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HQ 3.5/10 AIRFOIL (hq3510-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 3.5/10 AIRFOIL (hq3510-il)
Reynolds number: 1,000,000
Max Cl/Cd: 106.93 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq3510-il-1000000-n5.txt
Download as CSV file: xf-hq3510-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 3.5/10 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3112   0.08920   0.08759  -0.0498   0.9827   0.0039
  -9.000  -0.3000   0.08457   0.08296  -0.0543   0.9773   0.0040
  -8.500  -0.4122   0.02470   0.02186  -0.1055   0.9026   0.0032
  -8.250  -0.3989   0.02081   0.01751  -0.1056   0.8935   0.0033
  -8.000  -0.3754   0.01995   0.01653  -0.1056   0.8873   0.0034
  -7.750  -0.3533   0.01842   0.01476  -0.1056   0.8805   0.0035
  -7.500  -0.3284   0.01780   0.01404  -0.1055   0.8748   0.0037
  -7.250  -0.3049   0.01637   0.01236  -0.1054   0.8685   0.0038
  -7.000  -0.2803   0.01533   0.01111  -0.1053   0.8628   0.0040
  -6.750  -0.2549   0.01437   0.00995  -0.1052   0.8573   0.0043
  -6.500  -0.2293   0.01350   0.00890  -0.1051   0.8515   0.0045
  -6.250  -0.2034   0.01272   0.00795  -0.1050   0.8464   0.0047
  -6.000  -0.1768   0.01210   0.00720  -0.1049   0.8408   0.0049
  -5.750  -0.1503   0.01153   0.00650  -0.1048   0.8354   0.0051
  -5.500  -0.1234   0.01102   0.00588  -0.1047   0.8303   0.0052
  -5.250  -0.0960   0.01079   0.00559  -0.1047   0.8246   0.0054
  -5.000  -0.0704   0.00975   0.00435  -0.1045   0.8194   0.0060
  -4.750  -0.0431   0.00930   0.00384  -0.1045   0.8136   0.0064
  -4.500  -0.0158   0.00895   0.00342  -0.1044   0.8079   0.0068
  -4.250   0.0117   0.00865   0.00305  -0.1044   0.8024   0.0072
  -4.000   0.0394   0.00839   0.00273  -0.1044   0.7961   0.0075
  -3.750   0.0671   0.00818   0.00244  -0.1044   0.7903   0.0079
  -3.500   0.0950   0.00798   0.00219  -0.1044   0.7837   0.0081
  -3.250   0.1227   0.00783   0.00197  -0.1043   0.7768   0.0083
  -3.000   0.1504   0.00770   0.00178  -0.1043   0.7674   0.0088
  -2.750   0.1781   0.00759   0.00159  -0.1042   0.7558   0.0094
  -2.500   0.2056   0.00751   0.00143  -0.1041   0.7431   0.0101
  -2.250   0.2332   0.00743   0.00131  -0.1040   0.7316   0.0122
  -2.000   0.2607   0.00730   0.00120  -0.1040   0.7213   0.0288
  -1.750   0.2884   0.00723   0.00113  -0.1039   0.7109   0.0382
  -1.500   0.3161   0.00717   0.00106  -0.1039   0.7004   0.0505
  -1.250   0.3437   0.00712   0.00101  -0.1039   0.6892   0.0639
  -1.000   0.3713   0.00706   0.00096  -0.1039   0.6790   0.0870
  -0.500   0.4249   0.00626   0.00086  -0.1042   0.6538   0.3799
  -0.250   0.4514   0.00596   0.00089  -0.1042   0.6401   0.5148
   0.000   0.4785   0.00589   0.00093  -0.1041   0.6271   0.5756
   0.250   0.5055   0.00587   0.00099  -0.1039   0.6134   0.6280
   0.500   0.5323   0.00592   0.00105  -0.1037   0.5969   0.6590
   0.750   0.5593   0.00601   0.00110  -0.1036   0.5793   0.6725
   1.000   0.5863   0.00612   0.00115  -0.1034   0.5610   0.6798
   1.250   0.6129   0.00626   0.00121  -0.1032   0.5399   0.6870
   1.500   0.6390   0.00645   0.00129  -0.1029   0.5119   0.6941
   1.750   0.6648   0.00666   0.00139  -0.1026   0.4818   0.7021
   2.000   0.6907   0.00687   0.00151  -0.1023   0.4543   0.7097
   2.250   0.7163   0.00711   0.00164  -0.1019   0.4253   0.7181
   2.500   0.7416   0.00735   0.00178  -0.1016   0.3955   0.7264
   2.750   0.7670   0.00761   0.00192  -0.1012   0.3670   0.7356
   3.000   0.7919   0.00789   0.00210  -0.1007   0.3337   0.7453
   3.250   0.8165   0.00820   0.00228  -0.1003   0.3022   0.7552
