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HQ 2.0/12 AIRFOIL (hq2012-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: HQ 2.0/12 AIRFOIL (hq2012-il)
Reynolds number: 50,000
Max Cl/Cd: 33.2 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-hq2012-il-50000.txt
Download as CSV file: xf-hq2012-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 2.0/12 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3788   0.10114   0.09418  -0.0171   1.0000   0.3373
  -8.750  -0.3756   0.09807   0.09116  -0.0167   1.0000   0.3506
  -8.500  -0.3729   0.09503   0.08818  -0.0161   1.0000   0.3646
  -8.250  -0.3657   0.09201   0.08520  -0.0151   1.0000   0.3817
  -8.000  -0.3618   0.08908   0.08231  -0.0141   1.0000   0.3969
  -7.750  -0.5571   0.06765   0.06129  -0.0445   1.0000   0.1508
  -7.500  -0.5913   0.06228   0.05550  -0.0441   1.0000   0.1377
  -7.250  -0.5867   0.05842   0.05162  -0.0423   1.0000   0.1360
  -7.000  -0.5875   0.05462   0.04768  -0.0406   1.0000   0.1337
  -6.750  -0.5884   0.05070   0.04345  -0.0390   1.0000   0.1313
  -6.500  -0.5855   0.04715   0.03950  -0.0375   1.0000   0.1316
  -6.250  -0.5787   0.04388   0.03575  -0.0361   1.0000   0.1341
  -6.000  -0.5682   0.04072   0.03193  -0.0347   1.0000   0.1367
  -5.750  -0.5531   0.03796   0.02904  -0.0334   1.0000   0.1418
  -5.500  -0.5367   0.03578   0.02642  -0.0321   1.0000   0.1503
  -5.250  -0.5183   0.03355   0.02403  -0.0310   1.0000   0.1583
  -5.000  -0.4991   0.03172   0.02191  -0.0299   1.0000   0.1704
  -4.750  -0.4780   0.03003   0.01990  -0.0287   1.0000   0.1824
  -4.500  -0.4575   0.02860   0.01850  -0.0276   1.0000   0.1997
  -4.250  -0.4362   0.02721   0.01713  -0.0264   1.0000   0.2190
  -4.000  -0.4161   0.02594   0.01598  -0.0251   1.0000   0.2490
  -3.750  -0.3957   0.02444   0.01478  -0.0238   1.0000   0.2953
  -3.500  -0.3798   0.02254   0.01400  -0.0218   1.0000   0.4127
  -3.250  -0.3799   0.02253   0.01522  -0.0137   1.0000   0.6290
  -3.000  -0.3797   0.02324   0.01602  -0.0057   1.0000   0.7148
  -2.750  -0.3784   0.02363   0.01639   0.0016   1.0000   0.7705
  -2.500  -0.3763   0.02372   0.01642   0.0083   1.0000   0.8201
  -2.250  -0.3701   0.02368   0.01633   0.0143   1.0000   0.8691
  -2.000  -0.2828   0.02502   0.01722   0.0077   1.0000   0.9464
  -1.750  -0.1018   0.02626   0.01757  -0.0204   1.0000   1.0000
  -1.500  -0.1102   0.02587   0.01713  -0.0172   1.0000   1.0000
  -1.250  -0.1194   0.02542   0.01664  -0.0139   1.0000   1.0000
  -1.000  -0.1291   0.02491   0.01608  -0.0104   1.0000   1.0000
  -0.750  -0.1378   0.02437   0.01547  -0.0070   1.0000   1.0000
  -0.500  -0.1392   0.02400   0.01499  -0.0047   1.0000   1.0000
  -0.250  -0.1291   0.02397   0.01480  -0.0042   1.0000   1.0000
   0.000  -0.1128   0.02418   0.01484  -0.0044   1.0000   1.0000
   0.250  -0.0941   0.02453   0.01503  -0.0050   1.0000   1.0000
   0.500  -0.0745   0.02499   0.01533  -0.0056   1.0000   1.0000
   0.750  -0.0545   0.02553   0.01571  -0.0062   1.0000   1.0000
   1.000  -0.0097   0.02682   0.01686  -0.0114   0.9884   1.0000
