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Pulse Detonation Engine Air Induction System AnalysisA preliminary mixed-compression inlet design concept for potential pulse-detonation engine (PDE) powered supersonic aircraft was defined and analyzed. The objectives of this research were to conceptually design and integrate an inlet/PDE propulsion system into a supersonic aircraft, perform time-dependent CFD analysis of the inlet flowfield, and to estimate the installed PDE cycle performance. The study was baselined to a NASA Mach 5 Waverider study vehicle in which the baseline over/under turboramjet engines were replaced with a single flowpath PDE propulsion system. As much commonality as possible was maintained with the baseline configuration, including the engine location and forebody lines. Modifications were made to the inlet system's external ramp angles and a rotating cowl lip was incorporated to improve off-design inlet operability and performance. Engines were sized to match the baseline vehicle study's ascent trajectory thrust requirement at Mach 1.2. The majority of this study was focused on a flight Mach number of 3.0. The time-dependent Navier Stokes CFD analyses of a two-dimensional approximation of the inlet was conducted for the Mach 3.0 condition. The Lockheed Martin Tactical Aircraft Systems-developed FALCON CFD code with a two equation 'k-1' turbulence model was used. The downstream PDE was simulated by an array of four sonic nozzles in which the flow areas were rapidly varied in various opening/closing combinations. Results of the CFD study indicated that the inlet design concept operated successfully at the Mach 3.0 condition, satisfying mass capture, total pressure recovery, and operability requirements. Time-dependent analysis indicated that pressure and expansion waves from the simulated valve perturbations did not effect the inlet's operability or performance.
Document ID
19960041538
Acquisition Source
Langley Research Center
Document Type
Conference Paper
Authors
Pegg, R. J.
(NASA Langley Research Center Hampton, VA United States)
Hunter, L. G.
(Lockheed Martin Tactical Aircraft Systems Fort Worth, TX United States)
Couch, B. D.
(Lockheed Martin Tactical Aircraft Systems Fort Worth, TX United States)
Date Acquired
August 17, 2013
Publication Date
July 3, 1996
Subject Category
Mechanical Engineering
Report/Patent Number
NASA-TM-111863
AIAA Paper 96-2918
NAS 1.15:111863
Meeting Information
Meeting: AIAA/ASME/SAE/ASEE Joint Propulsion Conference
Location: Lake Buena Vista, FL
Country: United States
Start Date: July 1, 1996
End Date: July 3, 1996
Sponsors: Society of Automotive Engineers, Inc., American Society of Mechanical Engineers, American Society for Electrical Engineers, American Inst. of Aeronautics and Astronautics
Accession Number
96N72342
Distribution Limits
Public
Copyright
Public Use Permitted.
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