Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

HQ 0/10 AIRFOIL (hq010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/10 AIRFOIL (hq010-il)
Reynolds number: 1,000,000
Max Cl/Cd: 70.74 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq010-il-1000000-n5.txt
Download as CSV file: xf-hq010-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/10 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
  ------ -------- --------- --------- -------- -------- --------
 -16.000  -0.9739   0.11124   0.10919   0.0102   1.0000   0.0014
 -15.750  -1.0348   0.09340   0.09120   0.0006   1.0000   0.0014
 -15.500  -1.0998   0.07450   0.07204  -0.0107   1.0000   0.0014
 -15.250  -1.1293   0.06405   0.06142  -0.0176   1.0000   0.0014
 -15.000  -1.1476   0.05681   0.05403  -0.0223   1.0000   0.0013
 -14.750  -1.1729   0.04948   0.04650  -0.0265   1.0000   0.0013
 -14.500  -1.1860   0.04472   0.04158  -0.0286   1.0000   0.0013
 -14.250  -1.1934   0.04112   0.03785  -0.0296   1.0000   0.0013
 -14.000  -1.2042   0.03751   0.03408  -0.0299   1.0000   0.0013
 -13.750  -1.2112   0.03463   0.03105  -0.0295   1.0000   0.0013
 -13.500  -1.2139   0.03242   0.02871  -0.0285   1.0000   0.0013
 -13.250  -1.2179   0.03032   0.02646  -0.0268   1.0000   0.0013
 -13.000  -1.2202   0.02857   0.02456  -0.0245   1.0000   0.0014
 -12.750  -1.2196   0.02718   0.02305  -0.0217   1.0000   0.0014
 -12.500  -1.2168   0.02595   0.02169  -0.0189   1.0000   0.0014
 -12.250  -1.2078   0.02473   0.02033  -0.0169   1.0000   0.0014
 -12.000  -1.1961   0.02354   0.01901  -0.0153   1.0000   0.0014
 -11.750  -1.1824   0.02242   0.01776  -0.0138   1.0000   0.0014
 -11.500  -1.1662   0.02147   0.01670  -0.0126   1.0000   0.0014
 -11.250  -1.1489   0.02055   0.01565  -0.0114   1.0000   0.0014
 -11.000  -1.1309   0.01965   0.01464  -0.0104   1.0000   0.0015
 -10.750  -1.1115   0.01885   0.01374  -0.0094   1.0000   0.0015
 -10.500  -1.0914   0.01809   0.01288  -0.0086   1.0000   0.0015
 -10.250  -1.0705   0.01738   0.01209  -0.0078   1.0000   0.0015
 -10.000  -1.0491   0.01671   0.01133  -0.0070   1.0000   0.0016
  -9.750  -1.0271   0.01609   0.01064  -0.0063   1.0000   0.0016
  -9.500  -1.0045   0.01553   0.01001  -0.0057   1.0000   0.0016
  -9.250  -0.9821   0.01491   0.00930  -0.0050   1.0000   0.0017
  -9.000  -0.9593   0.01432   0.00861  -0.0044   1.0000   0.0020
  -8.750  -0.9360   0.01381   0.00804  -0.0038   1.0000   0.0022
  -8.500  -0.9127   0.01328   0.00747  -0.0032   1.0000   0.0027
  -8.250  -0.8893   0.01275   0.00693  -0.0026   1.0000   0.0038
  -8.000  -0.8659   0.01225   0.00645  -0.0020   1.0000   0.0069
  -7.750  -0.8412   0.01192   0.00611  -0.0016   1.0000   0.0086
  -7.500  -0.8165   0.01158   0.00577  -0.0012   1.0000   0.0099
  -7.250  -0.7882   0.01124   0.00542  -0.0016   0.9899   0.0114
  -7.000  -0.7525   0.01092   0.00509  -0.0036   0.9713   0.0129
  -6.750  -0.7179   0.01065   0.00477  -0.0052   0.9515   0.0136
