Item Details

Application of a One-Strip Integral Method to the Unsteady Supersonic Aerodynamics of an Inclined Flat Surface

Robert M. Bennett
Format
Book; Government Document; Online; EBook
Published
Washington, D.C. : National Aeronautics and Space Administration : [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1972.
Language
English
Variant Title
NASA TN D-6644
Application of a 1-strip integral method to the unsteady supersonic aerodynamics of an inclined flat surface
Series
NASA Technical Note
SuDoc Number
NAS 1.14:D-6644
Summary
The method of integral relations is applied in a one-strip approximation to the perturbation equations governing small motions of an inclined, sharp-edged, flat surface about the mean supersonic steady flow. Algebraic expressions for low reduced-frequency aerodynamics are obtained and a set of ordinary differential equations are obtained for general oscillatory motion. Results are presented for low reduced-frequency aerodynamics and for the variation of the unsteady forces with frequency. The method gives accurate results for the aerodynamic forces at low reduced frequency which are in good agreement with available experimental data. However, for cases in which the aerodynamic forces vary rapidly with frequency, the results are qualitatively correct, but of limited accuracy. Calculations indicate that for a range of inclination angles near shock detachment such that the flow in the shock layer is low supersonic, the aerodynamic forces vary rapidly both with inclination angle and with reduced frequency.
Description
55 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
Includes bibliographical references (p. 37-40).
Series Statement
NASA technical note ; D-6644
Logo for No Copyright - United StatesNo Copyright - United States
Technical Details

  • LEADER 02816cam a2200445Ma 4500
    001 011445012
    003 MiAaHDL
    005 20141009010000.0
    006 m d
    007 cr bn ---auaua
    008 030904s1972 dcua b f000 0 eng d
    035
      
      
    a| sdr-uiuc6403850
    035
      
      
    a| (OCoLC)643056061
    040
      
      
    a| EGM c| STF
    049
      
      
    a| UIUU
    086
    0
      
    a| NAS 1.14:D-6644
    088
      
      
    a| NASA-TN-D-6644
    100
    1
      
    a| Bennett, Robert M.
    245
    1
    0
    a| Application of a one-strip integral method to the unsteady supersonic aerodynamics of an inclined flat surface / c| Robert M. Bennett.
    246
    3
      
    a| NASA TN D-6644
    246
    3
      
    a| Application of a 1-strip integral method to the unsteady supersonic aerodynamics of an inclined flat surface
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration : b| [For sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151], c| 1972.
    300
      
      
    a| 55 p. : b| ill. ; c| 27 cm.
    490
    0
      
    a| NASA technical note ; v| D-6644
    504
      
      
    a| Includes bibliographical references (p. 37-40).
    520
      
      
    a| The method of integral relations is applied in a one-strip approximation to the perturbation equations governing small motions of an inclined, sharp-edged, flat surface about the mean supersonic steady flow. Algebraic expressions for low reduced-frequency aerodynamics are obtained and a set of ordinary differential equations are obtained for general oscillatory motion. Results are presented for low reduced-frequency aerodynamics and for the variation of the unsteady forces with frequency. The method gives accurate results for the aerodynamic forces at low reduced frequency which are in good agreement with available experimental data. However, for cases in which the aerodynamic forces vary rapidly with frequency, the results are qualitatively correct, but of limited accuracy. Calculations indicate that for a range of inclination angles near shock detachment such that the flow in the shock layer is low supersonic, the aerodynamic forces vary rapidly both with inclination angle and with reduced frequency.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Space shuttles x| Landing.
    650
      
    0
    a| Aerodynamics, Supersonic.
    650
      
    0
    a| Unsteady flow (Aerodynamics)
    710
    2
      
    a| Langley Research Center.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    974
      
      
    b| UIU c| UIUC d| 20200405 s| google u| uiug.30112106882845 y| 1972 r| pd q| bib t| US fed doc

Access online

Google Preview