.500   1.3029   0.06080   0.05342  -0.0215   0.0892   1.0000
  14.750   1.3000   0.06398   0.05663  -0.0217   0.0855   1.0000
  15.000   1.2988   0.06719   0.05999  -0.0219   0.0815   1.0000
  15.250   1.2955   0.07074   0.06370  -0.0225   0.0773   1.0000
  15.500   1.2901   0.07464   0.06768  -0.0234   0.0741   1.0000
  15.750   1.2862   0.07847   0.07161  -0.0243   0.0713   1.0000
  16.000   1.2813   0.08269   0.07604  -0.0255   0.0680   1.0000
  16.250   1.2746   0.08723   0.08072  -0.0271   0.0652   1.0000
  16.500   1.2672   0.09197   0.08554  -0.0289   0.0629   1.0000
  16.750   1.2605   0.09669   0.09034  -0.0307   0.0608   1.0000
  17.000   1.2534   0.10175   0.09562  -0.0327   0.0588   1.0000
  17.250   1.2456   0.10699   0.10105  -0.0350   0.0569   1.0000
  17.500   1.2374   0.11241   0.10662  -0.0376   0.0552   1.0000
  17.750   1.2290   0.11796   0.11229  -0.0404   0.0536   1.0000
  18.000   1.2216   0.12331   0.11769  -0.0432   0.0519   1.0000
  18.250   1.2130   0.12906   0.12354  -0.0463   0.0503   1.0000
  18.500   1.1993   0.13618   0.13088  -0.0504   0.0489   1.0000
  18.750   1.1846   0.14369   0.13858  -0.0548   0.0476   1.0000
  19.000   1.1689   0.15160   0.14666  -0.0596   0.0463   1.0000
<< Back to HQ 3.0/14 AIRFOIL (hq3014-il)

Polar data table (+)

Polar graphs


<< Back to HQ 3.0/14 AIRFOIL (hq3014-il)