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HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il)
Reynolds number: 100,000
Max Cl/Cd: 47.11 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq1012-il-100000.txt
Download as CSV file: xf-hq1012-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/12 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5648   0.09039   0.08551  -0.0283   1.0000   0.1039
 -10.000  -0.5656   0.08772   0.08289  -0.0292   1.0000   0.1174
  -9.750  -0.7473   0.05952   0.05379  -0.0455   1.0000   0.0600
  -9.500  -0.7551   0.05553   0.04952  -0.0440   1.0000   0.0600
  -9.250  -0.7613   0.05147   0.04513  -0.0422   1.0000   0.0603
  -9.000  -0.7616   0.04729   0.04061  -0.0404   1.0000   0.0604
  -8.750  -0.7590   0.04292   0.03590  -0.0386   1.0000   0.0609
  -8.500  -0.7507   0.03944   0.03222  -0.0369   1.0000   0.0623
  -8.250  -0.7367   0.03742   0.03016  -0.0355   1.0000   0.0655
  -8.000  -0.7268   0.03530   0.02770  -0.0332   1.0000   0.0695
  -7.750  -0.7176   0.03333   0.02510  -0.0303   1.0000   0.0726
  -7.500  -0.7034   0.03053   0.02231  -0.0288   1.0000   0.0769
  -7.250  -0.6900   0.02925   0.02084  -0.0266   1.0000   0.0835
  -7.000  -0.6761   0.02733   0.01878  -0.0245   1.0000   0.0893
  -6.750  -0.6626   0.02631   0.01764  -0.0223   1.0000   0.0971
  -6.500  -0.6480   0.02487   0.01618  -0.0203   1.0000   0.1044
  -6.250  -0.6338   0.02406   0.01514  -0.0182   1.0000   0.1131
  -6.000  -0.6179   0.02278   0.01400  -0.0165   1.0000   0.1218
  -5.750  -0.6024   0.02181   0.01302  -0.0147   1.0000   0.1320
  -5.500  -0.5864   0.02095   0.01213  -0.0129   1.0000   0.1433
  -5.250  -0.5707   0.02012   0.01141  -0.0112   1.0000   0.1581
  -5.000  -0.5552   0.01934   0.01080  -0.0096   1.0000   0.1781
  -4.750  -0.5398   0.01849   0.01014  -0.0079   1.0000   0.2084
  -4.500  -0.5259   0.01739   0.00947  -0.0062   1.0000   0.2666
  -4.250  -0.5143   0.01614   0.00903  -0.0042   1.0000   0.3799
  -4.000  -0.5023   0.01564   0.00920  -0.0015   1.0000   0.5106
  -3.750  -0.4823   0.01584   0.00960   0.0001   0.9980   0.5902
  -3.500  -0.4478   0.01639   0.01012  -0.0008   0.9906   0.6467
  -3.250  -0.4130   0.01696   0.01063  -0.0018   0.9834   0.6877
  -3.000  -0.3827   0.01744   0.01108  -0.0017   0.9756   0.7188
  -2.750  -0.3474   0.01798   0.01155  -0.0024   0.9691   0.7481
  -2.500  -0.3223   0.01831   0.01188  -0.0011   0.9606   0.7714
  -2.250  -0.2892   0.01869   0.01220  -0.0013   0.9541   0.7959
  -2.000  -0.2647   0.01886   0.01232  -0.0002   0.9454   0.8156
  -1.750  -0.2303   0.01903   0.01241  -0.0011   0.9390   0.8336
  -1.500  -0.2043   0.01908   0.01240  -0.0007   0.9303   0.8499
  -1.250  -0.1685   0.01919   0.01243  -0.0020   0.9240   0.8655
  -1.000  -0.1403   0.01929   0.01249  -0.0017   0.9155   0.8823
  -0.750  -0.0903   0.01955   0.01271  -0.0050   0.9112   0.8997
  -0.500  -0.0530   0.01975   0.01287  -0.0066   0.9031   0.9151
  -0.250   0.0021   0.01985   0.01291  -0.0119   0.8983   0.9256
   0.000   0.0656   0.01995   0.01296  -0.0188   0.8937   0.9313
   0.250   0.1118   0.01999   0.01297  -0.0227   0.8861   0.9408
   0.500   0.1842   0.01981   0.01277  -0.0311   0.8823   0.9441
   0.750   0.2367   0.01961   0.01258  -0.0357   0.8716   0.9510
   1.000   0.2917   0.01917   0.01215  -0.0403   0.8604   0.9569
