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HQ 2.5/12 AIRFOIL (hq2512-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 2.5/12 AIRFOIL (hq2512-il)
Reynolds number: 50,000
Max Cl/Cd: 36.06 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq2512-il-50000-n5.txt
Download as CSV file: xf-hq2512-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4067   0.10211   0.09504  -0.0423   1.0000   0.0522
 -10.000  -0.4100   0.09768   0.09070  -0.0442   1.0000   0.0522
  -9.500  -0.4544   0.08057   0.07378  -0.0566   1.0000   0.0472
  -9.250  -0.4689   0.07616   0.06944  -0.0583   1.0000   0.0470
  -9.000  -0.4873   0.07262   0.06597  -0.0586   1.0000   0.0468
  -8.750  -0.5055   0.06946   0.06286  -0.0577   1.0000   0.0466
  -8.500  -0.5236   0.06622   0.05959  -0.0566   1.0000   0.0465
  -8.250  -0.5413   0.06307   0.05635  -0.0549   1.0000   0.0466
  -8.000  -0.5561   0.05993   0.05304  -0.0529   1.0000   0.0468
  -7.750  -0.5678   0.05668   0.04952  -0.0508   1.0000   0.0471
  -7.500  -0.5722   0.05357   0.04626  -0.0490   1.0000   0.0478
  -7.250  -0.5715   0.05081   0.04333  -0.0473   1.0000   0.0487
  -7.000  -0.5680   0.04808   0.04038  -0.0457   1.0000   0.0496
  -6.750  -0.5615   0.04547   0.03752  -0.0442   1.0000   0.0509
  -6.500  -0.5523   0.04312   0.03487  -0.0429   1.0000   0.0535
  -6.250  -0.5409   0.04051   0.03175  -0.0418   1.0000   0.0574
  -6.000  -0.5221   0.03764   0.02828  -0.0415   0.9985   0.0608
  -5.750  -0.4920   0.03562   0.02612  -0.0432   0.9932   0.0664
  -5.500  -0.4603   0.03350   0.02335  -0.0445   0.9876   0.0740
  -5.250  -0.4290   0.03193   0.02172  -0.0459   0.9827   0.0819
  -5.000  -0.3989   0.03047   0.02004  -0.0466   0.9770   0.0905
  -4.750  -0.3656   0.02939   0.01868  -0.0477   0.9720   0.1013
  -4.500  -0.3375   0.02834   0.01765  -0.0481   0.9661   0.1115
  -4.250  -0.3071   0.02737   0.01657  -0.0488   0.9604   0.1221
  -4.000  -0.2764   0.02655   0.01570  -0.0499   0.9547   0.1417
  -3.750  -0.2480   0.02565   0.01490  -0.0508   0.9482   0.1671
  -3.500  -0.2154   0.02448   0.01408  -0.0527   0.9431   0.2308
  -3.250  -0.1948   0.02311   0.01380  -0.0525   0.9360   0.3984
  -3.000  -0.1703   0.02306   0.01427  -0.0509   0.9299   0.5681
  -2.750  -0.1493   0.02333   0.01453  -0.0489   0.9221   0.6412
  -2.500  -0.1241   0.02367   0.01481  -0.0473   0.9158   0.6988
  -2.250  -0.1075   0.02394   0.01506  -0.0439   0.9079   0.7449
  -2.000  -0.0842   0.02412   0.01514  -0.0418   0.9017   0.7856
  -1.750  -0.0655   0.02417   0.01511  -0.0393   0.8940   0.8160
  -1.500  -0.0384   0.02417   0.01501  -0.0384   0.8879   0.8458
  -1.250  -0.0129   0.02416   0.01489  -0.0376   0.8807   0.8715
  -1.000   0.0235   0.02416   0.01472  -0.0393   0.8746   0.8896
  -0.750   0.0635   0.02418   0.01459  -0.0419   0.8690   0.9058
  -0.500   0.1037   0.02425   0.01452  -0.0447   0.8620   0.9222
  -0.250   0.1561   0.02427   0.01440  -0.0497   0.8577   0.9374
   0.000   0.1975   0.02439   0.01444  -0.0531   0.8497   0.9563
   0.250   0.2504   0.02439   0.01431  -0.0584   0.8443   0.9730
   0.500   0.2918   0.02449   0.01435  -0.0620   0.8360   1.0000
   0.750   0.3191   0.02447   0.01424  -0.0625   0.8286   1.0000
   1.000   0.3327   0.02469   0.01437  -0.0609   0.8172   1.0000
   1.250   0.3554   0.02489   0.01450  -0.0607   0.8077   1.0000
   1.500   0.3884   0.02495   0.01450  -0.0619   0.8003   1.0000
   1.750   0.4100   0.02524   0.01474  -0.0614   0.7894   1.0000
   2.000   0.4380   0.02539   0.01485  -0.0616   0.7796   1.0000
   2.250   0.4751   0.02522   0.01466  -0.0628   0.7707   1.0000
