Under the Propulsion Discipline of NASA s Fundamental Aeronautics Program s Hypersonics Project, a test apparatus, for testing a scramjet isolator model, is being constructed at NASA's Langley Research Center. The test apparatus will incorporate a 1-inch by 2-inch by 15-inch-long scramjet isolator model supplied with 2.1 lbm/sec of unheated dry air through a Mach 2.5 converging-diverging nozzle. The planned research will incorporate progressively more challenging measurement techniques to characterize the flow field within the isolator, concluding with the application of the Laser-Induced Thermal Acoustic (LITA) measurement technique. The primary goal of this research is to use the data acquired to validate Computational Fluid Dynamics (CFD) models employed to characterize the complex flow field of a scramjet isolator. This paper describes the test apparatus being constructed, pre-test CFD simulations, and the LITA measurement technique.
Laser-Induced Thermal Acoustic Measurements in a Highly Back-Pressured Scramjet Isolator Model: A Research Plan
55th JANNAF Propulsion Meeting/42nd Combustion/30th Airbreathing Propulsion/30th Exhaust Plume Technology/24th Propulsion Systems Hazards/12th SPIRITS User Group Joint Subcommittee Meeting ; 2008 ; Newton, MA, United States
2008-05-12
Conference paper
No indication
English
British Library Conference Proceedings | 2013
|Unstart in an Axisymmetric Scramjet Isolator
AIAA | 2019
|SCRAMJET ISOLATOR SHOCK TRAIN LOCATION TECHNIQUES
British Library Conference Proceedings | 2011
|