  -6.500  -0.6903   0.01042   0.00447  -0.0052   0.9246   0.0149
  -6.250  -0.6660   0.01019   0.00420  -0.0046   0.8982   0.0183
  -6.000  -0.6410   0.01000   0.00395  -0.0040   0.8790   0.0206
  -5.750  -0.6155   0.00982   0.00368  -0.0036   0.8638   0.0227
  -5.500  -0.5898   0.00959   0.00343  -0.0032   0.8513   0.0273
  -5.250  -0.5636   0.00941   0.00320  -0.0029   0.8404   0.0307
  -4.750  -0.5109   0.00903   0.00278  -0.0024   0.8172   0.0433
  -4.500  -0.4845   0.00883   0.00258  -0.0022   0.8056   0.0531
  -4.250  -0.4580   0.00862   0.00238  -0.0020   0.7947   0.0662
  -4.000  -0.4315   0.00841   0.00219  -0.0018   0.7838   0.0819
  -3.750  -0.4051   0.00818   0.00200  -0.0016   0.7712   0.1025
  -3.500  -0.3796   0.00783   0.00179  -0.0013   0.7582   0.1459
  -3.250  -0.3532   0.00758   0.00164  -0.0012   0.7466   0.1876
  -3.000  -0.3261   0.00741   0.00152  -0.0011   0.7375   0.2081
  -2.750  -0.2988   0.00728   0.00140  -0.0010   0.7300   0.2250
  -2.500  -0.2716   0.00708   0.00129  -0.0009   0.7227   0.2520
  -2.250  -0.2450   0.00682   0.00116  -0.0008   0.7153   0.2951
  -2.000  -0.2195   0.00638   0.00101  -0.0006   0.7074   0.3823
  -1.750  -0.1925   0.00618   0.00093  -0.0005   0.7009   0.4265
  -1.500  -0.1653   0.00598   0.00086  -0.0004   0.6944   0.4648
  -1.250  -0.1392   0.00568   0.00079  -0.0002   0.6878   0.5349
  -1.000  -0.1117   0.00558   0.00076  -0.0001   0.6783   0.5664
  -0.750  -0.0838   0.00553   0.00074  -0.0001   0.6673   0.5852
  -0.500  -0.0560   0.00551   0.00072   0.0000   0.6542   0.6024
  -0.250  -0.0280   0.00550   0.00071   0.0000   0.6410   0.6163
   0.000   0.0000   0.00550   0.00071   0.0000   0.6295   0.6296
   0.250   0.0280   0.00550   0.00071   0.0000   0.6163   0.6412
   0.500   0.0560   0.00551   0.00072   0.0000   0.6024   0.6541
   0.750   0.0838   0.00553   0.00074   0.0001   0.5852   0.6672
   1.000   0.1117   0.00558   0.00076   0.0001   0.5663   0.6783
   1.250   0.1392   0.00568   0.00079   0.0002   0.5347   0.6878
   1.500   0.1653   0.00598   0.00086   0.0004   0.4645   0.6944
   1.750   0.1925   0.00618   0.00093   0.0005   0.4263   0.7010
   2.000   0.2195   0.00638   0.00101   0.0006   0.3834   0.7075
   2.250   0.2450   0.00682   0.00116   0.0008   0.2960   0.7152
   2.500   0.2716   0.00708   0.00129   0.0009   0.2518   0.7227
   2.750   0.2988   0.00728   0.00140   0.0010   0.2248   0.7300
   3.000   0.3261   0.00741   0.00152   0.0011   0.2079   0.7375
   3.250   0.3533   0.00758   0.00164   0.0011   0.1878   0.7465
   3.500   0.3796   0.00783   0.00179   0.0013   0.1458   0.7583
   3.750   0.4052   0.00818   0.00200   0.0016   0.1026   0.7711
   4.000   0.4315   0.00841   0.00219   0.0018   0.0822   0.7839
   4.250   0.4580   0.00862   0.00238   0.0020   0.0658   0.7947
   4.500   0.4845   0.00882   0.00258   0.0022   0.0532   0.8056
   4.750   0.5109   0.00903   0.00278   0.0024   0.0432   0.8172
