Hypersonic Intake Testing with Varying Wall Temperature
Abstract
This project contributes directly to the AFRL Hypersonics Game Changing Technology area by investigating the effect of wall temperature on scramjet starting, efficiency, and mass capture for three-dimensional C-REST intakes. The wall to total temperature ratio has an important influence on the thickness of the boundary layer and therefore the performance and starting limits of the intake. Testing in shock tunnels performed to date has too short a test time to evaluate these aspects. The testing will be performed in the newly re-established High Density Tunnel (HDT) at Oxford University, which can replicate a wide range of Mach numbers, Reynolds numbers and wall-to-total temperature ratios which cover the proposed trajectory space for the intake. The initial intake to be tested will be designed and manufactured at University of Queensland, then instrumented and tested at Oxford during a sabbatical visit by Prof Michael Smart for self-starting characteristics at varying wall to total temperature and pressure ratios.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Apr 09, 2018
- Source ID
- FA95501810022
Entities
People
- Matthew Mcgilvray
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Oxford