Accession Number : ADA567544


Title :   CFD Transient Simulation of an Isolator Shock Train in a Scramjet Engine


Descriptive Note : Doctoral thesis


Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING AND MANAGEMENT


Personal Author(s) : Hoeger, Troy C


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a567544.pdf


Report Date : Sep 2012


Pagination or Media Count : 221


Abstract : For hypersonic flight, the scramjet engine uses an isolator to contain the pre-combustion shock train formed by the pressure difference between the inlet and the combustion chamber. If this shock train were to reach the inlet, it would cause an engine unstart, disrupting the flow through the engine and leading to a loss of thrust and potential loss of the vehicle. Prior to this work, a Computational Fluid Dynamics (CFD) simulation of the isolator was needed for simulating and characterizing the isolator flow and for finding the relationship between back pressure and changes in the location of the leading edge of the shock train. In this work, the VULCAN code was employed with back pressure as an input to obtain the time history of the shock train leading location. Results were obtained for both transient and steady-state conditions. The simulation showed a relationship between back-to-inlet pressure ratios and final locations of the shock train. For the 2-D runs, locations were within one isolator duct height of experimental results while for 3-D runs, the results were within two isolator duct heights.


Descriptors :   *COMPUTATIONAL FLUID DYNAMICS , *SUPERSONIC COMBUSTION RAMJET ENGINES , HYPERSONIC FLIGHT , SIMULATION , THESES


Subject Categories : Jet and Gas Turbine Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE