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Aerodynamic Characteristics of a Spoiler-Slot-Deflector Control on a 45 deg Sweptback-Wing-Fuselage Model at High Subsonic Speeds

Alexander D Hammond

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Abstract

An investigation was made in the Langley high-speed 7-by 10-foot tunnel for a Mach number range from 0.60 to 0.95 to determine the lateral-iSupersedes NASA Technical Memorandum X-205 by Alexander D. Hammond, 1%o.

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An investigation was made in the Langley high-speed 7-by 10-foot tunnel for a Mach number range from 0.60 to 0.95 to determine the lateral-iSupersedes NASA Technical Memorandum X-205 by Alexander D. Hammond, 1%o.

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Available abstract

An investigation was made in the Langley high-speed 7-by 10-foot tunnel for a Mach number range from 0.60 to 0.95 to determine the lateral-iSupersedes NASA Technical Memorandum X-205 by Alexander D. Hammond, 1%o.

Key concepts: Fuselage, Wing, Aerodynamics, Aerospace engineering, Wing configuration, Flight control surfaces, Angle of attack, Aeronautics

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Aerodynamic Characteristics of a Spoiler-Slot-Deflector Control on a 45 deg Sweptback-Wing-Fuselage Model at High Subsonic Speeds — Research Paper | ScholarLens