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HQ 3.5/12 AIRFOIL (hq3512-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: HQ 3.5/12 AIRFOIL (hq3512-il)
Reynolds number: 200,000
Max Cl/Cd: 83.46 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq3512-il-200000.txt
Download as CSV file: xf-hq3512-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3580   0.09795   0.09475  -0.0415   1.0000   0.0446
  -9.000  -0.3676   0.09657   0.09344  -0.0385   1.0000   0.0451
  -8.750  -0.3801   0.09512   0.09205  -0.0359   1.0000   0.0455
  -8.500  -0.3843   0.09284   0.08981  -0.0354   0.9991   0.0463
  -8.250  -0.3692   0.08822   0.08519  -0.0410   0.9951   0.0480
  -8.000  -0.2585   0.06513   0.06224  -0.0641   0.9752   0.0568
  -7.750  -0.2460   0.06056   0.05766  -0.0676   0.9717   0.0583
  -7.500  -0.2471   0.05517   0.05229  -0.0727   0.9645   0.0595
  -7.250  -0.2495   0.04730   0.04432  -0.0838   0.9572   0.0605
  -7.000  -0.2505   0.04175   0.03861  -0.0889   0.9480   0.0625
  -6.750  -0.2461   0.03358   0.02962  -0.0986   0.9417   0.0681
  -6.500  -0.2346   0.02992   0.02604  -0.0982   0.9342   0.0694
  -6.250  -0.2632   0.03212   0.02644  -0.0976   0.9363   0.0332
  -6.000  -0.2344   0.02888   0.02280  -0.0989   0.9319   0.0327
  -5.750  -0.2002   0.02535   0.01873  -0.1010   0.9293   0.0332
  -5.500  -0.1637   0.02258   0.01571  -0.1034   0.9276   0.0351
  -5.250  -0.1401   0.02199   0.01506  -0.1029   0.9207   0.0386
  -5.000  -0.1056   0.02099   0.01374  -0.1038   0.9169   0.0426
  -4.750  -0.0711   0.01910   0.01184  -0.1053   0.9144   0.0501
  -4.500  -0.0346   0.01808   0.01077  -0.1070   0.9123   0.0626
  -4.250  -0.0149   0.01752   0.01018  -0.1056   0.9040   0.0717
  -4.000   0.0187   0.01695   0.00956  -0.1068   0.9006   0.0840
  -3.750   0.0535   0.01628   0.00887  -0.1081   0.8980   0.0936
  -3.500   0.0737   0.01579   0.00843  -0.1068   0.8899   0.1023
  -3.250   0.1048   0.01514   0.00781  -0.1075   0.8859   0.1182
  -3.000   0.1373   0.01425   0.00714  -0.1085   0.8830   0.1677
  -2.750   0.1506   0.01287   0.00718  -0.1068   0.8743   0.5121
  -2.500   0.1797   0.01275   0.00724  -0.1063   0.8703   0.6088
  -2.250   0.2056   0.01285   0.00731  -0.1055   0.8645   0.6472
  -2.000   0.2316   0.01293   0.00736  -0.1047   0.8584   0.6765
  -1.750   0.2618   0.01289   0.00730  -0.1044   0.8546   0.7018
  -1.500   0.2848   0.01302   0.00739  -0.1032   0.8469   0.7205
  -1.250   0.3115   0.01300   0.00739  -0.1021   0.8417   0.7425
  -1.000   0.3346   0.01308   0.00749  -0.1003   0.8358   0.7697
  -0.750   0.3579   0.01304   0.00745  -0.0987   0.8284   0.7894
  -0.500   0.3864   0.01283   0.00719  -0.0983   0.8226   0.8013
  -0.250   0.4120   0.01271   0.00702  -0.0976   0.8139   0.8111
   0.000   0.4405   0.01252   0.00677  -0.0973   0.8075   0.8205
   0.250   0.4660   0.01239   0.00663  -0.0966   0.7993   0.8297
   0.500   0.4941   0.01223   0.00642  -0.0964   0.7925   0.8398
   0.750   0.5198   0.01208   0.00626  -0.0957   0.7841   0.8503
   1.000   0.5456   0.01193   0.00610  -0.0949   0.7760   0.8609
   1.250   0.5722   0.01175   0.00590  -0.0943   0.7681   0.8727
   1.500   0.5968   0.01164   0.00583  -0.0935   0.7597   0.8862
   1.750   0.6242   0.01146   0.00564  -0.0930   0.7524   0.9012
   2.000   0.6499   0.01137   0.00560  -0.0924   0.7430   0.9202
   2.250   0.6856   0.01123   0.00545  -0.0938   0.7354   0.9449
   2.500   0.7286   0.01112   0.00537  -0.0970   0.7248   0.9977