   5.250   0.5636   0.00941   0.00320   0.0029   0.0306   0.8403
   5.500   0.5898   0.00959   0.00343   0.0032   0.0274   0.8514
   5.750   0.6155   0.00982   0.00368   0.0036   0.0227   0.8639
   6.000   0.6411   0.01000   0.00394   0.0040   0.0202   0.8790
   6.500   0.6903   0.01043   0.00448   0.0053   0.0146   0.9248
   6.750   0.7180   0.01065   0.00477   0.0052   0.0136   0.9517
   7.000   0.7526   0.01092   0.00509   0.0035   0.0128   0.9714
   7.250   0.7882   0.01124   0.00542   0.0016   0.0113   0.9899
   7.500   0.8165   0.01159   0.00577   0.0012   0.0097   1.0000
   7.750   0.8412   0.01192   0.00611   0.0016   0.0085   1.0000
   8.000   0.8659   0.01224   0.00645   0.0020   0.0072   1.0000
   8.250   0.8889   0.01281   0.00697   0.0026   0.0032   1.0000
   8.500   0.9126   0.01328   0.00747   0.0032   0.0027   1.0000
   8.750   0.9359   0.01381   0.00804   0.0038   0.0022   1.0000
   9.000   0.9592   0.01432   0.00862   0.0044   0.0020   1.0000
   9.250   0.9817   0.01495   0.00936   0.0051   0.0017   1.0000
   9.500   1.0044   0.01553   0.01000   0.0057   0.0016   1.0000
   9.750   1.0269   0.01610   0.01064   0.0064   0.0016   1.0000
  10.000   1.0490   0.01671   0.01134   0.0070   0.0016   1.0000
  10.250   1.0705   0.01737   0.01207   0.0078   0.0015   1.0000
  10.500   1.0913   0.01807   0.01287   0.0086   0.0015   1.0000
  10.750   1.1115   0.01883   0.01372   0.0094   0.0015   1.0000
  11.000   1.1307   0.01965   0.01464   0.0104   0.0015   1.0000
  11.250   1.1491   0.02051   0.01561   0.0114   0.0014   1.0000
  11.500   1.1659   0.02149   0.01672   0.0126   0.0014   1.0000
  11.750   1.1819   0.02246   0.01781   0.0139   0.0014   1.0000
  12.000   1.1955   0.02359   0.01907   0.0153   0.0014   1.0000
  12.250   1.2075   0.02473   0.02034   0.0170   0.0014   1.0000
  12.500   1.2166   0.02595   0.02169   0.0189   0.0014   1.0000
  12.750   1.2201   0.02714   0.02300   0.0217   0.0014   1.0000
  13.000   1.2177   0.02874   0.02475   0.0247   0.0013   1.0000
  13.250   1.2189   0.03024   0.02636   0.0267   0.0014   1.0000
  13.500   1.2151   0.03231   0.02859   0.0284   0.0013   1.0000
  13.750   1.2100   0.03475   0.03118   0.0295   0.0013   1.0000
  14.000   1.2061   0.03732   0.03388   0.0299   0.0013   1.0000
  14.250   1.1937   0.04110   0.03784   0.0295   0.0013   1.0000
  14.500   1.1847   0.04491   0.04178   0.0285   0.0013   1.0000
  14.750   1.1717   0.04969   0.04672   0.0264   0.0013   1.0000
  15.000   1.1530   0.05597   0.05317   0.0228   0.0013   1.0000
  15.250   1.1260   0.06478   0.06217   0.0170   0.0013   1.0000
  15.500   1.0846   0.07805   0.07566   0.0082   0.0014   1.0000
  15.750   1.0341   0.09369   0.09149  -0.0009   0.0014   1.0000
  16.000   0.9657   0.11326   0.11122  -0.0114   0.0014   1.0000
<< Back to HQ 0/10 AIRFOIL (hq010-il)

Polar data table (+)

Polar graphs


<< Back to HQ 0/10 AIRFOIL (hq010-il)