Novel Fluidic Flow Control of Scramjet Isolators

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 II activity will further mature this concept using combined CFD and optimization and prepare for experimental assessment, optimization, and verification.