As hypersonic propulsion technology moves from the laboratory to flight demonstrators and on to operational systems, improved overall engine performance and operability become more critical. Numerous factors challenge engine designers, however, the inlet/isolator compression system that couples to the hypersonic ramjet/scramjet combustor is one of the most vexing. Packaging, acceleration, range, maneuverability, survivability, are all first order design drivers. These flow down to requirements for the inlet/isolator to achieve high engine back pressure, deliver minimum flow distortion at the engine aerodynamic inlet plane, and avoid unstart over an accelerating and maneuvering flight profile. To achieve these objectives, Innoveering has identified a fluidic system for inlet/isolator integration that can deliver the needed improvements. The proposed Phase I activity will mature this concept using combined CFD and optimization and prepare for experimental assessment, optimization, and verification in Phase II.
Benefit: Hypersonic engine designs require improve performance and operability to achieve envisioned missions. As the DoD writes requirements for future procurements, the requirements will exceed the capabilities of the demonstration vehicles that are being flight tested currently. The Innoveering fluidic control approach for inlet/isolators will improve overall isolator performance and operability and deliver the necessary combustor entrance conditions needed for hypersonic engines to achieve the required acceleration, range, and maneuverability. Working with the System Integrators, Innoveering will package our system to inlet isolator to be compatible with existing systems and consistent with overall vehicle design intent.
Keywords: scramjet operability improvement, scramjet operability improvement, Inlet Isolator aerodynamic design, Fluidic Isolator Control, Scramjet Isolator Control
