You're welcome. I'm sorry I came across as I did in the original reply. This thesis just irked me on so many different levels, the most basic that this poor student came away with such a lack of the fundamentals involved in the inlet starting problem. It didn't help that I know a few of those referenced and had/have a hard time comprehending how they might have even been peripherally involved and it still come to this end. Another irritation is the lack of many of those involved in the 3D inlet work these days having not learned the lessons from multi-dimensional internal compression work done by NASA and others, such as Rocketdyne.
Title: Rocket-Based Combined Cycle Engine Concept Development
Online Source: Click to View PDF File [PDF Size: 978 KB]
Author: Ratekin, G.; Goldman, Allen; Ortwerth, P.; Weisberg, S.; McArthur, J. Craig
Abstract:
The development of rocket-based combined cycle (RBCC) propulsion hide hide
systems is part of a 12 year effort under both company funding and contract work. The concept is a fixed geometry integrated rocket, ramjet, scramjet, which is hydrogen fueled and uses hydrogen regenerative cooling. The baseline engine structural configuration uses an integral structure that eliminates panel seals, seal purge gas, and closeout side attachments. Engine A5 is the current configuration for NASA Marshall Space Flight Center (MSFC) for the ART program. Engine A5 models the complete flight engine flowpath of inlet, isolator, airbreathing combustor, and nozzle. High-performance rocket thrusters are integrated into the engine enabling both low speed air-augmented rocket (AAR) and high speed pure rocket operation. Engine A5 was tested in GASL's new Flight Acceleration Simulation Test (FAST) facility in all four operating modes, AAR, RAM, SCRAM, and Rocket. Additionally, transition from AAR to RAM and RAM to SCRAM was also demonstrated. Measured performance demonstrated vision vehicle performance levels for Mach 3 AAR operation and ramjet operation from Mach 3 to 4. SCRAM and rocket mode performance was above predictions. For the first time, testing also demonstrated transition between operating modes.
Collection: NASA
NASA Center: Marshall Space Flight Center
Publication Date: [2001]
Publication Year: 2001
Document ID: 20020016608
Subject Category: SPACECRAFT PROPULSION AND POWER
Contract/Grant/Task Number: NAS8-40864
Publication Information: Number of pages = 35
Language: English
Subject Terms: ENGINE DESIGN; FLIGHT SIMULATION; PERFORMANCE TESTS; PROPULSION SYSTEM CONFIGURATIONS; RAMJET ENGINES; STRUCTURAL ANALYSIS; SUPERSONIC COMBUSTION RAMJET ENGINES; WEIGHT REDUCTION
Accessibility: Unclassified; Publicly available; Unlimited; Copyright, Distribution as joint owner in the copyright
Document Source: CASI
Updated/Added to NTRS: Jul 25, 2009
http://hdl.handle.net/2060/20020016608
Title: A Combined Experimental/Computational Investigation of a Rocket Based Combined Cycle Inlet
Online Source: Click to View PDF File [PDF Size: 1024 KB]
Author: Smart, Michael K.; Trexler, Carl A.; Goldman, Allen L.
Abstract:
A rocket based combined cycle inlet geometry has undergone wind tunnel hide hide
testing and computational analysis with Mach 4 flow at the inlet face. Performance parameters obtained from the wind tunnel tests were the mass capture, the maximum back-pressure, and the self-starting characteristics of the inlet. The CFD analysis supplied a confirmation of the mass capture, the inlet efficiency and the details of the flowfield structure. Physical parameters varied during the test program were cowl geometry, cowl position, body-side bleed magnitude and ingested boundary layer thickness. An optimum configuration was determined for the inlet as a result of this work.
Collection: NASA
NASA Center: Langley Research Center; Marshall Space Flight Center
Publication Date: [2001]
Publication Year: 2001
Document ID: 20010023936
Subject Category: SPACECRAFT PROPULSION AND POWER
Report/Patent Number: AIAA Paper 2001-0671
Publication Information: Number of pages = 10
Language: English
Meeting Information: Aerospace Sciences; 39th; 8-11 Jan. 2001; Reno, NV; United States
Subject Terms: ANALYSIS (MATHEMATICS); COMPUTATIONAL FLUID DYNAMICS; FLOW DISTRIBUTION; PRESSURE; ROCKET-BASED COMBINED-CYCLE ENGINES; SPACECRAFT PROPULSION; SUPERSONIC SPEED; WIND TUNNEL TESTS
Accessibility: Unclassified; Publicly available; Unlimited; Copyright, Distribution as joint owner in the copyright
Document Source: CASI
Updated/Added to NTRS: Jul 25, 2009
http://hdl.handle.net/2060/20010023936
