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HQ 0/7 AIRFOIL (hq07-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: HQ 0/7 AIRFOIL (hq07-il)
Reynolds number: 50,000
Max Cl/Cd: 24.71 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-hq07-il-50000-n5.txt
Download as CSV file: xf-hq07-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: HQ 0/7 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.6623   0.09326   0.08662   0.0038   1.0000   0.0358
  -8.750  -0.6675   0.08692   0.08034  -0.0013   1.0000   0.0348
  -8.500  -0.6795   0.08031   0.07375  -0.0070   1.0000   0.0335
  -8.000  -0.6946   0.07056   0.06359  -0.0120   1.0000   0.0316
  -7.750  -0.6947   0.06591   0.05876  -0.0129   1.0000   0.0315
  -7.500  -0.6922   0.06128   0.05390  -0.0134   1.0000   0.0314
  -7.250  -0.6869   0.05672   0.04903  -0.0136   1.0000   0.0313
  -7.000  -0.6786   0.05225   0.04416  -0.0135   1.0000   0.0313
  -6.750  -0.6670   0.04801   0.03943  -0.0131   1.0000   0.0315
  -6.500  -0.6529   0.04377   0.03470  -0.0125   1.0000   0.0320
  -6.250  -0.6372   0.03960   0.03018  -0.0120   1.0000   0.0335
  -6.000  -0.6178   0.03653   0.02678  -0.0113   1.0000   0.0368
  -5.750  -0.5968   0.03384   0.02349  -0.0105   1.0000   0.0459
  -5.500  -0.5730   0.03091   0.02027  -0.0096   1.0000   0.0507
  -5.250  -0.5464   0.02831   0.01720  -0.0084   1.0000   0.0554
  -5.000  -0.5217   0.02617   0.01494  -0.0073   1.0000   0.0615
  -4.750  -0.4982   0.02471   0.01335  -0.0065   1.0000   0.0771
  -4.500  -0.4749   0.02309   0.01159  -0.0053   1.0000   0.0883
  -4.250  -0.4523   0.02153   0.00994  -0.0043   1.0000   0.1078
  -4.000  -0.4320   0.01955   0.00840  -0.0038   1.0000   0.1840
  -3.750  -0.4202   0.01725   0.00758  -0.0016   1.0000   0.4284
  -3.500  -0.4081   0.01651   0.00774   0.0033   1.0000   0.6441
  -3.250  -0.3928   0.01646   0.00785   0.0082   1.0000   0.7557
  -3.000  -0.3708   0.01656   0.00789   0.0121   1.0000   0.8313
  -2.750  -0.3383   0.01649   0.00752   0.0125   1.0000   0.8688
  -2.500  -0.3008   0.01635   0.00707   0.0112   1.0000   0.8960
  -2.250  -0.2524   0.01629   0.00668   0.0079   1.0000   0.9291
  -2.000  -0.1902   0.01615   0.00603   0.0014   1.0000   0.9573
  -1.750  -0.1424   0.01585   0.00550  -0.0031   1.0000   0.9747
  -1.500  -0.0986   0.01552   0.00501  -0.0071   1.0000   0.9906
  -1.250  -0.0671   0.01524   0.00463  -0.0089   1.0000   1.0000
  -1.000  -0.0518   0.01502   0.00440  -0.0076   1.0000   1.0000
  -0.750  -0.0374   0.01484   0.00419  -0.0060   1.0000   1.0000
  -0.500  -0.0240   0.01471   0.00405  -0.0042   1.0000   1.0000
  -0.250  -0.0116   0.01463   0.00397  -0.0022   1.0000   1.0000
   0.000   0.0000   0.01460   0.00394   0.0000   1.0000   1.0000
   0.250   0.0116   0.01463   0.00396   0.0022   1.0000   1.0000
   0.500   0.0240   0.01471   0.00405   0.0042   1.0000   1.0000
   0.750   0.0375   0.01484   0.00418   0.0060   1.0000   1.0000
   1.000   0.0519   0.01502   0.00439   0.0076   1.0000   1.0000
   1.250   0.0673   0.01523   0.00463   0.0089   1.0000   1.0000
   1.500   0.0987   0.01552   0.00500   0.0071   0.9907   1.0000
   1.750   0.1424   0.01584   0.00549   0.0031   0.9747   1.0000
   2.000   0.1903   0.01614   0.00602  -0.0014   0.9574   1.0000
   2.250   0.2525   0.01629   0.00667  -0.0079   0.9291   1.0000
   2.500   0.3009   0.01635   0.00706  -0.0112   0.8961   1.0000
   2.750   0.3383   0.01648   0.00752  -0.0125   0.8688   1.0000
   3.000   0.3707   0.01655   0.00789  -0.0121   0.8313   1.0000
   3.250   0.3927   0.01645   0.00785  -0.0082   0.7558   1.0000
   3.500   0.4079   0.01651   0.00774  -0.0033   0.6432   1.0000
   3.750   0.4201   0.01725   0.00757   0.0016   0.4287   1.0000
   4.000   0.4320   0.01956   0.00840   0.0038   0.1838   1.0000
   4.250   0.4524   0.02153   0.00994   0.0043   0.1078   1.0000
   4.500   0.4750   0.02309   0.01159   0.0053   0.0881   1.0000
   4.750   0.4984   0.02472   0.01336   0.0065   0.0769   1.0000
   5.000   0.5219   0.02617   0.01494   0.0073   0.0615   1.0000
   5.250   0.5466   0.02832   0.01720   0.0084   0.0554   1.0000
   5.500   0.5733   0.03092   0.02028   0.0096   0.0507   1.0000
   5.750   0.5970   0.03386   0.02350   0.0105   0.0457   1.0000
   6.000   0.6182   0.03653   0.02678   0.0112   0.0366   1.0000
   6.250   0.6376   0.03965   0.03023   0.0119   0.0334   1.0000
   6.500   0.6535   0.04377   0.03471   0.0124   0.0321   1.0000
   6.750   0.6676   0.04806   0.03948   0.0130   0.0315   1.0000
   7.000   0.6791   0.05236   0.04428   0.0134   0.0313   1.0000
   7.250   0.6876   0.05679   0.04911   0.0134   0.0313   1.0000
   7.500   0.6927   0.06142   0.05405   0.0132   0.0313   1.0000
   7.750   0.6956   0.06597   0.05883   0.0127   0.0315   1.0000
   8.000   0.6959   0.07061   0.06363   0.0118   0.0317   1.0000
   8.500   0.6805   0.08045   0.07390   0.0068   0.0335   1.0000
   8.750   0.6685   0.08706   0.08048   0.0011   0.0347   1.0000
   9.000   0.6634   0.09340   0.08676  -0.0041   0.0358   1.0000
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