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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 ControlsAn 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 we re a body alone which had a ratio of length to diameter of 10, the b ody 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 te sted 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.
Document ID
19650014456
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Robinson, R. B.
(National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
September 2, 2013
Publication Date
March 10, 1958
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-L58A21
Accession Number
65N24057
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AERODYNAMIC CHARACTERISTICS
MISSILE CONTROL
MISSILE CONFIGURATION
CANARD
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