The proposed effort will perform a complementary experimental and computational investigation of the scramjet inlet performance at sub-design Mach numbers.

The goal of the proposed effort is to develop and evaluate rapid morphing concepts for hypersonic waveriders. Two applications are proposed: 1) inlet duct morphing to improve the off-cruise efficiency and achieve adaptive thrust demanded at various trajectory points, and 2) rapid control surface (can be waverider body/underbelly) morphing to optimize the control output with lowest vehicle drag. The proposed effort is primarily experimental with a basic modeling element to extract the flow physics and integral forces. The base period of performance is three years with two subsequent option years.

The objective of the effort is to develop and evaluate an array of flow distortion devices that will be integrated into ADAC facility at AFRL, Dayton.

The vision of the proposed research is to remotely alter the flight trajectory of high-speed projectiles as a possible defense strategy against munition strikes that minimizes collateral damage. To this end, we propose to investigate manipulating the non-linear shock/boundary layer interactions (SBLI) around the munition control fins with the aim of creating amplified perturbation forces and moments. Such manipulation can be achieved by introducing steady and unsteady distortions into the missile boundary layer that interacts with the control-fin shock by several interception strategies described earlier. In this effort, we consider generic boundary layer distortions of various magnitudes, study the resulting SBLI responses, and map the sensitive perturbation regions using state-of-the-art experimental and computational tools. To maintain relevance to the Navy's goals and capabilities, the boundary layer distortions will be created either using small sized dents on the model surface or by embedding an unsteady wake field.

NCSU will support testing of RDC by making detailed flow field measurements. NCSU will provide consulting services to GE Research to ensure that appropriate designs are implemented in the RDC-compressor rig hardware to enable optical access that is suitable for optical measurement systems for 2D total temperature and total pressure imaging measurements at the exit of combustor. NCSU will support up to two measurement campaigns at the GE Research test facility and will supply the necessary equipment and personnel to make 2D total temperature and total pressure imaging measurements

The objective of the proposed effort is to study the use of fluid structure interactions with compliant materials to obtain positive outcomes in supersonic flows.

There are two basic questions for FSTI at any Mach number including hypersonic Mach numbers. First, what is the impact of a flexible structure on the flowfield, and second what is the impact of the flowfield on the structure? If there is truly an interaction, i.e., FSTI, then the flow field creates motion in the structure and the structural motion creates changes in the flow field. Both always occur to some degree, so the question is when are such interactions significant? The vision of the proposed effort is to advance the current state of Fluid Structural Thermal Interactions (FSTI) that occur in hypersonic aerospace vehicles by finding comprehensive answers to the above questions. The objective of the proposed effort is to develop fundamental insights into the FSTI phenomena that occur when a shock wave is present on a structure with or without accompanying boundary layer separation at hypersonic Mach numbers.

To upgrade the current NCSU Mach 6 wind tunnel to obtain longer run time higher Reynolds numbers and temperature.

The overall vision of the proposed effort is to enable physics-based data-driven design decisions of hypersonic scramjet engines. The objective of proposed effort is to unravel the flow processes within a truncated buseman inlet/isolator executing different tactical maneuvers using complementary experiments and computations. The investigations will focus on ram/scram take-over Mach numbers, which form the critical bottleneck in the engine operation.

The overall vision of the proposed work is to contribute to the understanding of inlet unstart in practical scramjet engine configurations. The theme of this proposal is to answer ����������������what basic physics relevant to unstart initiation and propagation are transferable between canonical axisymmetric and rectangular geometries that could be subject to unit problem investigation and more practical geometries?��������������� Specifically, the objective of the proposed work is to unravel the feedback interactions between the boundary layer structures and separated flow in the isolator and the corresponding combustion processes. An experimental effort is proposed where unstart in an axisymmetric geometry held at different incidence angles will be generated by combustion.