HIFiRE Flight 2 Project Overview and Status Update 2011

Jackson, Kevin; Gruber, Mark; Buccellato, Salvatore

doi:10.2514/6.2011-2202

Cited by 42 publications

(16 citation statements)

References 18 publications

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“…In prior wall-modeling implementations, thermal feedback to the LES solution was limited to the wall heat flux and was simply zero in the adiabatic case. Figure 1 shows the HIFiRE Flight 2 (HF2) scramjet [22] with relevant dimensions shown. At each streamwise fuel injection station shown in Fig.…”

Section: Wall Modelingmentioning

confidence: 99%

“…Profiles of the Reynolds stress tensor from the boundary layer DNS data of Wu and Moin [29] are rescaled and used as inputs. As the turbulent conditions inside the HIFiRE isolator are not well characterized [23,22], the objective of this approach is simply to develop a fully turbulent boundary layer prior to the primary fuel injectors. This is similar to the approach taken in Brès et al [30], where for practical design studies the synthetic turbulence inside a jet nozzle is prescribed in a manner to ensure realistic turbulence levels at the nozzle exit.…”

Section: Boundary Conditionsmentioning

confidence: 99%

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Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Saghafian

Shunn

Philips

et al. 2015

Proceedings of the Combustion Institute

106

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In this study, large eddy simulations (LES) of supersonic combustion using a compressible flamelet/progress variable (CFPV) approach are performed for the HIFiRE scramjet at Mach 8 flight conditions. The LES results show good agreement with the ground test experimental measurements. The combustion model is based on an efficient flamelet approach, where compressibility corrections are devised based on assumed functional forms of important thermo-chemical quantities. Specifically, the source term of the progress variable is rescaled with the local density and temperature in the LES, leading to improved predictions relative to existing flamelet models. A modified equilibrium wall-model, capable of predicting the viscous heating, is used in the viscous near-wall region. Temperature near the wall increases significantly due to viscous heating, enhancing the reaction rate and heat-release. This is shown to be a crucial step for accurately predicting the pressure rise in the combustor.

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Section: Wall Modelingmentioning

confidence: 99%

Section: Boundary Conditionsmentioning

confidence: 99%

Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Saghafian

Shunn

Philips

et al. 2015

Proceedings of the Combustion Institute

106

View full text Add to dashboard Cite

show abstract

“…7 HIFiRE Flight 2 -scheduled for launch in 2012 -includes a water-based absorption sensor at the combustor exit aimed at in-flight assessment of combustion efficiency. 8 This same technology lends itself well to ground test applications, particularly in hardware with limited optical access. By using a time-multiplexed direct scan absorption approach we serially collect three types of optical signals for each frequency sweep of the diode lasers employed.…”

Section: Introductionmentioning

confidence: 95%

Application of Diode-Laser-Based Measurements in Hypersonic Flows

Brown

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The development of optical techniques capable of measuring in-stream flow properties of air breathing hypersonic engines is a goal of the Aerospace Propulsion Division at AFRL. This goal is motivated by the need for in-stream data to support both ground and flight tests of scramjet engine designs. While particular fundamental hypersonic flow problems are addressable using well-established laser-based techniques, advanced engine concepts using axisymmetric hardware typically have minimal optical access making some of the more traditional techniques difficult to deploy. To meet the need we have an ongoing in-house program to mature diode-laser-based techniques for application in hypersonic flows. Additional motivation for developing diode-laser-based measurement strategies comes from the need for flight sensors. Flight-worthy packages must be small, light, low-power and rugged. For measurement objectives in both ground and flight experiments we have adopted tunable diode laser absorption spectroscopy making heavy use of fiber coupling and integrated optomechanics. Water-based measurements of temperature, pressure, velocity, and water mole fraction are executed using time-multiplexed near-infrared diodes. These fundamental flow parameters can be combined to yield optical mass capture and thrust. Similar measurements can be made in inlets using an oxygen-based strategy employing visible diodes. In this paper we summarize the absorption sensor work done to date in AFRL. Particular attention will be paid to the fact that a single hardware platform can be used to capture absorption, non-resonant transmission, and optical emission signals all three of which provide relevant information.

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“…The primary objective of HF2 is to explore mode transition and supersonic combustion of a hydrocarbon fuel between M 6 and 8. Collaborators for this flight include the U.S. Air Force Research Laboratory, NASA Langley Research Center, ATK Aerospace Company General Applied Science Laboratories and the White Sands Missile Range (WSMR) [4].…”

Section: Introductionmentioning

confidence: 99%

Mach 6–8+ Hydrocarbon-Fueled Scramjet Flight Experiment: The HIFiRE Flight 2 Project

Jackson

Gruber

Buccellato

2015

Journal of Propulsion and Power

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The Hypersonic International Flight Research Experimentation (HIFiRE) program is a collaborative international effort designed to study basic hypersonic phenomena through flight experimentation. On 1 May 2012, the HIFiRE Flight 2 project successfully flew a hydrocarbon-fueled, Mach 8 scramjet experiment and demonstrated the ability to fly an accelerating, constant dynamic pressure trajectory consistent with a scramjet-powered flight vehicle using unguided sounding rocket techniques. The project goals of capturing high-quality flight data from a research scramjet operating through dual-to-scram mode transition up to and beyond Mach 8 were achieved. HIFiRE Flight 2 is unique in its contribution to scramjet research, providing a reference dataset to the hydrocarbon scramjet community while maturing a novel and reduced-cost strategy for performing similar future experiments. This paper describes the programmatic approach, the overall scramjet flight test experiment mission objectives, and the flight test strategy. It also includes an overview of launch system and payload hardware, and brief discussions of flight activities, flight data, and experimental results. Preliminary results from flight indicate a fully successful mission and experiment. Based on evaluations of data collected during the project, including ground test, flight test, and multiple analysis activities, all project-level scientific objectives have been successfully achieved.

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HIFiRE Flight 2 Project Overview and Status Update 2011

Cited by 42 publications

References 18 publications

Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Large eddy simulations of the HIFiRE scramjet using a compressible flamelet/progress variable approach

Application of Diode-Laser-Based Measurements in Hypersonic Flows

Mach 6–8+ Hydrocarbon-Fueled Scramjet Flight Experiment: The HIFiRE Flight 2 Project

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