   3.500   0.8416   0.00845   0.00246  -0.0999   0.2796   0.7657
   3.750   0.8674   0.00864   0.00262  -0.0996   0.2660   0.7768
   4.000   0.8931   0.00880   0.00280  -0.0993   0.2549   0.7884
   4.250   0.9187   0.00897   0.00297  -0.0989   0.2456   0.8013
   4.500   0.9443   0.00912   0.00313  -0.0986   0.2361   0.8164
   4.750   0.9692   0.00927   0.00331  -0.0981   0.2246   0.8355
   5.000   0.9921   0.00949   0.00353  -0.0973   0.2039   0.8652
   5.250   1.0190   0.00953   0.00371  -0.0973   0.1910   1.0000
   5.500   1.0437   0.00983   0.00393  -0.0968   0.1730   1.0000
   5.750   1.0668   0.01026   0.00422  -0.0962   0.1463   1.0000
   6.000   1.0888   0.01077   0.00457  -0.0954   0.1173   1.0000
   6.250   1.1080   0.01153   0.00509  -0.0942   0.0765   1.0000
   6.500   1.1237   0.01262   0.00584  -0.0924   0.0243   1.0000
   6.750   1.1431   0.01337   0.00647  -0.0911   0.0046   1.0000
   7.000   1.1662   0.01375   0.00686  -0.0904   0.0034   1.0000
   7.250   1.1894   0.01410   0.00723  -0.0897   0.0031   1.0000
   7.500   1.2121   0.01448   0.00765  -0.0890   0.0029   1.0000
   7.750   1.2342   0.01489   0.00813  -0.0881   0.0026   1.0000
   8.000   1.2557   0.01534   0.00862  -0.0872   0.0024   1.0000
   8.250   1.2765   0.01583   0.00917  -0.0862   0.0023   1.0000
   8.500   1.2964   0.01636   0.00975  -0.0850   0.0021   1.0000
   8.750   1.3150   0.01698   0.01044  -0.0836   0.0019   1.0000
   9.000   1.3300   0.01787   0.01142  -0.0817   0.0017   1.0000
   9.250   1.3458   0.01850   0.01212  -0.0798   0.0016   1.0000
   9.500   1.3615   0.01905   0.01274  -0.0780   0.0016   1.0000
   9.750   1.3752   0.01972   0.01348  -0.0759   0.0016   1.0000
  10.000   1.3886   0.02041   0.01423  -0.0738   0.0015   1.0000
  10.250   1.4016   0.02114   0.01502  -0.0717   0.0015   1.0000
  10.500   1.4128   0.02199   0.01595  -0.0695   0.0014   1.0000
  10.750   1.4228   0.02294   0.01699  -0.0672   0.0014   1.0000
  11.000   1.4321   0.02395   0.01808  -0.0649   0.0014   1.0000
  11.250   1.4398   0.02510   0.01933  -0.0626   0.0013   1.0000
  11.500   1.4492   0.02616   0.02047  -0.0607   0.0013   1.0000
  11.750   1.4556   0.02749   0.02190  -0.0585   0.0012   1.0000
  12.000   1.4613   0.02891   0.02342  -0.0564   0.0012   1.0000
  12.500   1.4726   0.03194   0.02665  -0.0529   0.0011   1.0000
  12.750   1.4745   0.03387   0.02869  -0.0511   0.0011   1.0000
  13.000   1.4796   0.03559   0.03050  -0.0497   0.0010   1.0000
  13.250   1.4808   0.03774   0.03277  -0.0483   0.0010   1.0000
  13.500   1.4807   0.04013   0.03528  -0.0471   0.0009   1.0000
  13.750   1.4797   0.04274   0.03800  -0.0462   0.0009   1.0000
  14.000   1.4770   0.04565   0.04103  -0.0455   0.0009   1.0000
  14.250   1.4725   0.04893   0.04444  -0.0450   0.0009   1.0000
  14.500   1.4731   0.05177   0.04737  -0.0450   0.0008   1.0000
  14.750   1.4663   0.05571   0.05144  -0.0452   0.0008   1.0000
  15.000   1.4576   0.06016   0.05603  -0.0459   0.0008   1.0000
  15.250   1.4479   0.06505   0.06106  -0.0470   0.0008   1.0000
  15.500   1.4430   0.06947   0.06559  -0.0484   0.0008   1.0000
  15.750   1.4306   0.07534   0.07161  -0.0506   0.0008   1.0000
  16.000   1.4167   0.08184   0.07826  -0.0532   0.0008   1.0000
  16.250   1.4048   0.08829   0.08484  -0.0562   0.0008   1.0000
  16.500   1.3905   0.09546   0.09216  -0.0597   0.0008   1.0000
  16.750   1.3741   0.10329   0.10013  -0.0636   0.0008   1.0000
  17.000   1.3596   0.11097   0.10794  -0.0676   0.0008   1.0000
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