   2.500   0.5019   0.02523   0.01466  -0.0625   0.7576   1.0000
   2.750   0.5296   0.02519   0.01462  -0.0621   0.7444   1.0000
   3.000   0.5570   0.02518   0.01461  -0.0617   0.7314   1.0000
   3.250   0.5844   0.02518   0.01466  -0.0613   0.7186   1.0000
   3.500   0.6122   0.02517   0.01468  -0.0610   0.7059   1.0000
   3.750   0.6403   0.02513   0.01468  -0.0606   0.6929   1.0000
   4.000   0.6680   0.02507   0.01467  -0.0601   0.6791   1.0000
   4.250   0.6949   0.02502   0.01472  -0.0594   0.6642   1.0000
   4.500   0.7211   0.02498   0.01474  -0.0586   0.6481   1.0000
   4.750   0.7476   0.02490   0.01473  -0.0578   0.6310   1.0000
   5.000   0.7754   0.02474   0.01467  -0.0570   0.6131   1.0000
   5.250   0.7973   0.02484   0.01485  -0.0557   0.5915   1.0000
   5.500   0.8239   0.02474   0.01479  -0.0547   0.5698   1.0000
   5.750   0.8461   0.02486   0.01496  -0.0533   0.5445   1.0000
   6.000   0.8696   0.02496   0.01511  -0.0521   0.5178   1.0000
   6.250   0.8927   0.02515   0.01527  -0.0508   0.4895   1.0000
   6.500   0.9148   0.02547   0.01553  -0.0494   0.4603   1.0000
   6.750   0.9354   0.02594   0.01592  -0.0480   0.4317   1.0000
   7.000   0.9549   0.02656   0.01646  -0.0466   0.4047   1.0000
   7.250   0.9737   0.02728   0.01713  -0.0452   0.3797   1.0000
   7.500   0.9913   0.02811   0.01793  -0.0438   0.3564   1.0000
   7.750   1.0088   0.02899   0.01878  -0.0424   0.3349   1.0000
   8.000   1.0258   0.02992   0.01971  -0.0410   0.3148   1.0000
   8.250   1.0430   0.03089   0.02064  -0.0397   0.2965   1.0000
   8.500   1.0594   0.03194   0.02176  -0.0384   0.2786   1.0000
   8.750   1.0756   0.03303   0.02292  -0.0371   0.2619   1.0000
   9.000   1.0910   0.03416   0.02412  -0.0357   0.2459   1.0000
   9.250   1.1059   0.03532   0.02536  -0.0343   0.2314   1.0000
   9.500   1.1199   0.03652   0.02667  -0.0328   0.2177   1.0000
   9.750   1.1345   0.03779   0.02803  -0.0314   0.2053   1.0000
  10.000   1.1479   0.03908   0.02940  -0.0300   0.1936   1.0000
  10.250   1.1593   0.04043   0.03090  -0.0284   0.1823   1.0000
  10.500   1.1686   0.04197   0.03265  -0.0267   0.1715   1.0000
  10.750   1.1786   0.04358   0.03443  -0.0252   0.1616   1.0000
  11.000   1.1876   0.04512   0.03601  -0.0237   0.1525   1.0000
  11.250   1.1931   0.04698   0.03811  -0.0221   0.1435   1.0000
  11.500   1.1986   0.04900   0.04033  -0.0206   0.1352   1.0000
  11.750   1.2031   0.05074   0.04207  -0.0192   0.1270   1.0000
  12.000   1.1993   0.05343   0.04510  -0.0178   0.1190   1.0000
  12.250   1.1975   0.05577   0.04749  -0.0167   0.1113   1.0000
  12.500   1.1888   0.05870   0.05063  -0.0158   0.1036   1.0000
  12.750   1.1784   0.06201   0.05407  -0.0155   0.0961   1.0000
  13.000   1.1685   0.06535   0.05747  -0.0156   0.0891   1.0000
  13.250   1.1549   0.06980   0.06214  -0.0164   0.0826   1.0000
  13.500   1.1440   0.07387   0.06624  -0.0174   0.0765   1.0000
  13.750   1.1301   0.07913   0.07172  -0.0191   0.0712   1.0000
  14.000   1.1176   0.08437   0.07711  -0.0211   0.0663   1.0000
  14.250   1.1061   0.08959   0.08239  -0.0233   0.0617   1.0000
  14.500   1.0897   0.09659   0.08964  -0.0265   0.0585   1.0000
  14.750   1.0753   0.10339   0.09662  -0.0298   0.0556   1.0000
  15.000   1.0694   0.10806   0.10119  -0.0322   0.0511   1.0000
  15.250   1.0524   0.11630   0.10971  -0.0365   0.0501   1.0000
  15.500   1.0319   0.12584   0.11942  -0.0417   0.0497   1.0000
  15.750   1.0104   0.13622   0.12994  -0.0474   0.0500   1.0000
  16.000   0.9874   0.14783   0.14159  -0.0538   0.0505   1.0000
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