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CFD for hypersonic propulsionAn overview is given of research activity on the application of computational fluid dynamics (CDF) for hypersonic propulsion systems. After the initial consideration of the highly integrated nature of air-breathing hypersonic engines and airframe, attention is directed toward computations carried out for the components of the engine. A generic inlet configuration is considered in order to demonstrate the highly three dimensional viscous flow behavior occurring within rectangular inlets. Reacting flow computations for simple jet injection as well as for more complex combustion chambers are then discussed in order to show the capability of viscous finite rate chemical reaction computer simulations. Finally, the nozzle flow fields are demonstrated, showing the existence of complex shear layers and shock structure in the exhaust plume. The general issues associated with code validation as well as the specific issue associated with the use of CFD for design are discussed. A prognosis for the success of CFD in the design of future propulsion systems is offered.
Document ID
19910012134
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Povinelli, Louis A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-TM-103791
E-5689
NAS 1.15:103791
Meeting Information
Meeting: Workshop on Hypersonic Flow
Location: Antibes
Country: France
Start Date: January 22, 1990
End Date: January 25, 1990
Sponsors: National Research Inst. for Information and Automation, Group for Advancement of Numerical Engineering Methods
Accession Number
91N21447
Funding Number(s)
PROJECT: RTOP 506-62-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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