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HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il)
Reynolds number: 100,000
Max Cl/Cd: 53.91 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2512-il-100000-n5.txt
Download as CSV file: xf-hq2512-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.5/12 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4261   0.09393   0.08891  -0.0447   1.0000   0.0254
 -10.250  -0.4366   0.08725   0.08231  -0.0480   1.0000   0.0259
 -10.000  -0.4447   0.08161   0.07674  -0.0507   1.0000   0.0257
  -9.750  -0.4579   0.07440   0.06961  -0.0547   1.0000   0.0254
  -9.500  -0.4788   0.06687   0.06211  -0.0596   1.0000   0.0249
  -9.250  -0.5040   0.06180   0.05706  -0.0618   1.0000   0.0245
  -9.000  -0.5323   0.05881   0.05409  -0.0604   1.0000   0.0239
  -8.750  -0.5585   0.05589   0.05116  -0.0579   1.0000   0.0235
  -8.500  -0.5815   0.05318   0.04834  -0.0547   1.0000   0.0237
  -8.250  -0.5913   0.04886   0.04371  -0.0546   0.9964   0.0241
  -8.000  -0.5796   0.04267   0.03682  -0.0585   0.9871   0.0252
  -7.750  -0.5618   0.03758   0.03091  -0.0607   0.9793   0.0262
  -7.500  -0.5383   0.03382   0.02664  -0.0625   0.9732   0.0273
  -7.250  -0.5121   0.03169   0.02427  -0.0638   0.9673   0.0287
  -7.000  -0.4841   0.02980   0.02210  -0.0650   0.9614   0.0309
  -6.750  -0.4512   0.02798   0.01981  -0.0667   0.9574   0.0352
  -6.500  -0.4257   0.02632   0.01801  -0.0670   0.9507   0.0384
  -6.000  -0.3595   0.02379   0.01509  -0.0701   0.9426   0.0497
  -5.750  -0.3339   0.02305   0.01426  -0.0701   0.9351   0.0565
  -5.500  -0.3021   0.02198   0.01309  -0.0712   0.9307   0.0632
  -5.250  -0.2730   0.02128   0.01230  -0.0717   0.9249   0.0710
  -5.000  -0.2449   0.02044   0.01143  -0.0721   0.9190   0.0775
  -4.750  -0.2119   0.01979   0.01064  -0.0732   0.9150   0.0872
  -4.500  -0.1875   0.01912   0.01000  -0.0729   0.9076   0.0959
  -4.250  -0.1573   0.01847   0.00934  -0.0736   0.9026   0.1092
  -4.000  -0.1297   0.01786   0.00881  -0.0739   0.8967   0.1340
  -3.750  -0.1037   0.01715   0.00834  -0.0740   0.8902   0.1881
  -3.500  -0.0752   0.01615   0.00786  -0.0748   0.8859   0.3063
  -3.250  -0.0563   0.01552   0.00789  -0.0733   0.8776   0.4618
  -3.000  -0.0281   0.01536   0.00794  -0.0730   0.8728   0.5513
  -2.750  -0.0039   0.01541   0.00801  -0.0719   0.8657   0.6004
  -2.500   0.0236   0.01546   0.00802  -0.0713   0.8600   0.6396
  -2.250   0.0495   0.01556   0.00811  -0.0703   0.8542   0.6742
  -2.000   0.0735   0.01566   0.00819  -0.0690   0.8472   0.7016
  -1.750   0.1029   0.01565   0.00809  -0.0688   0.8427   0.7212
  -1.500   0.1252   0.01573   0.00813  -0.0675   0.8345   0.7391
  -1.250   0.1532   0.01570   0.00804  -0.0670   0.8293   0.7564
  -1.000   0.1772   0.01572   0.00801  -0.0660   0.8215   0.7700
  -0.750   0.2057   0.01564   0.00787  -0.0658   0.8157   0.7795
  -0.500   0.2313   0.01562   0.00781  -0.0653   0.8083   0.7889
  -0.250   0.2594   0.01556   0.00767  -0.0652   0.8018   0.7990
   0.000   0.2852   0.01552   0.00762  -0.0646   0.7945   0.8083
   0.250   0.3126   0.01546   0.00753  -0.0643   0.7876   0.8181
   0.500   0.3390   0.01544   0.00748  -0.0640   0.7804   0.8289
   0.750   0.3660   0.01539   0.00742  -0.0636   0.7734   0.8397
   1.000   0.3921   0.01535   0.00739  -0.0630   0.7656   0.8508
   1.250   0.4204   0.01520   0.00723  -0.0627   0.7571   0.8626
   1.500   0.4461   0.01507   0.00712  -0.0619   0.7451   0.8757
