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HQ 1.0/9 AIRFOIL (hq109-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: HQ 1.0/9 AIRFOIL (hq109-il)
Reynolds number: 100,000
Max Cl/Cd: 45 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq109-il-100000-n5.txt
Download as CSV file: xf-hq109-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 1.0/9 AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.5687   0.08885   0.08400  -0.0162   1.0000   0.0211
  -9.250  -0.5736   0.08309   0.07830  -0.0198   1.0000   0.0209
  -9.000  -0.5824   0.07591   0.07119  -0.0252   1.0000   0.0202
  -8.750  -0.6241   0.06176   0.05693  -0.0352   1.0000   0.0168
  -8.250  -0.6365   0.05421   0.04905  -0.0367   1.0000   0.0177
  -8.000  -0.6346   0.05097   0.04564  -0.0367   1.0000   0.0183
  -7.750  -0.6300   0.04763   0.04207  -0.0365   1.0000   0.0191
  -7.500  -0.6250   0.04349   0.03756  -0.0360   1.0000   0.0194
  -7.250  -0.6168   0.03946   0.03309  -0.0352   1.0000   0.0197
  -7.000  -0.6054   0.03567   0.02881  -0.0340   1.0000   0.0200
  -6.750  -0.5907   0.03238   0.02504  -0.0327   1.0000   0.0205
  -6.500  -0.5735   0.02951   0.02171  -0.0313   1.0000   0.0214
  -6.250  -0.5545   0.02702   0.01881  -0.0299   1.0000   0.0225
  -6.000  -0.5339   0.02523   0.01667  -0.0286   1.0000   0.0247
  -5.750  -0.5149   0.02346   0.01476  -0.0274   1.0000   0.0280
  -5.500  -0.4950   0.02207   0.01326  -0.0261   1.0000   0.0308
  -5.250  -0.4753   0.02069   0.01173  -0.0245   1.0000   0.0343
  -5.000  -0.4568   0.01944   0.01034  -0.0230   1.0000   0.0394
  -4.750  -0.4373   0.01870   0.00950  -0.0216   1.0000   0.0492
  -4.500  -0.4193   0.01776   0.00857  -0.0202   1.0000   0.0610
  -4.250  -0.4009   0.01700   0.00783  -0.0188   1.0000   0.0770
  -4.000  -0.3825   0.01628   0.00719  -0.0175   1.0000   0.0991
  -3.750  -0.3634   0.01559   0.00661  -0.0163   0.9999   0.1285
  -3.500  -0.3302   0.01464   0.00605  -0.0183   0.9927   0.2170
  -3.250  -0.2996   0.01346   0.00562  -0.0199   0.9856   0.3874
  -3.000  -0.2705   0.01287   0.00564  -0.0202   0.9778   0.5473
  -2.750  -0.2371   0.01275   0.00566  -0.0211   0.9711   0.6316
  -2.500  -0.2067   0.01272   0.00569  -0.0211   0.9628   0.6907
  -2.250  -0.1738   0.01273   0.00570  -0.0217   0.9561   0.7336
  -2.000  -0.1418   0.01272   0.00560  -0.0222   0.9481   0.7625
  -1.750  -0.1102   0.01271   0.00553  -0.0226   0.9404   0.7875
  -1.500  -0.0786   0.01268   0.00547  -0.0229   0.9328   0.8127
  -1.250  -0.0488   0.01265   0.00538  -0.0229   0.9241   0.8358
  -1.000  -0.0148   0.01259   0.00528  -0.0237   0.9174   0.8547
  -0.750   0.0162   0.01254   0.00519  -0.0241   0.9080   0.8702
  -0.500   0.0504   0.01249   0.00510  -0.0252   0.9000   0.8844
  -0.250   0.0853   0.01244   0.00501  -0.0264   0.8917   0.8987
   0.000   0.1207   0.01241   0.00496  -0.0278   0.8822   0.9131
   0.250   0.1590   0.01236   0.00490  -0.0297   0.8735   0.9270
