Wall Temperature and Bluntness Effects in High Enthalpy Hypersonic Separated Flows
Abstract
Strong wall temperature effects in large scale hypersonic flows have generated considerable interest in recent years in the context of hypersonic SWBLI. These effects become significant because in most of high enthalpy ground based facilities such as shock tunnels the test duration is only of the order of a few milliseconds so that the model remains ‘cold’. In many cases, in order to simulate realistic temperatures such as those encountered in flight, the model surface has to be heated. Another issue to be considered in conjunction with wall temperature is the leading edge bluntness effect. It is now well known that bluntness of the leading edge profoundly influences both separation and the SWBLI. However, not much is known when both wall temperature and bluntness effects are present simultaneously. Herein, we have proposed a comprehensive program consisting of experiments as well as numerical simulations and theoretical analysis to investigate small to large separated flows at wall to stagnation temperature ratios varying from 0.095 to 0.317 by heating the model. The experiments will be conducted in a free piston shock tunnel at a specific enthalpy of 3.1 MJ-kg; stagnation temperature of 3150 K; Mach number of 10; and unit Reynolds number of 1.34 million per metre based on freestream conditions. The experimental models will involve some unique design features including the use of graphite surface for heating. We will conduct both two dimensional and axisymmetric tests. For two dimensional tests, we will use the compression ramp geometry and for axisymmetric tests, a cylinder flare. The ramp and flare angles will vary from 10° to 30°. Numerical simulations will be carried out using the compressible Navier Stokes code US3D developed by Professor Graham Candler and his associates at the University of Minnesota. The code can handle both perfect and real gases and is well adapted for hypersonic problems.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jan 14, 2022
- Source ID
- FA23861914023XX0
Entities
People
- S. L. Gai
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of New South Wales