   2.750   0.7572   0.01116   0.00538  -0.0975   0.7140   1.0000
   3.000   0.7865   0.01119   0.00535  -0.0980   0.7036   1.0000
   3.250   0.8161   0.01121   0.00530  -0.0984   0.6929   1.0000
   3.500   0.8430   0.01126   0.00535  -0.0983   0.6797   1.0000
   3.750   0.8697   0.01132   0.00538  -0.0980   0.6657   1.0000
   4.000   0.8961   0.01140   0.00541  -0.0977   0.6508   1.0000
   4.250   0.9220   0.01148   0.00546  -0.0973   0.6341   1.0000
   4.500   0.9462   0.01159   0.00556  -0.0965   0.6138   1.0000
   4.750   0.9705   0.01172   0.00563  -0.0958   0.5918   1.0000
   5.000   0.9932   0.01190   0.00575  -0.0947   0.5645   1.0000
   5.250   1.0146   0.01217   0.00589  -0.0934   0.5324   1.0000
   5.500   1.0340   0.01256   0.00611  -0.0918   0.4936   1.0000
   5.750   1.0517   0.01310   0.00643  -0.0900   0.4541   1.0000
   6.000   1.0687   0.01373   0.00685  -0.0882   0.4184   1.0000
   6.250   1.0865   0.01436   0.00731  -0.0866   0.3897   1.0000
   6.500   1.1052   0.01497   0.00780  -0.0852   0.3669   1.0000
   6.750   1.1245   0.01555   0.00829  -0.0839   0.3482   1.0000
   7.000   1.1440   0.01612   0.00879  -0.0827   0.3323   1.0000
   7.250   1.1635   0.01668   0.00932  -0.0815   0.3181   1.0000
   7.500   1.1830   0.01724   0.00986  -0.0803   0.3053   1.0000
   7.750   1.2026   0.01784   0.01042  -0.0791   0.2941   1.0000
   8.000   1.2222   0.01849   0.01102  -0.0780   0.2836   1.0000
   8.250   1.2411   0.01902   0.01163  -0.0767   0.2727   1.0000
   8.500   1.2599   0.01961   0.01226  -0.0754   0.2626   1.0000
   8.750   1.2776   0.02027   0.01290  -0.0740   0.2529   1.0000
   9.000   1.2928   0.02082   0.01351  -0.0721   0.2426   1.0000
   9.250   1.3068   0.02137   0.01416  -0.0701   0.2320   1.0000
   9.500   1.3195   0.02198   0.01481  -0.0680   0.2211   1.0000
   9.750   1.3300   0.02260   0.01547  -0.0656   0.2094   1.0000
  10.000   1.3390   0.02323   0.01615  -0.0632   0.1962   1.0000
  10.250   1.3485   0.02391   0.01689  -0.0609   0.1816   1.0000
  10.500   1.3586   0.02468   0.01771  -0.0590   0.1659   1.0000
  10.750   1.3683   0.02560   0.01865  -0.0571   0.1503   1.0000
  11.000   1.3770   0.02668   0.01973  -0.0552   0.1358   1.0000
  11.250   1.3845   0.02792   0.02096  -0.0533   0.1214   1.0000
  11.500   1.3912   0.02929   0.02234  -0.0515   0.1076   1.0000
  11.750   1.3974   0.03077   0.02383  -0.0498   0.0947   1.0000
  12.000   1.4020   0.03243   0.02549  -0.0481   0.0815   1.0000
  12.250   1.4028   0.03451   0.02751  -0.0463   0.0645   1.0000
  12.500   1.3954   0.03742   0.03028  -0.0443   0.0448   1.0000
  12.750   1.3851   0.04079   0.03362  -0.0423   0.0315   1.0000
  13.000   1.3743   0.04434   0.03718  -0.0408   0.0261   1.0000
  13.250   1.3707   0.04732   0.04030  -0.0398   0.0234   1.0000
  13.500   1.3625   0.05092   0.04399  -0.0391   0.0215   1.0000
  13.750   1.3485   0.05539   0.04856  -0.0387   0.0203   1.0000
  14.000   1.3445   0.05889   0.05224  -0.0386   0.0196   1.0000
  14.250   1.3395   0.06268   0.05618  -0.0388   0.0190   1.0000
  14.500   1.3337   0.06673   0.06037  -0.0392   0.0183   1.0000
  14.750   1.3280   0.07089   0.06467  -0.0398   0.0177   1.0000
  15.000   1.3226   0.07517   0.06907  -0.0407   0.0172   1.0000
  15.250   1.3170   0.07959   0.07360  -0.0417   0.0168   1.0000
  15.500   1.3122   0.08396   0.07811  -0.0428   0.0164   1.0000
  15.750   1.3073   0.08841   0.08265  -0.0439   0.0160   1.0000
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