Numerical Investigation of Supersonic Flow over a Wedge by Solving 2D Euler Equations Utilizing the Steger–Warming Flux Vector Splitting (FVS) Scheme-Reference-Cited by-同舟云学术

Numerical Investigation of Supersonic Flow over a Wedge by Solving 2D Euler Equations Utilizing the Steger–Warming Flux Vector Splitting (FVS) Scheme

Published:2024-04-24 Issue:9 Volume:12 Page:1282
ISSN:2227-7390
Container-title:Mathematics
language:en
Short-container-title:Mathematics

Author:

Wolff Mitch¹,Abada Hashim H.²^ORCID,Saad Hussein Awad Kurdi³

Affiliation:

1. Mechanical & Materials Engineering Department, Wright State University, Dayton, OH 45435-0001, USA

2. Mechanical Engineering Department, Al-Kufa Technical Institute, Al-Furat Al-Awsat Technical University (ATU), Kufa 54003, Iraq

3. Power/Mechanical Engineering Department, Engineering Technical College of Al-Najaf, Al-Furat Al-Awsat Technical University (ATU), Al-Najaf 54001, Iraq

Abstract

Supersonic flow over a half-angle wedge (θ = 15°) with an upstream Mach number of 2.0 was investigated using 2D Euler equations where sea level conditions were considered. The investigation employed the Steger–Warming flux vector splitting (FVS) method executed in MATLAB 9.13.0 (R2022b) software. The study involved a meticulous comparison between theoretical calculations and numerical results. Particularly, the research emphasized the angle of oblique shock and downstream flow properties. A substantial iteration count of 2000 iteratively refined the outcomes, underscoring the role of advanced computational resources. Validation and comparative assessment were conducted to elucidate the superiority of the Steger–Warming flux vector splitting (FVS) scheme over existing methodologies. This research serves as a link between theoretical rigor and practical applications in high-speed aerospace design, enhancing the efficiency of aircraft components.

Publisher

MDPI AG

Link

https://www.mdpi.com/2227-7390/12/9/1282/pdf

Reference20 articles.

1. Abada, H.H. (2017). Turboelectric Distributed Propulsion System for NASA Next Turboelectric Distributed Propulsion System for NASA Next Generation Aircraft Generation Aircraft. [Master’s Thesis, Wright State University]. Available online: https://corescholar.libraries.wright.edu/etd_all.

2. Newman, P.A., and Allison, D.O. (2023, May 09). An Annotated Bibliography on Transonic Flow Theory, Available online: https://ntrs.nasa.gov/api/citations.

3. Structure of an oblique detonation wave induced by a wedge;Liu;Shock. Waves,2015

4. Numerical experiments using high-resolution schemes for unsteady, inviscid, compressible flows;Bagabir;Comput. Methods Appl. Mech. Eng.,2004

5. Özgün, M. (2016). Analysis of Hypersonic Flow Using Three Dimensional Navier-Stokes Equations. [Master’s Thesis, Graduate School of Natural and Applied Sciences of Middle East Technical University].