HAPB Functional Capabilities

Engine Flowpath Development and Integration

Responsible for hypersonic airbreathing propulsion flowpath development, performance, and operability assessment. This includes design and development of the propulsion flowpath for a given vehicle and mission, including efficient integration of combined-cycle propulsion modes (ramjet, scramjet, rocket, turbojet, detonation engine, etc.), testing of both engine and component hardware, analysis of the acquired data, the codification and archiving of design databases and criteria gleaned from both analysis and test programs, and the projection of ground facility data to flight environments.

Computational Methods for Reacting Flows

Responsible for developing, validating, and applying computational fluid dynamics (CFD) codes and analytical methods for the prediction and assessment of the performance of hypersonic airbreathing propulsion systems and the individual system components. The spectrum of codes include engine cycle codes, including flow distortion; combined CFD/analytical codes, such as SRGULL; and 3-D FNS codes, such as VULCAN, which is capable of providing detailed engine flowfield information. These codes, after validation using data acquired from fundamental experiments and from engine tests in ground test facilities, are applied to predict propulsion system performance in flight..

Hypersonic Airbreathing Propulsion Test Facilities

Responsible for operating and conducting propulsion tests in the facilities of the NASA Langley Scramjet Test Complex and advancing facility flight simulation capabilities. This Complex includes the Direct-Connect Supersonic Combustion Test Facility, the Combustion-Heated Scramjet Test Facility, the Arc-Heated Scramjet Test Facility, the 8-Foot High Temperature Tunnel, and the HYPULSE shock/expansion tunnel (located at ATK-GASL). These facilities provide information on the effects on propulsion system performance of speed and dynamic pressure from Mach 3.5 to near-orbital speeds, and engine scale and test gas composition from Mach 4 to 7. Experienced facility personnel and propulsion engineers provide unique test capabilities using proven scramjet test techniques.

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Last updated: Thursday, August 14, 2008 14:48