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Experimental Investigation of the Flow Structure over a Delta Wing Via Flow Visualization Methods
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Numerical simulation of supersonic gap flow.

Xu Jing1, Huang Haiming1, Huang Guo1

  • 1Institute of Engineering Mechanics, Beijing Jiaotong University, Beijing, 100044, China.

Plos One
|January 31, 2015
PubMed
Summary
This summary is machine-generated.

Surface gaps on supersonic aircraft impact airflow and heating. Chamfering gap corners can reduce aerodynamic heating effects, aiding thermal protection system design for reentry vehicles.

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Area of Science:

  • Aerospace Engineering
  • Computational Fluid Dynamics
  • Heat Transfer

Background:

  • Surface discontinuities on supersonic aircraft significantly alter airflow patterns.
  • Understanding aerodynamic heating in these gaps is crucial for vehicle design and safety.

Purpose of the Study:

  • To predict the aerodynamic heating environment in supersonic flow gaps.
  • To analyze the influence of attack angle, Mach number, and gap geometry on heat flux.
  • To evaluate mitigation strategies for gap effects.

Main Methods:

  • Solving two-dimensional compressible Navier-Stokes equations using the finite volume method.
  • Employing the Roe format for convective flux and a 5-step Runge-Kutta algorithm for time discretization.
  • Investigating the impact of geometric modifications like windward corner chamfering.

Main Results:

  • Heat flux exhibits a U-shaped distribution along the gap wall, peaking at the windward corner.
  • Increased gap depth and Mach number reduce heat flux ratio.
  • Elevated attack angles lead to a higher heat flux ratio.
  • Chamfering the windward corner effectively minimizes the gap effect coefficient.

Conclusions:

  • Gap geometry and flow conditions critically influence aerodynamic heating.
  • Chamfering offers a viable method to mitigate adverse heating effects in surface gaps.
  • Findings support the design of robust thermal protection systems for supersonic vehicles and reentry applications.