Award Data

Our Phase II program will provide for the design, fabrication, and testing of skin friction gauges and force measurement modules that will operate in a hypersonic scramjet propulsive flowpath with hydrogen/air combustion. Gauges will be installed in the CUBRC Combustion Duct and a test matrix performed to demonstrate operability as well as to provide detailed data for the validation of CFD codes. ...

The program focuses on turbulence modeling enhancements for predicting coupled jet interaction baseflows. Unified ke turbulence model, and varied extensions that provide for scalar fluctutation models (SFM), baroclinic torque effects, realizability constrainst, vorticity/strain non-equilibrium effects, etc. will be systematically evaluated. Complimentary Large Eddy Simulations (LES) and hybrid RAN ...

Our proposal addresses the high fidelity modeling of transient rocket exhaust plumes in a static test environment. Static testing provides a practical means of obtaining plume signature data to support model validation. However, existing CFD codes routinely used for plumes in flight cannot accurately address many of the complexities associated with a static test environment. Our starting point wil ...

Plume signature phenomenology plays an increasingly important role in the development of a wide variety of missile defense technologies, both at the tactical and strategic levels. With the emergence of recent threats, plume signature phenomenology is increasingly central to Missile Defense Agency"s fundamental mission of development of a Ballistic Missile Defense System (BMDS). The Missile Defense ...

Plume signature phenomenology plays an increasingly important role in the development of a wide variety of missile defense technologies, both at the tactical and strategic levels. With the emergence of recent threats, plume signature phenomenology is increasingly central to Missile Defense Agency"s fundamental mission of development of a Ballistic Missile Defense System (BMDS). The Missile Defense ...

The proposed Phase I effort involves the formulation of improved models to accurately simulate the particles that are present in rocket exhaust plume flowfields with the goal of obtaining improved plume signature predictions. While the modeling of the exhaust plume flowfield is a relatively mature technology, the sub models that are utilized to describe the behavior of the particle phase are in n ...

ABSTRACT: Next generation liquid rocket systems, envision novel designs for cryogenic turbopumps that exhibit high suction performance with low inlet pressures, operate at high tip speeds to reduce size and weight, and can be throttled over a wide range of low, off-design flow conditions where the inlet flow quality is poor with large backflow. These are extremely demanding flow regimes which ma ...

As air vehicle speeds increase, air breathing engine and inlet technology follow through concurrent supersonic performance requirements. The recent ability to build smaller supersonic engines has established a void in small air vehicle inlet capability. A solution to decrease the overall footprint of supersonic inlets within next-generation Supersonic Cruise Missiles (SSCMs) is desired. SSCMs, lik ...

The noise from the turbulent, hot, supersonic jets at take-offs and landings dominates noise emanating from other powerplant components and has significant safety implications for launch personnel, as well as by the integrity of the structural components of the deck itself. With the impending induction of the JSF/F-35B into the US Navy in the near-future, concerns regarding noise emissions have ta ...

An innovative approach for incorporating the coupled interaction between a ship airwake and rotor downwash in real-time dynamic interface simulations is proposed. The approach employs a database of high-fidelity ship-alone and coupled rotor-ship airwake CFD simulations to train an artificial neural network (ANN) based model of the recirculation effects due to the rotor downwash interaction with sh ...