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ENCIT 2020
18th Brazilian Congress of Thermal Sciences and Engineering
DEVELOPMENT OF A DEVICE FOR ANALYZING THE FLOW IN COLD CONDITION AT THE EXIT OF A SUPERSONIC COMBUSTION TEST BENCH
Submission Author:
Débora Cristina Menezes Silva , SP
Co-Authors:
Débora Cristina Menezes Silva, Valéria Leite, Israel Rêgo, Taiana Cortes
Presenter: Débora Cristina Menezes Silva
doi://10.26678/ABCM.ENCIT2020.CIT20-0352
Abstract
The study of hypersonic flow and supersonic combustion is conducted using ground test facilities such as shock tunnel, hypersonic mass accelerator and the direct-connected supersonic combustion test bench (SCTB). The present work will use a SCTB, one of the most commonly equipment used for the study of supersonic combustion and aerothermodynamics tests, which the main advantage is the time duration of the tests, compared to others ground test facilities and the fact that flow test can be performed both in cold or hot conditions .The SCTB simulates the same flow conditions inside a Scramjet’s combustor in actual flight. It consists basically of a combustion chamber or vitiated air generator (VAG), where the flow is heated to the desired temperature, and a supersonic nozzle, where the heated air is accelerated to supersonic speeds. In this context, the objective of this paper is to develop a device that can be capable to measure the speed of the cold flow at the outlet of the supersonic nozzle. For this it will be used a wedge, located in front of the supersonic flow, at the exit of the nozzle and the schlieren technique to visualize shock wave angle over the device to be tested.
Keywords
Supersonic Flow, ground test facilities, supersonic nozzle
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