Item Details

Dynamic Stability Derivatives of a Twin-Jet Fighter Model for Angles of Attack From -10 ̊to 110

Sue B. Grafton and Charles E. Libbey
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, Springfield, Virginia 22151], 1971.
Language
English
Variant Title
NASA TN D-6091
Series
NASA Technical Note
Summary
A low-speed investigation was conducted to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -10 [degree] to 110 [degree] for a twin-jet swept-wing fighter model. Several frequencies and amplitudes were investigated to determine the effects of these variables on the stability derivatives. The effect of the vertical and horizontal tail, and horizontal-tail incidence on the derivatives was also evaluated. The results indicate that the model exhibited stable values of damping in pitch over the entire angle-of-attack range, but marked reductions of damping in roll were measured at the stall, and unstable values of damping in yaw were present for the very high angles of attack associated with flat spins. Either removal of the horizontal or vertical tail or full up deflection of the horizontal tail eliminated the unstable characteristics of the damping-in-yaw derivatives.
Description
36 p. : ill. ; 27 cm.
Mode of access: Internet.
Notes
Includes bibliographical references (p. 12).
Series Statement
NASA technical note ; D-6091
Logo for Copyright Not EvaluatedCopyright Not Evaluated
Technical Details

  • LEADER 02609cam a2200433Ma 4500
    001 011443552
    003 MiAaHDL
    005 20141009010000.0
    006 m d
    007 cr bn ---auaua
    008 041209s1971 dcua b f000 0 eng d
    035
      
      
    a| sdr-uiuc6402044
    035
      
      
    a| (OCoLC)647696932
    040
      
      
    a| EGM c| STF
    049
      
      
    a| UIUU
    100
    1
      
    a| Grafton, Sue B.
    245
    1
    0
    a| Dynamic stability derivatives of a twin-jet fighter model for angles of attack from -10 ̊to 110 c| Sue B. Grafton and Charles E. Libbey.
    246
    3
      
    a| NASA TN D-6091
    260
      
      
    a| Washington, D.C. : b| National Aeronautics and Space Administration ; a| [For sale by the Clearinghouse for Federal Scientific and Technical, Springfield, Virginia 22151], c| 1971.
    300
      
      
    a| 36 p. : b| ill. ; c| 27 cm.
    490
    0
      
    a| NASA technical note ; v| D-6091
    504
      
      
    a| Includes bibliographical references (p. 12).
    520
      
      
    a| A low-speed investigation was conducted to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -10 [degree] to 110 [degree] for a twin-jet swept-wing fighter model. Several frequencies and amplitudes were investigated to determine the effects of these variables on the stability derivatives. The effect of the vertical and horizontal tail, and horizontal-tail incidence on the derivatives was also evaluated. The results indicate that the model exhibited stable values of damping in pitch over the entire angle-of-attack range, but marked reductions of damping in roll were measured at the stall, and unstable values of damping in yaw were present for the very high angles of attack associated with flat spins. Either removal of the horizontal or vertical tail or full up deflection of the horizontal tail eliminated the unstable characteristics of the damping-in-yaw derivatives.
    538
      
      
    a| Mode of access: Internet.
    650
      
    0
    a| Fighter planes x| Aerodynamics.
    650
      
    0
    a| Spin (Aerodynamics)
    650
      
    0
    a| Angle of attack (Aerodynamics)
    650
      
    0
    a| Airplanes x| Wings, Swept-back x| Aerodynamics.
    700
    1
      
    a| Libbey, Charles E.
    710
    2
      
    a| Langley Research Center.
    710
    1
      
    a| United States. b| National Aeronautics and Space Administration.
    974
      
      
    b| UIU c| UIUC d| 20141113 s| google u| uiug.30112106880534 y| 1971 r| pd q| bib

Access online

Google Preview