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HQ 3.0/10 AIRFOIL (hq3010-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.0/10 AIRFOIL (hq3010-il)
Reynolds number: 100,000
Max Cl/Cd: 60.04 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3010-il-100000.txt
Download as CSV file: xf-hq3010-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.0/10 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3638   0.09482   0.09013  -0.0379   1.0000   0.0880
  -8.250  -0.3798   0.09276   0.08822  -0.0396   1.0000   0.0906
  -8.000  -0.4005   0.09119   0.08680  -0.0395   1.0000   0.0912
  -7.750  -0.4252   0.08953   0.08528  -0.0394   1.0000   0.0914
  -7.500  -0.4463   0.08702   0.08282  -0.0414   1.0000   0.0917
  -7.250  -0.4270   0.08355   0.07943  -0.0327   1.0000   0.0951
  -7.000  -0.4328   0.08147   0.07741  -0.0305   1.0000   0.0972
  -6.750  -0.4432   0.07899   0.07499  -0.0300   1.0000   0.0997
  -6.500  -0.4550   0.07585   0.07188  -0.0320   1.0000   0.1026
  -6.250  -0.4760   0.07211   0.06779  -0.0410   1.0000   0.1063
  -6.000  -0.4670   0.06839   0.06436  -0.0355   1.0000   0.1086
  -5.750  -0.4629   0.06598   0.06198  -0.0336   1.0000   0.1127
  -5.500  -0.4606   0.06155   0.05727  -0.0385   1.0000   0.1217
  -5.250  -0.4528   0.05904   0.05487  -0.0360   1.0000   0.1261
  -5.000  -0.4427   0.05534   0.05098  -0.0383   1.0000   0.1374
  -4.750  -0.4298   0.05226   0.04774  -0.0395   1.0000   0.1507
  -4.500  -0.4162   0.04946   0.04484  -0.0397   1.0000   0.1653
  -4.250  -0.4014   0.04685   0.04220  -0.0395   1.0000   0.1814
  -4.000  -0.3286   0.03420   0.02720  -0.0471   1.0000   0.0626
  -3.750  -0.2953   0.03116   0.02367  -0.0487   0.9979   0.0620
  -3.500  -0.2536   0.02891   0.02075  -0.0511   0.9939   0.0636
  -3.250  -0.2157   0.02684   0.01817  -0.0527   0.9894   0.0645
  -3.000  -0.1788   0.02444   0.01569  -0.0546   0.9854   0.0705
  -2.750  -0.1404   0.02320   0.01434  -0.0566   0.9811   0.0865
  -2.500  -0.1071   0.02201   0.01320  -0.0579   0.9755   0.1117
  -2.250  -0.0692   0.02115   0.01248  -0.0600   0.9706   0.1442
  -2.000  -0.0360   0.02021   0.01187  -0.0615   0.9647   0.2009
  -1.750  -0.0172   0.01870   0.01252  -0.0588   0.9589   0.7167
  -1.500   0.0056   0.01896   0.01281  -0.0566   0.9517   0.7931
  -1.250   0.0278   0.01899   0.01284  -0.0545   0.9439   0.8520
  -1.000   0.0587   0.01886   0.01277  -0.0540   0.9371   0.9292
  -0.750   0.1141   0.01895   0.01264  -0.0602   0.9303   1.0000
  -0.500   0.1522   0.01920   0.01266  -0.0632   0.9223   1.0000
  -0.250   0.1955   0.01945   0.01271  -0.0669   0.9151   1.0000
   0.000   0.2290   0.01971   0.01281  -0.0688   0.9060   1.0000
   0.250   0.2761   0.01991   0.01285  -0.0728   0.9000   1.0000
   0.500   0.3054   0.02018   0.01301  -0.0737   0.8898   1.0000
   0.750   0.3442   0.02038   0.01311  -0.0761   0.8820   1.0000
   1.000   0.3841   0.02049   0.01314  -0.0785   0.8737   1.0000
   1.250   0.4182   0.02060   0.01320  -0.0797   0.8631   1.0000
   1.500   0.4762   0.02020   0.01278  -0.0846   0.8574   1.0000
   1.750   0.5077   0.02018   0.01273  -0.0851   0.8455   1.0000
   2.000   0.5402   0.02014   0.01269  -0.0856   0.8344   1.0000
   2.250   0.5777   0.01994   0.01250  -0.0868   0.8253   1.0000
