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HQ 3.5/9 AIRFOIL (hq359-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/9 AIRFOIL (hq359-il)
Reynolds number: 50,000
Max Cl/Cd: 41.98 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq359-il-50000-n5.txt
Download as CSV file: xf-hq359-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/9 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3561   0.10235   0.09595  -0.0361   1.0000   0.0902
  -7.750  -0.3748   0.10158   0.09537  -0.0358   1.0000   0.0910
  -7.500  -0.3893   0.10007   0.09401  -0.0367   1.0000   0.0913
  -7.250  -0.3838   0.09607   0.09008  -0.0337   1.0000   0.0924
  -7.000  -0.3823   0.09311   0.08718  -0.0315   1.0000   0.0936
  -6.750  -0.3853   0.09060   0.08468  -0.0303   1.0000   0.0947
  -6.500  -0.3896   0.08802   0.08219  -0.0297   1.0000   0.0957
  -6.250  -0.3932   0.08543   0.07966  -0.0298   1.0000   0.0966
  -6.000  -0.3956   0.08257   0.07686  -0.0304   1.0000   0.0975
  -5.750  -0.3847   0.07574   0.06983  -0.0369   1.0000   0.0477
  -5.500  -0.3818   0.07237   0.06648  -0.0369   1.0000   0.0445
  -5.250  -0.3646   0.06669   0.06048  -0.0444   1.0000   0.0371
  -5.000  -0.3587   0.06339   0.05716  -0.0435   1.0000   0.0359
  -4.750  -0.3474   0.05988   0.05357  -0.0446   1.0000   0.0348
  -4.500  -0.3298   0.05608   0.04959  -0.0468   0.9994   0.0335
  -4.250  -0.2947   0.05131   0.04447  -0.0525   0.9947   0.0319
  -4.000  -0.2584   0.04685   0.03959  -0.0574   0.9899   0.0305
  -3.750  -0.2192   0.04272   0.03491  -0.0620   0.9858   0.0291
  -3.500  -0.1821   0.03919   0.03080  -0.0652   0.9814   0.0282
  -3.250  -0.1440   0.03616   0.02717  -0.0679   0.9772   0.0274
  -3.000  -0.1054   0.03361   0.02406  -0.0703   0.9736   0.0273
  -2.750  -0.0723   0.03176   0.02181  -0.0716   0.9687   0.0284
  -2.500  -0.0377   0.03026   0.01989  -0.0730   0.9640   0.0314
  -2.250  -0.0015   0.02896   0.01822  -0.0742   0.9601   0.0346
  -2.000   0.0274   0.02795   0.01688  -0.0739   0.9540   0.0371
  -1.750   0.0610   0.02683   0.01563  -0.0750   0.9492   0.0417
  -1.500   0.0958   0.02603   0.01455  -0.0763   0.9440   0.0516
  -1.250   0.1317   0.02476   0.01362  -0.0787   0.9385   0.1227
  -1.000   0.1442   0.02151   0.01348  -0.0730   0.9338   1.0000
  -0.750   0.1762   0.02177   0.01308  -0.0742   0.9259   1.0000
  -0.500   0.2158   0.02208   0.01289  -0.0769   0.9201   1.0000
  -0.250   0.2456   0.02236   0.01282  -0.0778   0.9113   1.0000
   0.000   0.2830   0.02266   0.01278  -0.0800   0.9048   1.0000
   0.250   0.3143   0.02295   0.01279  -0.0811   0.8960   1.0000
   0.500   0.3466   0.02324   0.01287  -0.0824   0.8875   1.0000
   0.750   0.3838   0.02348   0.01292  -0.0844   0.8801   1.0000
   1.000   0.4128   0.02377   0.01307  -0.0849   0.8701   1.0000
   1.250   0.4458   0.02401   0.01316  -0.0861   0.8612   1.0000
   1.500   0.4824   0.02418   0.01325  -0.0878   0.8531   1.0000
   1.750   0.5109   0.02444   0.01345  -0.0881   0.8423   1.0000
   2.000   0.5432   0.02456   0.01355  -0.0888   0.8311   1.0000
   2.250   0.5779   0.02447   0.01347  -0.0895   0.8179   1.0000
