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Navier-Stokes computations with finite-rate chemistry for LO2/LH2 rocket engine plume flow studiesComputational fluid dynamics methods have been developed and applied to Space Shuttle Main Engine LO2/LH2 plume flow simulation/analysis of airloading and convective base heating effects on the vehicle at high flight velocities and altitudes. New methods are described which were applied to the simulation of a Return-to-Launch-Site abort where the vehicle would fly briefly at negative angles of attack into its own plume. A simplified two-perfect-gases-mixing approach is used where one gas is the plume and the other is air at 180-deg and 135-deg flight angle of attack. Related research has resulted in real gas multiple-plume interaction methods with finite-rate chemistry described herein which are applied to the same high-altitude-flight conditions of 0 deg angle of attack. Continuing research plans are to study Orbiter wake/plume flows at several Mach numbers and altitudes during ascent and then to merge this model with the Shuttle 'nose-to-tail' aerodynamic and SRB plume models for an overall 'nose-to-plume' capability. These new methods are also applicable to future launch vehicles using clustered-engine LO2/LH2 propulsion.
Document ID
19910034577
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Dougherty, N. Sam
(Rockwell International Corp. Huntsville, AL, United States)
Liu, Baw-Lin
(Rockwell International Corp. Space Systems Div., Huntsville, AL, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 91-0246
Accession Number
91A19200
Distribution Limits
Public
Copyright
Other

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