   1.250   0.0338   0.02811   0.01801  -0.0162   0.9759   1.0000
   1.500   0.0749   0.02933   0.01913  -0.0205   0.9631   1.0000
   1.750   0.1153   0.03051   0.02024  -0.0244   0.9492   1.0000
   2.000   0.1560   0.03166   0.02133  -0.0282   0.9335   1.0000
   2.250   0.2045   0.03281   0.02245  -0.0329   0.9135   1.0000
   2.500   0.2494   0.03375   0.02338  -0.0366   0.8917   1.0000
   2.750   0.2934   0.03455   0.02421  -0.0399   0.8703   1.0000
   3.000   0.3443   0.03535   0.02504  -0.0440   0.8513   1.0000
   3.250   0.3718   0.03600   0.02575  -0.0445   0.8308   1.0000
   3.500   0.4126   0.03656   0.02637  -0.0466   0.8109   1.0000
   3.750   0.4637   0.03684   0.02676  -0.0497   0.7919   1.0000
   4.000   0.4891   0.03733   0.02736  -0.0494   0.7692   1.0000
   4.250   0.5416   0.03711   0.02729  -0.0519   0.7492   1.0000
   4.500   0.5732   0.03724   0.02757  -0.0518   0.7257   1.0000
   4.750   0.6321   0.03616   0.02671  -0.0539   0.7054   1.0000
   5.000   0.6661   0.03577   0.02647  -0.0532   0.6811   1.0000
   5.250   0.7222   0.03399   0.02492  -0.0538   0.6607   1.0000
   5.500   0.7559   0.03331   0.02437  -0.0525   0.6348   1.0000
   5.750   0.7975   0.03210   0.02332  -0.0516   0.6099   1.0000
   6.000   0.8443   0.03050   0.02180  -0.0511   0.5850   1.0000
   6.250   0.8777   0.02985   0.02118  -0.0497   0.5570   1.0000
   6.500   0.9070   0.02955   0.02091  -0.0482   0.5284   1.0000
   6.750   0.9350   0.02943   0.02076  -0.0467   0.4995   1.0000
   7.000   0.9615   0.02950   0.02075  -0.0451   0.4698   1.0000
   7.250   0.9869   0.02974   0.02087  -0.0435   0.4392   1.0000
   7.500   1.0075   0.03035   0.02142  -0.0416   0.4076   1.0000
   7.750   1.0257   0.03121   0.02221  -0.0396   0.3754   1.0000
   8.000   1.0433   0.03221   0.02310  -0.0376   0.3420   1.0000
   8.250   1.0631   0.03340   0.02402  -0.0358   0.3078   1.0000
   8.500   1.0804   0.03509   0.02554  -0.0341   0.2757   1.0000
   8.750   1.0984   0.03702   0.02735  -0.0325   0.2471   1.0000
   9.000   1.1097   0.03909   0.02961  -0.0304   0.2249   1.0000
   9.250   1.1277   0.04139   0.03196  -0.0291   0.2076   1.0000
   9.500   1.1424   0.04367   0.03440  -0.0275   0.1936   1.0000
   9.750   1.1539   0.04608   0.03702  -0.0257   0.1821   1.0000
  10.000   1.1703   0.04874   0.03979  -0.0246   0.1732   1.0000
  10.250   1.1715   0.05204   0.04354  -0.0221   0.1676   1.0000
  10.500   1.1880   0.05469   0.04626  -0.0212   0.1602   1.0000
  10.750   1.1742   0.05846   0.05053  -0.0179   0.1571   1.0000
  11.000   1.1616   0.06217   0.05458  -0.0152   0.1541   1.0000
  11.250   1.1529   0.06575   0.05839  -0.0130   0.1513   1.0000
  11.500   1.1437   0.06955   0.06234  -0.0109   0.1496   1.0000
  11.750   1.1323   0.07381   0.06675  -0.0093   0.1484   1.0000
  12.000   1.1174   0.07866   0.07173  -0.0084   0.1476   1.0000
  12.250   0.8548   0.11929   0.11208  -0.0342   0.1863   1.0000
  12.500   0.8506   0.12628   0.11907  -0.0367   0.1884   1.0000
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