   2.500   0.6123   0.02425   0.01324  -0.0900   0.8032   1.0000
   2.750   0.6457   0.02400   0.01301  -0.0902   0.7885   1.0000
   3.000   0.6771   0.02386   0.01291  -0.0902   0.7745   1.0000
   3.250   0.7072   0.02378   0.01289  -0.0900   0.7608   1.0000
   3.500   0.7371   0.02369   0.01293  -0.0898   0.7465   1.0000
   3.750   0.7672   0.02355   0.01287  -0.0895   0.7315   1.0000
   4.000   0.7958   0.02344   0.01286  -0.0890   0.7149   1.0000
   4.250   0.8213   0.02345   0.01297  -0.0880   0.6954   1.0000
   4.500   0.8514   0.02324   0.01298  -0.0875   0.6762   1.0000
   4.750   0.8766   0.02325   0.01312  -0.0864   0.6523   1.0000
   5.000   0.9032   0.02321   0.01319  -0.0854   0.6259   1.0000
   5.250   0.9300   0.02320   0.01326  -0.0844   0.5963   1.0000
   5.500   0.9557   0.02329   0.01346  -0.0832   0.5627   1.0000
   5.750   0.9810   0.02349   0.01366  -0.0821   0.5267   1.0000
   6.000   1.0042   0.02392   0.01404  -0.0807   0.4896   1.0000
   6.250   1.0267   0.02451   0.01454  -0.0795   0.4552   1.0000
   6.500   1.0478   0.02527   0.01526  -0.0782   0.4236   1.0000
   6.750   1.0685   0.02611   0.01609  -0.0770   0.3954   1.0000
   7.000   1.0889   0.02701   0.01712  -0.0758   0.3699   1.0000
   7.250   1.1089   0.02796   0.01809  -0.0746   0.3461   1.0000
   7.500   1.1278   0.02893   0.01918  -0.0734   0.3228   1.0000
   7.750   1.1457   0.02996   0.02030  -0.0720   0.2997   1.0000
   8.000   1.1625   0.03104   0.02145  -0.0705   0.2771   1.0000
   8.250   1.1774   0.03220   0.02273  -0.0688   0.2540   1.0000
   8.500   1.1897   0.03340   0.02411  -0.0669   0.2299   1.0000
   8.750   1.1984   0.03465   0.02549  -0.0646   0.2051   1.0000
   9.000   1.2033   0.03596   0.02691  -0.0619   0.1794   1.0000
   9.250   1.2056   0.03742   0.02839  -0.0591   0.1544   1.0000
   9.500   1.2069   0.03922   0.03027  -0.0565   0.1311   1.0000
   9.750   1.2094   0.04134   0.03240  -0.0543   0.1086   1.0000
  10.000   1.2115   0.04386   0.03489  -0.0521   0.0935   1.0000
  10.250   1.2134   0.04657   0.03764  -0.0501   0.0807   1.0000
  10.500   1.2124   0.04941   0.04055  -0.0484   0.0686   1.0000
  10.750   1.2138   0.05247   0.04382  -0.0467   0.0593   1.0000
  11.000   1.2139   0.05591   0.04741  -0.0451   0.0522   1.0000
  11.250   1.2086   0.05929   0.05089  -0.0441   0.0458   1.0000
  11.500   1.2036   0.06316   0.05502  -0.0434   0.0402   1.0000
  11.750   1.1974   0.06706   0.05913  -0.0431   0.0361   1.0000
  12.000   1.1888   0.07127   0.06333  -0.0433   0.0332   1.0000
  12.250   1.1821   0.07598   0.06843  -0.0436   0.0308   1.0000
  12.500   1.1730   0.08114   0.07392  -0.0446   0.0290   1.0000
  12.750   1.1628   0.08663   0.07968  -0.0461   0.0278   1.0000
  13.000   1.1511   0.09255   0.08586  -0.0483   0.0271   1.0000
  13.250   1.1386   0.09897   0.09251  -0.0511   0.0267   1.0000
  13.500   1.1249   0.10611   0.09989  -0.0547   0.0267   1.0000
  13.750   1.1095   0.11414   0.10816  -0.0591   0.0270   1.0000
  14.000   1.0930   0.12317   0.11741  -0.0643   0.0280   1.0000
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