   2.500   0.6182   0.01954   0.01214  -0.0883   0.8168   1.0000
   2.750   0.6491   0.01935   0.01198  -0.0882   0.8047   1.0000
   3.000   0.6814   0.01903   0.01169  -0.0881   0.7925   1.0000
   3.250   0.7143   0.01861   0.01134  -0.0879   0.7799   1.0000
   3.500   0.7466   0.01816   0.01094  -0.0876   0.7665   1.0000
   3.750   0.7779   0.01775   0.01057  -0.0871   0.7523   1.0000
   4.000   0.8084   0.01736   0.01023  -0.0865   0.7368   1.0000
   4.250   0.8390   0.01696   0.00990  -0.0859   0.7200   1.0000
   4.500   0.8663   0.01671   0.00970  -0.0848   0.6998   1.0000
   4.750   0.8943   0.01644   0.00945  -0.0838   0.6775   1.0000
   5.000   0.9197   0.01631   0.00935  -0.0825   0.6510   1.0000
   5.250   0.9450   0.01623   0.00928  -0.0812   0.6209   1.0000
   5.500   0.9677   0.01630   0.00933  -0.0796   0.5846   1.0000
   5.750   0.9900   0.01649   0.00942  -0.0780   0.5436   1.0000
   6.000   1.0107   0.01690   0.00964  -0.0762   0.4990   1.0000
   6.250   1.0302   0.01752   0.01004  -0.0744   0.4546   1.0000
   6.500   1.0486   0.01831   0.01064  -0.0727   0.4125   1.0000
   6.750   1.0667   0.01916   0.01132  -0.0710   0.3741   1.0000
   7.000   1.0845   0.02005   0.01202  -0.0694   0.3400   1.0000
   7.250   1.1019   0.02095   0.01281  -0.0678   0.3084   1.0000
   7.500   1.1190   0.02189   0.01366  -0.0662   0.2792   1.0000
   7.750   1.1356   0.02287   0.01457  -0.0646   0.2522   1.0000
   8.000   1.1512   0.02389   0.01555  -0.0629   0.2263   1.0000
   8.250   1.1658   0.02499   0.01659  -0.0611   0.2007   1.0000
   8.500   1.1786   0.02618   0.01775  -0.0590   0.1747   1.0000
   8.750   1.1910   0.02755   0.01909  -0.0569   0.1506   1.0000
   9.000   1.2054   0.02922   0.02059  -0.0552   0.1315   1.0000
   9.250   1.2174   0.03057   0.02205  -0.0531   0.1148   1.0000
   9.500   1.2258   0.03175   0.02329  -0.0508   0.1001   1.0000
   9.750   1.2330   0.03307   0.02466  -0.0483   0.0878   1.0000
  10.000   1.2358   0.03436   0.02606  -0.0454   0.0755   1.0000
  10.250   1.2374   0.03598   0.02775  -0.0427   0.0635   1.0000
  10.500   1.2393   0.03850   0.03033  -0.0400   0.0514   1.0000
  10.750   1.2479   0.04172   0.03351  -0.0382   0.0434   1.0000
  11.000   1.2581   0.04453   0.03662  -0.0363   0.0387   1.0000
  11.250   1.2692   0.04748   0.03967  -0.0350   0.0359   1.0000
  11.500   1.2813   0.05252   0.04494  -0.0342   0.0339   1.0000
  11.750   1.2757   0.05536   0.04818  -0.0316   0.0331   1.0000
  12.000   1.2679   0.05862   0.05180  -0.0294   0.0323   1.0000
  12.250   1.2572   0.06228   0.05580  -0.0277   0.0317   1.0000
  12.500   1.2440   0.06629   0.06013  -0.0266   0.0313   1.0000
  12.750   1.2281   0.07080   0.06494  -0.0262   0.0312   1.0000
  13.000   1.2100   0.07572   0.07014  -0.0265   0.0310   1.0000
  13.250   1.1901   0.08134   0.07602  -0.0278   0.0312   1.0000
  13.500   1.1684   0.08762   0.08254  -0.0301   0.0314   1.0000
  13.750   1.1462   0.09461   0.08974  -0.0333   0.0320   1.0000
  14.000   1.1236   0.10230   0.09761  -0.0375   0.0326   1.0000
  14.250   1.1013   0.11067   0.10614  -0.0425   0.0331   1.0000
  14.500   1.0813   0.11950   0.11506  -0.0478   0.0338   1.0000
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