Work

Nozzle Flow Characterization of the SNU Hypersonic Shock Tunnel

Year: 2024

Type: article

Abstract: This paper presents the operational capabilities and the characteristics of the nozzle flow of the Seoul National University Hypersonic Shock Tunnel (SHyST), a recently added impulse facility designed to produce high-enthalpy flows reaching up to 5 MJ/kg through hypersonic contoured nozzles. Within this investigation, emphasis is placed on the design and utilization of a pitot rake, serving as an essential instrument for quantifying pitot pressure and Mach number distributions throughout the test section. The experimental results confirm the presence of axis-symmetric behavior and spatial–temporal uniformity of the freestream Mach number at the nozzle outlet and along the test section. In addition, the study demonstrates a good agreement with the predictions of numerical simulation. Mach number validation is further supported by the measurement of shock standoff distance through schlieren visualization.

Source: International Journal of Aeronautical and Space Sciences

DOI: 10.1007/s42405-024-00806-5

Authors: Jinyoung Kim, Jinhwi Kim, Jungmu Hur, Bok Jik Lee, In-Seuck Jeung

Institution: Seoul National University

Language: English

Topic: Computational Fluid Dynamics and Aerodynamics

Subfield: Computational Mechanics

Field: Engineering

Domain: Physical Sciences

Open Access status: hybrid

Estimated APC paid: $3,290

Funders: Seoul National University, Agency for Defense Development, Defense Acquisition Program Administration