A 3-d numerical model for predicting mesoscale windfields over vandenberg afb is being developed. the model utilizes an objective analysis technique and available meteorological data to generate a first guess, mass consistent windfield. a hybrid finite element method is then used to solve the… More

The use of rectangular exhaust nozzles for aircraft configurations offers some interesting possibilities in the area of flow manipulation in order to enhance the mixing of the hot exhaust plume with the surrounding cool air. this proposal suggests that the manipulation and placement of streamwise… More

This proposal describes a project to develop, analyze, and design a novel oblique detonation wave ram accelerator driven hypersonic test capability in the high velocity, high temperature, and high pressure regime. current wind tunnels are inadequate for the high temperature and pressureconditions… More

A multi-dimensional numerical model for predicting cloud cover, fog, and haze under battlefield conditions is developed. the program utilizes real time meteorological data (when available) to predict meteorological conditions over irregular terrain. the computer program is relatively simple and… More

Phase I will analyze use of a hypervelocity launcher to provide ahigh mass (2 to 20 kilograms), hypervelocity (4 km\sec) demonstrator for a Theater Missile Defense (TMD) System. Current ballistic powder guns, along with one and two stage light gas guns, cannot meet the high mass requirements while… More

A two-dimensional numerical model based on a hybrid finite element method with mesh adaptation is proposed to calculate groundwater flow and pollutant transport in unsaturated porous media. the algorithm is modified to enhance computational speed and storage, and incorporates petrov-galerkin… More

The following proposal details an effort required for understanding the in-bore aerodynamic stability of sub-caliber projectiles in aero-thermal- chemical (ATC) guns in order to design stable projectiles. The ATC gun is based on the concept of a projectile traveling through the propellant and… More

This proposal describes a novel, high thrust density Detonation Wave Engine (DWE) applicable to the Mach range of 0 to 3. The geometry of this novel engine concept naturally provides for integration into a new Combined Cycle Engine with Ramjets. The concept is an intermittent combustion jet engine… More

An innovative actively cooled structure concept is proposed which integrates proven cooling techniques and state-of-the-art fabrication methods to extend the maximum combustor wall temperature, thereby reducing cooling requirements and aircraft weight while improving engine performance.… More

The Oblique Detonation Wave Hypervelocity Scramjet(ODW Hy-Scram) Engine is applicable to hypersonic flight vehicles that require high Mach Scramjet operation. This project will implement a unique new analysis capability to analyze and assess a novel propulsion device that could greatly enhance… More

This proposal describes an innovative Ultra-Low NOx annular swirl combustor concept for aircraft gas turbine engines. The concept is based on previously demonstrated means for creating high mixing rate regions in free shear flows by manipulating existing vorticity to create multiple discrete… More

The Oblique Detonation Wave Hypervelocity Scramjet (ODW Hy-Scram) Engine is applicable to hypersonic flight vehicles that require high Mach Scramjet operation. This project will implement a unique new analysis capability to analyze and assess a novel propulsion device that could greatly enhance… More

The use of commercially available technology for military hardware either as it exists off-the-shelf or with slight modification presents a large opportunity for cost saving in both the non-recurring development cost and the recurring cost of production and maintenance of military hardware. This… More

We propose to engineer a low-cost computer-controlled optical diagnostic system for measuring sound speed, thermal diffusivity, density, and velocity. This system will use laser-induced thermal accoustics (LITA), a transient-grating technique capable of making accurate single-shot measurements in… More

We propose to engineer a low-cost computer-controlled optical diagnostic system for measuring sound speed, thermal diffusivity, density, and velocity. This system will use laser-induced thermal accoustics (LITA), a transient-grating technique capable of making accurate single-shot measurements in… More

The complex HEV power systems necessitates flexible and dynamic simulation software providing tools for evaluating, characterizing and optimizing these systems. Existing software have neglected to characterize significant component data such as heat loads, cabin cooling requirements, battery… More

The Pulse Detonation Engine (PDE) is an intermittent combustion engine that relies on traveling detonation waves for the combustion and compression elements of the prosulsive cycle. This engine may be used as a low cost propulsion system in defense flight vehicle system applications or as the low… More

Not Available As microelectronic circuits used in space applications become more and more complex with greater capabilities, they require more chips, more memory, and more room. This means increased size and weight which means increased launch costs. One technique tha

The development of a pre-compressor mass injection system for extending the flight Mach number and altitude of conventional military afterburning turbofan engines is proposed. The injection of water and liquid oxidizer such as liquid oxygen can be used toenhance the performance of these engines so… More

"The development of a pre-compressor mass injection system for extending the flight Mach number and altitude of conventional military afterburning turbo jet and turbofan engines is proposed. The injection of water and liquid oxidizer such as liquid oxygencan be used to enhance the performance of… More

This proposal describes an innovative, high-efficiency, compactcombustor for lean-premixed, low-emissions gas turbine systems andresponds directly to NASA's request for Innovative technologiesrelating to combustion processes, including fuel injectors, piloting,flameholding techniques for increased… More

This proposal describes an innovative, high-efficiency, compactcombustor for lean-premixed, low-emissions gas turbine systems andresponds directly to NASA's request for Innovative technologiesrelating to combustion processes, including fuel injectors, piloting,flameholding techniques for increased… More

We propose to engineer a compact, robust, optically-based sensor for measuring local oxygen concentration in aircraft fuel tanks. This system will utilize absorption of rapidly scanned Vertical Cavity Surface Emitting Diode Lasers (VCSELs) by molecular oxygen. This proposed system can measure 100… More

The objective of the proposed Phase II effort is to transfer proven sensor technology from the laboratory breadboard to a functional flight-ready prototype for installation in an aircraft fuel tank. In the Phase I effort, a novel spectroscopic technique was shown to be an effective method for… More

Laser induced thermal acoustics (LITA) is a nonintrusive, transient-grating optical technique that provides simultaneous high-accuracy measurements of velocity, sound-speed, and thermal diffusivity among other parameters. In a fluid of known composition, sound speed and thermal diffusivity are… More

he use of an inter-turbine burner for improving the part power performance of small turboshaft engines in proposed. An inter-turbine burner is a second combustor placed between the gas generator exit and the power turbine to "reheat" the engine gas stream before it enters the power turbine. The… More

The Air Force seeks a large production wind tunnel seeding system with full field steering capability. Additionally, the system must offer control of the particle size and density along with minimal maintenance and flow disturbance characteristics. These features will increase tunnel productivity,… More

The development of an Inter-Turbine Burner (ITB) for improving the part power performance of small gas turbine engines is proposed. An Inter-Turbine Burner is a second combustor placed between the gas generator exit and the power turbine to "reheat" the engine gas stream before it enters the power… More

We propose a method that specifically addresses the requirement for helicopter engine torque sensor validation by integrating the engine component level model, model reduction techniques, and real-time parameter estimation algorithms. The method starts with a component level turboshaft model.… More

The Air Force seeks a large production wind tunnel seeding system with full field steering capability. Additionally, the system must offer control of the particle size and density along with minimal maintenance and flow disturbance characteristics. These features will increase tunnel productivity,… More