COMBINED EXPERIMENTAL-ANALYTICAL INVESTIGATION OF AFTERBURNING SOLID ROCKET EXHAUST PLUME PROPERTIES TO IMPROVE SIGNATURE LEVEL PREDICTION CAPABILITY

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Authors
  1. Sislian, J.P.
Corporate Authors
Toronto Univ, Toronto ONT (CAN) Inst for Aerospace Studies;Defence Research Establishment Valcartier, Valcartier QUE (CAN)
Abstract
The present report outlines the experimental work performed on a high speed premixed hydrogen/air jet flame in a co-flowing annular air flow in the presence and absence of a base flow at the exit. The results of the investigation of the "cold" flow were reported in the Annual Contract Report, 1988. A detailed description is given of the high-speed (300 m/s) premixed hydrogen/air flame in a high-speed (100 m/s) co-axial air facility which was designed, built and thoroughly tested to simulate, in a first approximation, rocket exhaust flow conditions. Also, a new high spatial resolution computer-controlled three-dimensional gear was built to traverse the investigated flowfield. The main experimental tool is a two-dimensional laser Doppler velocimeter with the corresponding data acquisition and processing system.
Keywords
Laser Doppler velocimetry (LDV)
Date of publication
01 Oct 1990
Number of Pages
192
DSTKIM No
96-01989
CANDIS No
203317
Format(s):
Document Image stored on Optical Disk;Hardcopy

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