Supersonic External-Compression Inlets for Mach 1.4 to 2.0

John W Slater

NASA NTRS · 20230006132

Supersonic External-Compression Inlets for Mach 1.4 to 2.0

Abstract

A series of supersonic, external-compression inlets were designed for freestream Mach numbers of Mach 1.4, 1.7, and 2.0. The types of inlets included axisymmetric pitot, axisymmetric spike, two-dimensional, two-dimensional bifurcated, and streamline-traced inlets. The inlets were designed as isolated from an aircraft with freestream conditions, engine-face geometry, and flow rates established from a reference NASA commercial aircraft concept. The inlets were designed using the NASA Supersonic Inlet Design and Analysis (SUPIN) Tool and the inlet performance was obtained from computational fluid dynamics (CFD) simulations. The study compares the physical dimensions and aerodynamic performance of the inlets to provide reference information for the selection of inlet types for commercial supersonic aircraft.

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Supersonics Propulsion Computational Fluid Dynamics

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John W Slater. Supersonic External-Compression Inlets for Mach 1.4 to 2.0. https://ntrs.nasa.gov/citations/20230006132

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