Education

Research Description

Dr. Edwards is interested in computational fluid dynamics (CFD), 2D and 3D compressible flows, reactive and multi-phase flows, and turbulence modeling. Dr. Edwards is currently 1) developing large eddy simulation techniques for high speed internal flows in advanced engine concepts (ram jets, scram jets, etc.), 2) conducting simulations of entry/exit into collective protection systems designed to enable operation in contaminated environments, and 3) developing multi-phase flow simulation methods as applied to industrial/medical processes. He is Principal Investigator of the Aerospace Engineering Computational Fluid Dynamics Laboratory. In MAE, he collaborates with Dr. Dow, Dr. Eischen, Dr. Hassan, Dr. Luo, Dr. Fang, and Dr. Gopalarathnam.

Publications

Flow criticality governs leading-edge-vortex initiation on finite wings in unsteady flow

Hirato, Y., Shen, M., Gopalarathnam, A., & Edwards, J. R. (2021), JOURNAL OF FLUID MECHANICS, 910. https://doi.org/10.1017/jfm.2020.896

Are poly(p-phenylene terephthalamide) (Kevlar (R)) and other liquid crystalline polymers conformationally rigid?

Tonelli, A. E., & Edwards, J. F. (2020), POLYMER, 193. https://doi.org/10.1016/j.polymer.2020.122342

Mesh-Sequenced Realizations for Evaluation of Subgrid-Scale Models for Turbulent Combustion

Edwards, J. R., & Nielsen, T. B. (2020), AIAA JOURNAL, 58(11), 4878–4892. https://doi.org/10.2514/1.J059217

Variation of leading-edge suction during stall for unsteady aerofoil motions

Narsipur, S., Hosangadi, P., Gopalarathnam, A., & Edwards, J. R. (2020), JOURNAL OF FLUID MECHANICS, 900. https://doi.org/10.1017/jfm.2020.467

Least Squares Minimization Closure Models for LES of Turbulent Combustion

Patton, C. H., & Edwards, J. R. (2019), FLOW TURBULENCE AND COMBUSTION, 102(3), 699–733. https://doi.org/10.1007/s10494-018-9968-5

Low-Order Model for Prediction of Trailing-Edge Separation in Unsteady Flow

Narsipur, S., Gopalarathnam, A., & Edwards, J. R. (2019), AIAA JOURNAL, 57(1), 191–207. https://doi.org/10.2514/1.J057132

Numerical Simulation of Two-Phase Flow Within Aerated-Liquid Injectors

Bornhoft, B. J., Edwards, J. R., & Lin, K.-C. (2019), JOURNAL OF PROPULSION AND POWER, 35(6), 1034–1047. https://doi.org/10.2514/1.B37284

Reflections on the early development of the "AUSM family" of Riemann solvers

Edwards, J. R. (2019). [Review of , ]. SHOCK WAVES, 29(5), 601–609. https://doi.org/10.1007/s00193-018-0863-8

Vortex-Sheet Representation of Leading-Edge Vortex Shedding from Finite Wings

Hirato, Y., Shen, M., Gopalarathnam, A., & Edwards, J. R. (2019), JOURNAL OF AIRCRAFT, 56(4), 1626–1640. https://doi.org/10.2514/1.C035124

Development of a premixed combustion capability for dual-mode scramjet experiments

Rockwell, R. D., Goyne, C. P., Chelliah, H., McDaniel, J. C., Rice, B. E., Edwards, J. R., … Danehy, P. M. (2018), Journal of Propulsion and Power, 34(2), 438–448. https://doi.org/10.2514/1.b36550

View all publications via NC State Libraries

Grants

2020-2021 AIAA Design-Build-Fly Team Space Grant Proposal

National Aeronautics & Space Administration (NASA)(11/01/20 - 7/15/21)

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2020-2021 AIAA Design-Build-Fly Team Space Grant Proposal

Sponsor: National Aeronautics & Space Administration (NASA)

Start Date: 11/01/20

End Date: 7/15/21

Abstract

This proposal requests support for our AIAA Design-Build-Fly team to build an aircraft in response to AIAA's annual competition. This year's aircraft will be designed to deploy a banner and will have short takeoff capabilities.

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Scale-Resolving Numerical Simulation of Reactive, Two Phase Flows in Hypersonic Propulsion Designs – Part II

Air Force Research Laboratory (AFRL)(3/01/21 - 1/02/23)

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Scale-Resolving Numerical Simulation of Reactive, Two Phase Flows in Hypersonic Propulsion Designs – Part II

Sponsor: Air Force Research Laboratory (AFRL)

Start Date: 3/01/21

End Date: 1/02/23

Abstract

This project continues the development of modeling and simulation strategies for two-phase reactive flows characteristic of high-speed engine concepts. We will develop a method for modeling primary atomization enhancement through dissolved-gas nucleation, will develop a primary breakup model for pure liquid injection, and will model injection, vaporization, and breakup of liquid hydrocarbons.

