A Numerical Solution of a Nonisothermal Wall Using the Two-Dimensional Navier-Stokes Equations.
Abstract
Wind tunnel tests of Space Shuttle Orbiter insulating articles have demonstrated the presence of a nonisothermal wall effect, which is a lag in heat transfer recovery after the flow passes over a surface temperature discontinuity resulting in a downstream transport of energy, Theoretical analyses and numerical simulations of hypersonic flow over discontinuous nonisothermal surfaces using boundary layer theory have also indicated the presence of this effect. This thesis studies the nonisothermal wall effect by modelling the hypersonic flow over an inclined wedge with a discontinuous nonisothermal surface. The flow is modeled using the two-dimensional Navier-Stokes equations. MacCormack's method is used to solve the Navier-Stokes equations. The computer program used to implement these methodologies is discussed and a listing is given. A semi-adaptive grid is used to represent the physical conditions of the problem, Heat transfer is presented as a nondimensional ratio of the local convective heat transfer coefficient to a reference heat transfer coefficient. Additional keywords: Shock wave boundary layer insulation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1985
- Accession Number
- ADA154467
Entities
People
- T. K. Roberts
Organizations
- Air Force Institute of Technology