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An Experimental Investigation at Low Speeds of the Effects of Lip Shape on the Drag and Pressure Recovery of a Nose Inlet in a Body of Revolution

James R Blackaby, E. C. Watson

Open publisher page 3 citations

Abstract

Report presenting wind-tunnel tests of a body of revolution with a circular nose inlet conducted at low speeds to ascertain some of the effects of inlet lip bluntness and profile on diffuser performance and body drag. Testing occurred at free-stream Mach numbers up to 0.330 with inlet flows from zero to choking and a steady 0 degree angle of attack and angle of yaw. Results regarding the internal-flow studies with the strut-mounted model and drag and surface-pressure studies with the sting-supported model are provided.

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What this paper is about

Report presenting wind-tunnel tests of a body of revolution with a circular nose inlet conducted at low speeds to ascertain some of the effects of inlet lip bluntness and profile on diffuser performance and body drag. Testing occurred at free-stream Mach numbers up to 0.330 with inlet flows from zero to choking and a steady 0 degree angle of attack and angle of yaw. Results regarding the internal-flow studies with the strut-mounted model and drag and surface-pressure studies with the sting-supported model are provided.

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Available abstract

Report presenting wind-tunnel tests of a body of revolution with a circular nose inlet conducted at low speeds to ascertain some of the effects of inlet lip bluntness and profile on diffuser performance and body drag. Testing occurred at free-stream Mach numbers up to 0.330 with inlet flows from zero to choking and a steady 0 degree angle of attack and angle of yaw. Results regarding the internal-flow studies with the strut-mounted model and drag and surface-pressure studies with the sting-supported model are provided.

Key concepts: Drag, Inlet, Mechanics, Wave drag, Wind tunnel, Angle of attack, Aerodynamic drag, Mach number

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