   1.750   0.4734   0.01493   0.00698  -0.0615   0.7328   0.8904
   2.000   0.5036   0.01481   0.00690  -0.0616   0.7216   0.9068
   2.250   0.5389   0.01470   0.00679  -0.0628   0.7121   0.9251
   2.500   0.5757   0.01466   0.00680  -0.0646   0.7004   0.9502
   3.000   0.6401   0.01469   0.00685  -0.0668   0.6753   1.0000
   3.250   0.6657   0.01476   0.00690  -0.0664   0.6620   1.0000
   3.500   0.6914   0.01484   0.00695  -0.0661   0.6474   1.0000
   3.750   0.7170   0.01493   0.00704  -0.0656   0.6316   1.0000
   4.000   0.7425   0.01502   0.00712  -0.0651   0.6145   1.0000
   4.250   0.7674   0.01515   0.00722  -0.0645   0.5956   1.0000
   4.500   0.7916   0.01530   0.00736  -0.0638   0.5740   1.0000
   4.750   0.8156   0.01547   0.00752  -0.0630   0.5499   1.0000
   5.000   0.8390   0.01569   0.00767  -0.0621   0.5225   1.0000
   5.250   0.8615   0.01598   0.00786  -0.0610   0.4915   1.0000
   5.750   0.9036   0.01682   0.00844  -0.0587   0.4267   1.0000
   6.000   0.9236   0.01735   0.00884  -0.0574   0.3960   1.0000
   6.250   0.9431   0.01792   0.00930  -0.0562   0.3674   1.0000
   6.500   0.9624   0.01852   0.00980  -0.0549   0.3408   1.0000
   6.750   0.9815   0.01914   0.01038  -0.0537   0.3179   1.0000
   7.000   0.9999   0.01981   0.01096  -0.0524   0.2972   1.0000
   7.250   1.0185   0.02048   0.01159  -0.0511   0.2789   1.0000
   7.500   1.0369   0.02115   0.01225  -0.0499   0.2616   1.0000
   7.750   1.0550   0.02184   0.01294  -0.0486   0.2456   1.0000
   8.000   1.0728   0.02253   0.01366  -0.0473   0.2310   1.0000
   8.250   1.0903   0.02324   0.01444  -0.0459   0.2174   1.0000
   8.500   1.1070   0.02397   0.01521  -0.0445   0.2046   1.0000
   8.750   1.1225   0.02473   0.01601  -0.0429   0.1920   1.0000
   9.000   1.1360   0.02552   0.01682  -0.0411   0.1802   1.0000
   9.250   1.1492   0.02635   0.01771  -0.0393   0.1688   1.0000
   9.500   1.1627   0.02721   0.01866  -0.0375   0.1578   1.0000
   9.750   1.1749   0.02815   0.01966  -0.0357   0.1471   1.0000
  10.000   1.1855   0.02917   0.02075  -0.0339   0.1366   1.0000
  10.250   1.1946   0.03027   0.02188  -0.0321   0.1259   1.0000
  10.500   1.2031   0.03142   0.02307  -0.0304   0.1139   1.0000
  10.750   1.2121   0.03262   0.02435  -0.0288   0.1019   1.0000
  11.000   1.2201   0.03395   0.02572  -0.0274   0.0893   1.0000
  11.250   1.2260   0.03549   0.02723  -0.0260   0.0752   1.0000
  11.500   1.2321   0.03714   0.02891  -0.0247   0.0627   1.0000
  11.750   1.2370   0.03896   0.03080  -0.0235   0.0522   1.0000
  12.000   1.2383   0.04119   0.03306  -0.0222   0.0404   1.0000
  12.250   1.2353   0.04391   0.03579  -0.0210   0.0305   1.0000
  12.500   1.2319   0.04678   0.03879  -0.0200   0.0251   1.0000
  12.750   1.2254   0.05010   0.04217  -0.0194   0.0218   1.0000
  13.000   1.2206   0.05336   0.04560  -0.0190   0.0196   1.0000
  13.250   1.2133   0.05709   0.04949  -0.0191   0.0182   1.0000
  13.500   1.2038   0.06126   0.05381  -0.0196   0.0172   1.0000
  13.750   1.1925   0.06592   0.05862  -0.0206   0.0167   1.0000
  14.000   1.1814   0.07086   0.06373  -0.0220   0.0164   1.0000
  14.250   1.1700   0.07615   0.06922  -0.0238   0.0160   1.0000
  14.500   1.1577   0.08192   0.07520  -0.0262   0.0158   1.0000
  14.750   1.1452   0.08806   0.08153  -0.0289   0.0156   1.0000
  15.000   1.1315   0.09470   0.08835  -0.0321   0.0153   1.0000
  15.250   1.1189   0.10140   0.09522  -0.0354   0.0153   1.0000
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