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THE AERODYNAMIC CHARACTERISTICS OF A 75-DEG SWEPT DELTA WING AT HIGH ANGLES OF ATTACK AND MACH NUMBERS OF 2 TO 8 (U)

Edward L. Clark, C. J. Spurlin

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Abstract

An experimental investigation was conducted in a 12 in. supersonic tunnel and a 50 in. Mach 8 tunnel to determine the aerodynamic characteristics of a delta wing at high angles of attack. The configuration tested was a flat, blunt leading edge, delta wing with 75 degree sweepback. The tests were conducted at angles of attack from 30 to 105 degree and Mach numbers of 2, 3, 5, and 8. Longitudinal stability and drag characteristics, surface pressure distributions, and shock wave shapes are presented with theoretical estimates based on the Newtonian theory.

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What this paper is about

An experimental investigation was conducted in a 12 in. supersonic tunnel and a 50 in. Mach 8 tunnel to determine the aerodynamic characteristics of a delta wing at high angles of attack. The configuration tested was a flat, blunt leading edge, delta wing with 75 degree sweepback. The tests were conducted at angles of attack from 30 to 105 degree and Mach numbers of 2, 3, 5, and 8. Longitudinal stability and drag characteristics, surface pressure distributions, and shock wave shapes are presented with theoretical estimates based on the Newtonian theory.

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Available abstract

An experimental investigation was conducted in a 12 in. supersonic tunnel and a 50 in. Mach 8 tunnel to determine the aerodynamic characteristics of a delta wing at high angles of attack. The configuration tested was a flat, blunt leading edge, delta wing with 75 degree sweepback. The tests were conducted at angles of attack from 30 to 105 degree and Mach numbers of 2, 3, 5, and 8. Longitudinal stability and drag characteristics, surface pressure distributions, and shock wave shapes are presented with theoretical estimates based on the Newtonian theory.

Key concepts: Mach number, Aerodynamics, Delta wing, Angle of attack, Wing, Aerospace engineering, Physics, Swept wing

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THE AERODYNAMIC CHARACTERISTICS OF A 75-DEG SWEPT DELTA WING AT HIGH ANGLES OF ATTACK AND MACH NUMBERS OF 2 TO 8 (U) — Research Paper | ScholarLens