<div class="description">
<p>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.
</p>
<br>Subjects: Aerodynamics, Hypersonic; Combustion chambers; Testing</div>
<div class="fn value">
O'Kresik, Stephen R.</div>
Internet Archive identifier