NDLI: Space shuttle orbiter rear mounted reaction control system jet interaction study. [hypersonic wind tunnel tests

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Space shuttle orbiter rear mounted reaction control system jet interaction study. [hypersonic wind tunnel tests

Content Provider	NASA Technical Reports Server (NTRS)
Author	Rausch, J. R.
Copyright Year	1977
Description	The effect of interaction between the reaction control system (RCS) jets and the flow over the space shuttle orbiter in the atmosphere was investigated in the NASA Langley 31-inch continuous flow hypersonic tunnel at a nominal Mach number of 10.3 and in the AEDC continuous flow hypersonic tunnel B at a nominal Mach number of 6, using 0.01 and .0125 scale force models with aft RCS nozzles mounted both on the model and on the sting of the force model balance. The data show that RCS nozzle exit momentum ratio is the primary correlating parameter for effects where the plume impinges on an adjacent surface and mass flow ratio is the parameter when the plume interaction is primarily with the external stream. An analytic model of aft mounted RCS units was developed in which the total reaction control moments are the sum of thrust, impingement, interaction, and cross-coupling terms.
File Size	21303044
Page Count	451
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19770022263
Archival Resource Key	ark:/13960/t8jd9nt61
Language	English
Publisher Date	1977-05-01
Access Restriction	Open
Subject Keyword	Space Transportation Jet Thrust Wind Tunnel Tests Orbit Maneuvering Engine Space Shuttle Spacecraft Control Hypersonic Wind Tunnels Thrust Control Space Shuttle Orbiters Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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