Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls

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Description

An investigation of the aerodynamic characteristics of several hypersonic missile configurations with various canard controls for an angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about 0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by 4-foot supersonic pressure tunnel. The configurations tested were a body alone which had a ratio of length to diameter of 10, the body with a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and a flare-stabilized rocket model with a modified Von ... continued below

Creation Information

Robinson, R. B. March 10, 1958.

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This report is part of the collection entitled: National Advisory Committee for Aeronautics Collection and one other and was provided by UNT Libraries Government Documents Department to Digital Library, a digital repository hosted by the UNT Libraries. It has been viewed 110 times , with 4 in the last month . More information about this report can be viewed below.

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  • Main Title: Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls
  • Series Title: NACA Research Memorandums

Description

An investigation of the aerodynamic characteristics of several
hypersonic missile configurations with various canard controls for an
angle-of-attack range from 0 deg to about 28 deg at sideslip angles of about
0 deg and 4 deg at a Mach number of 2.01 has been made in the Langley 4- by
4-foot supersonic pressure tunnel.

The configurations tested were a

body alone which had a ratio of length to diameter of 10, the body with
a 10 deg flare, the body with cruciform fins of 5 deg or 15 deg apex angle, and
a flare-stabilized rocket model with a modified Von Karman nose.

Various canard surfaces for pitch control only were tested on the body with the
10 deg flare and on the body with both sets of fins.
The results indicated that the addition of a flared afterbody or
cruciform fins produced configurations which were longitudinally and
directionally stable. The body with 5 deg fins should be capable of producing higher normal accelerations than the flared body. A l l of the
canard surfaces were effective longitudinal controls which produced
net positive increments of normal force and pitching moments which
progressively decreased with increasing angle of attack.

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  • : 65N24057
  • URL: http://hdl.handle.net/2060/19650014456 External Link
  • Report No.: NACA-RM-L58A21
  • Center for AeroSpace Information Number: 19650014456
  • Archival Resource Key: ark:/67531/metadc52987

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National Advisory Committee for Aeronautics Collection

The National Advisory Committee for Aeronautics (NACA) was a U.S. federal agency founded on March 3, 1915 to undertake, promote, and institutionalize aeronautical research. On October 1, 1958 the agency was dissolved, and its assets and personnel transferred to the newly created National Aeronautics and Space Administration (NASA).

Technical Report Archive and Image Library

This selection of materials from the Technical Report Archive and Image Library (TRAIL) includes hard-to-find reports published by various government agencies. The technical publications contain reports, images, and technical descriptions of research performed for U.S. government agencies. Topics range from mining, desalination, and radiation to broader physics, biology, and chemistry studies. Some reports include maps, foldouts, blueprints, and other oversize materials.

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Creation Date

  • March 10, 1958

Added to The UNT Digital Library

  • Nov. 11, 2011, 7:22 p.m.

Description Last Updated

  • Jan. 27, 2017, 1:50 p.m.

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Robinson, R. B. Wind-Tunnel Investigation at a Mach Number of 2.01 of the Aerodynamic Characteristics in Combined Angles of Attack and Sideslip of Several Hypersonic Missile Configurations with Various Canard Controls, report, March 10, 1958; (digital.library.unt.edu/ark:/67531/metadc52987/: accessed November 18, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.