Scramjet Systems Integration for a Dual Mode Scramjet Flight Test

The Hy-V project will conduct the first-ever mode-transition flight-test for a dual-mode hypersonic scramjet, which will occur at approximately 90,000 feet onboard a sounding rocket. At altitude, atmospheric conditions and inlet flow speed will match the flow conditions simulated in the UVA Aerospace Research Laboratory (ARL) hypersonic wind tunnel. Geometric similarity between the wind tunnel and flight-test flow path presents a unique opportunity to calibrate the two environments. This, however, requires a close agreement between the flight and ARL wind tunnel flow conditions, fuel injection systems, combustion environment, and exhaust pressure. This research presents strategies for transitioning the ARL hypersonic wind tunnel into the payload of a sounding rocket in a matter that optimizes the desired geometric similarity. Space constraints in the scramjet’s flight-test configuration require an innovative approach to managing fuel storage, fuel mass flow rate, data acquisition, and exhaust. In addition, this research considers factors such as budgetary constraints and thermal management to optimize the implementation of pressure and temperature recording devices implanted in the flow path wall.