Design and Optimization of a Hypersonic Test Facility for Sub-Scale Testing

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 ft(3), 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.Naval Postgraduate School Monterey CA is the author of 'Design and Optimization of a Hypersonic Test Facility for Sub-Scale Testing', published 2003 under ISBN 9781423514145 and ISBN 1423514149.