   1.250   0.3478   0.01861   0.01160  -0.0449   0.8494   0.9623
   1.500   0.3910   0.01827   0.01130  -0.0475   0.8379   0.9704
   1.750   0.4349   0.01803   0.01111  -0.0507   0.8256   0.9785
   2.000   0.4772   0.01775   0.01087  -0.0535   0.8129   0.9867
   2.250   0.5190   0.01743   0.01063  -0.0562   0.7998   0.9953
   2.500   0.5491   0.01718   0.01042  -0.0567   0.7857   1.0000
   2.750   0.5639   0.01706   0.01032  -0.0543   0.7714   1.0000
   3.000   0.5782   0.01693   0.01024  -0.0519   0.7565   1.0000
   3.250   0.5921   0.01678   0.01012  -0.0492   0.7408   1.0000
   3.500   0.6056   0.01662   0.00998  -0.0464   0.7245   1.0000
   3.750   0.6192   0.01641   0.00978  -0.0435   0.7073   1.0000
   4.000   0.6341   0.01616   0.00952  -0.0406   0.6893   1.0000
   4.250   0.6477   0.01600   0.00938  -0.0376   0.6677   1.0000
   4.500   0.6657   0.01575   0.00909  -0.0351   0.6445   1.0000
   4.750   0.6836   0.01560   0.00890  -0.0327   0.6158   1.0000
   5.000   0.7025   0.01549   0.00874  -0.0304   0.5811   1.0000
   5.250   0.7220   0.01549   0.00862  -0.0283   0.5394   1.0000
   5.500   0.7406   0.01572   0.00866  -0.0262   0.4912   1.0000
   5.750   0.7591   0.01619   0.00886  -0.0243   0.4445   1.0000
   6.000   0.7777   0.01681   0.00923  -0.0226   0.4029   1.0000
   6.250   0.7964   0.01751   0.00973  -0.0210   0.3664   1.0000
   6.500   0.8151   0.01827   0.01030  -0.0196   0.3330   1.0000
   6.750   0.8336   0.01910   0.01098  -0.0182   0.3008   1.0000
   7.000   0.8517   0.02006   0.01178  -0.0168   0.2697   1.0000
   7.250   0.8694   0.02110   0.01266  -0.0154   0.2394   1.0000
   7.500   0.8872   0.02213   0.01361  -0.0140   0.2122   1.0000
   7.750   0.9050   0.02315   0.01447  -0.0126   0.1891   1.0000
   8.000   0.9235   0.02420   0.01554  -0.0113   0.1689   1.0000
   8.250   0.9422   0.02529   0.01659  -0.0101   0.1520   1.0000
   8.500   0.9615   0.02650   0.01778  -0.0090   0.1379   1.0000
   8.750   0.9808   0.02782   0.01911  -0.0079   0.1252   1.0000
   9.000   1.0003   0.02929   0.02062  -0.0070   0.1139   1.0000
   9.250   1.0205   0.03094   0.02220  -0.0062   0.1036   1.0000
   9.500   1.0383   0.03241   0.02380  -0.0050   0.0946   1.0000
   9.750   1.0548   0.03437   0.02598  -0.0037   0.0861   1.0000
  10.000   1.0748   0.03675   0.02826  -0.0032   0.0785   1.0000
  10.250   1.0839   0.03838   0.03031  -0.0009   0.0721   1.0000
  10.500   1.1010   0.04123   0.03313  -0.0004   0.0662   1.0000
  10.750   1.1027   0.04322   0.03564   0.0025   0.0623   1.0000
  11.000   1.1103   0.04537   0.03797   0.0044   0.0583   1.0000
  11.250   1.1198   0.04907   0.04167   0.0052   0.0547   1.0000
  11.500   1.1086   0.05144   0.04449   0.0087   0.0534   1.0000
  11.750   1.0927   0.05407   0.04749   0.0123   0.0521   1.0000
  12.000   1.0770   0.05730   0.05102   0.0147   0.0515   1.0000
  12.250   1.0581   0.06093   0.05493   0.0162   0.0508   1.0000
  12.500   1.0366   0.06529   0.05956   0.0167   0.0509   1.0000
  12.750   1.0133   0.07027   0.06477   0.0160   0.0512   1.0000
  13.000   0.9860   0.07620   0.07092   0.0140   0.0516   1.0000
  13.250   0.9561   0.08326   0.07817   0.0105   0.0521   1.0000
  13.500   0.9314   0.09083   0.08586   0.0064   0.0534   1.0000
  13.750   0.9064   0.09933   0.09444   0.0014   0.0543   1.0000
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