   0.500   0.1974   0.01232   0.00486  -0.0318   0.8640   0.9416
   0.750   0.2357   0.01230   0.00483  -0.0339   0.8536   0.9566
   1.000   0.2746   0.01223   0.00477  -0.0360   0.8407   0.9712
   1.250   0.3132   0.01213   0.00468  -0.0380   0.8237   0.9858
   1.500   0.3474   0.01206   0.00459  -0.0392   0.8055   1.0000
   1.750   0.3674   0.01209   0.00460  -0.0377   0.7879   1.0000
   2.000   0.3893   0.01215   0.00464  -0.0365   0.7721   1.0000
   2.250   0.4123   0.01222   0.00474  -0.0355   0.7564   1.0000
   2.500   0.4360   0.01229   0.00482  -0.0345   0.7397   1.0000
   2.750   0.4598   0.01237   0.00492  -0.0335   0.7209   1.0000
   3.000   0.4839   0.01246   0.00503  -0.0326   0.7000   1.0000
   3.250   0.5080   0.01255   0.00514  -0.0316   0.6759   1.0000
   3.500   0.5319   0.01266   0.00529  -0.0305   0.6467   1.0000
   3.750   0.5556   0.01280   0.00541  -0.0293   0.6106   1.0000
   4.000   0.5787   0.01301   0.00553  -0.0281   0.5638   1.0000
   4.250   0.6008   0.01335   0.00567  -0.0267   0.5018   1.0000
   4.500   0.6218   0.01388   0.00591  -0.0253   0.4297   1.0000
   4.750   0.6425   0.01455   0.00634  -0.0241   0.3593   1.0000
   5.000   0.6632   0.01531   0.00683  -0.0230   0.3006   1.0000
   5.250   0.6844   0.01607   0.00741  -0.0222   0.2536   1.0000
   5.500   0.7062   0.01682   0.00804  -0.0214   0.2086   1.0000
   5.750   0.7278   0.01761   0.00870  -0.0206   0.1632   1.0000
   6.000   0.7484   0.01856   0.00944  -0.0198   0.1216   1.0000
   6.250   0.7688   0.01961   0.01034  -0.0189   0.0929   1.0000
   6.500   0.7894   0.02066   0.01146  -0.0179   0.0718   1.0000
   6.750   0.8090   0.02187   0.01267  -0.0169   0.0571   1.0000
   7.000   0.8285   0.02312   0.01398  -0.0158   0.0450   1.0000
   7.250   0.8477   0.02447   0.01543  -0.0146   0.0353   1.0000
   7.500   0.8657   0.02600   0.01706  -0.0134   0.0285   1.0000
   7.750   0.8848   0.02727   0.01844  -0.0125   0.0229   1.0000
   8.000   0.9005   0.02950   0.02080  -0.0111   0.0205   1.0000
   8.250   0.9190   0.03169   0.02329  -0.0097   0.0189   1.0000
   8.500   0.9363   0.03422   0.02614  -0.0084   0.0177   1.0000
   8.750   0.9515   0.03701   0.02929  -0.0070   0.0169   1.0000
   9.000   0.9633   0.03995   0.03270  -0.0055   0.0161   1.0000
   9.250   0.9720   0.04269   0.03578  -0.0040   0.0153   1.0000
   9.500   0.9782   0.04500   0.03832  -0.0026   0.0143   1.0000
   9.750   0.9791   0.04786   0.04141  -0.0011   0.0136   1.0000
  10.250   0.9571   0.05509   0.04918   0.0031   0.0130   1.0000
  10.500   0.9430   0.05866   0.05302   0.0041   0.0129   1.0000
  10.750   0.9274   0.06285   0.05743   0.0038   0.0129   1.0000
  11.000   0.9109   0.06773   0.06249   0.0021   0.0130   1.0000
  11.250   0.8927   0.07356   0.06850  -0.0011   0.0130   1.0000
  11.500   0.7428   0.08574   0.08139  -0.0085   0.0172   1.0000
  11.750   0.7159   0.09681   0.09252  -0.0148   0.0179   1.0000
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