Upper-stage rocket engines with large area ratio nozzles must be tested under simulated altitude conditions during development; experiment conducted to determine operational and heat-transfer characteristics of rocket engine altitude-simulation ejector systems for such testing; constant-area and second-throat types were tested; both types, with 90° turns required higher engine chamber pressures to obtain ejector system start than geometrically similar straight systems; other findings.
Scale model testing of 90° supersonic turn ejector systems for altitude simulation
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 1 , n 1
1964
4 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.