Numerical Investigation of Second-Order Effects in a Supersonic Boundary-Layer

<p>Historically, the study of boundary-layer flows has centered on the analysis of the first-order boundary-layer equations and their application to physical flow problems. However, selected “real-world” boundary-layer flows exhibit significant second-order effects which are neglected by the first-order equations. Full Navier-Stokes solutions are often not merited or desired for these flows. Therefore, the second-order boundary-layer equations provide a compromise.</p> <p>Few validating comparisons have been attempted between second-order boundary-layer theory and experimental or numerical solutions of compressible viscous flows. Experimental simulations to capture second-order effects are difficult since the desired effects are small and can exist simultaneously, resulting in a neutralizing effect.</p> <p>This report documents the application of Computational Fluid Dynamics (CFD) to the solution of second-order boundary-layer effects. Development of an optimum computational grid is the primary problem encountered. The effort involves significant analysis of the influence of various grid designs on the computational resolution. The numerical experimentation is performed for the supersonic flow over a flat plate at zero angle of attack. The second-order effects are initiated by the introduction of a stagnation enthalpy gradient in the flowfield at the plate leading edge.</p>

Name thesis:degree_name

Master of Aerospace Engineering

Level thesis:degree_level

Thesis - Open Access

Discipline thesis:degree_discipline

Graduate Studies

Year

1995

Author dc:creator

• Membrino, Timothy R.

Contributors dc:contributor

• Jose Rodriguez
• George Emanuel
• Tej Gupta

• boundary-layer flows
• supersonic
• Computational Fluid Dynamics
• Aerospace Engineering

Repository record dc:identifier

https://commons.erau.edu/db-theses/256

OAI identifier oai:identifier

oai:commons.erau.edu:db-theses-1197