Design and optimization of a hypersonic test facility for sub-scale testing
Loading...
Authors
O'Kresik, Stephen R.
Subjects
Advisors
Sinibaldi, Jose O.
Date of Issue
2003-12
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
Abstract
The Rocket Propulsion and Combustion Laboratory at the Naval Postgraduate School was evaluated to determine if the currently installed systems could support the operation of a subscale hypersonic test stand. Trait analysis of existing lab support sub-systems was performed and an envelope of operation, defined by flight altitude and flight Mach number was determined. Calculations revealed that if the air supply volume was doubled to 160 ft3, a hypersonic blow-down facility could generate conditions to perform testing in the dynamic pressure window of 500 to 2000 psf, from Mach 5 to 7.5 with a maximum system mass flow rate variation from 3 to 45 lbm/s. Additionally, a dynamic design process was outlined to assist other designers in producing similar test stands. Finally, a software analysis package was developed to analyze proposed changes in the support system architecture.
Type
Thesis
Description
Series/Report No
Department
Astronautical Engineering
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
xiv, 71 p. : col. ill. ;
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.