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Investigations of Self Starting Streamtraced Inlets at Off-Design Conditions

US Navy - Naval Surface Warfare Center(9/09/20 - 9/08/21)

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Investigations of Self Starting Streamtraced Inlets at Off-Design Conditions

Sponsor: US Navy - Naval Surface Warfare Center

Start Date: 9/09/20

End Date: 9/08/21

Abstract

The overall vision of the proposed effort is to enable physics-based data-driven design decisions of hypersonic scramjet engines. The objective of proposed effort is to unravel the flow processes within a truncated buseman inlet/isolator executing different tactical maneuvers using complementary experiments and computations. The investigations will focus on ram/scram take-over Mach numbers, which form the critical bottleneck in the engine operation.

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High-Fidelity Numerical Simulations of Inlet / Isolator / Combustor Interactions

US Air Force - Office of Scientific Research (AFOSR)(9/24/20 - 9/23/21)

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High-Fidelity Numerical Simulations of Inlet / Isolator / Combustor Interactions

Sponsor: US Air Force - Office of Scientific Research (AFOSR)

Start Date: 9/24/20

End Date: 9/23/21

Abstract

This work will conduct large-eddy and direct numerical simulations of ethylene-fueled combustion in an inlet / isolator / combustor rig operational at the University of Illinois. Research issues include determination of the physical mechanisms that lead to the onset of thermal choking, upward propagation of pressure disturbances, and eventual transition to stable dual-model operation. Out-year tasks include simulations of combustion in non-axisymmetric flowpaths and predictive simulations of scramjet operation in the University of Queensland's R3X reflected-shock tunnel.

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Tailored Supersonic Flowfields

US Dept. of Defense (DOD)(12/12/19 - 12/14/20)

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Tailored Supersonic Flowfields

Sponsor: US Dept. of Defense (DOD)

Start Date: 12/12/19

End Date: 12/14/20

Abstract

This work will conduct numerical simulations and companion experiments to develop ways for modeling compressor-face distortion created by external compression, supersonic inlets. The work will be conducted in collaboration with Corvid Technologies through an Air Force STTR contract.

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2019-2020 AIAA Design-Build-Fly Team Space Grant Proposal

National Aeronautics & Space Administration (NASA)(11/15/19 - 8/01/20)

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2019-2020 AIAA Design-Build-Fly Team Space Grant Proposal

Sponsor: National Aeronautics & Space Administration (NASA)

Start Date: 11/15/19

End Date: 8/01/20

Abstract

This proposal requests support for our AIAA Design-Build-Fly team to build an aircraft in response to AIAA's annual competition. This year's aircraft will be designed to deploy a banner and will have short takeoff capabilities.

Close

Transition Prediction and Control for Blunt Hypersonic Configurations with Hemispherical and Ogival Nosetips

US Navy-Office Of Naval Research(4/27/20 - 3/31/23)

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Transition Prediction and Control for Blunt Hypersonic Configurations with Hemispherical and Ogival Nosetips

Sponsor: US Navy-Office Of Naval Research

Start Date: 4/27/20

End Date: 3/31/23

Abstract

This is a computational investigation into the physical mechanisms that lead to the onset of boundary layer transition (BLT) within the swallowing distance of the entropy layer on slender hypersonic vehicles with blunt, hemispherical or ogival nosetips.

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Development of Improved RANS and Hybrid LES/RANS Turbulence Models for Hypersonic Flow Applications

US Air Force Academy(7/08/19 - 7/07/22)

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Development of Improved RANS and Hybrid LES/RANS Turbulence Models for Hypersonic Flow Applications

Sponsor: US Air Force Academy

Start Date: 7/08/19

End Date: 7/07/22

Abstract

The proposed will develop new strategies for Reynolds-averaged Navier-Stokes (RANS) and hybrid large-eddy simulation / RANS modeling for hypersonic shock / boundary layer interactions. The approach will utilize wall-resolved large-eddy simulations, anchored using relevant experimental data, to provide information that can be used to refine and improve both classes of lower-fidelity models. Specific attention will be devoted to examining turbulence length scale evolution through a shock / boundary layer interaction, turbulence production near unsteady shock waves, and turbulent transport of energy to the surface, with a view toward incorporating more exact effects for these processes in engineering level models. An additional task will determine 'best practices' for comparing computational solutions with legacy experimental data sets for hypersonic flows. The University of Tennessee will be a subcontractor to this effort. UT will implement improved RANS and LES/RANS models developed by NCSU into COFFE, the higher-order finite-element branch of CREATE-AV's Kestrel suite of flow solvers.

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Scale-Resolving Numerical Simulation of Reactive, Two Phase Flows in Hypersonic Propulsion Designs

Air Force Research Laboratory (AFRL)(1/01/19 - 10/01/20)

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Scale-Resolving Numerical Simulation of Reactive, Two Phase Flows in Hypersonic Propulsion Designs

Sponsor: Air Force Research Laboratory (AFRL)

Start Date: 1/01/19

End Date: 10/01/20

Abstract

This proposal will develop an integrated scale-resolving modeling strategy for conducting numerical simulations of two-phase, reactive flows characteristic of high-speed propulsion devices. Components of the formulation include liquid-jet breakup models, secondary droplet breakup models, droplet vaporization, and hydrocarbon combustion. A hybrid large-eddy / Reynolds-averaged Navier-Stokes simulation strategy will be utilized. Geometric configurations to be studied will be obtained from AFRL.

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NCSU American Institute for Aeronautics and Astronautics 2019 Design-Build-Fly Competition

National Aeronautics & Space Administration (NASA)(11/15/18 - 7/31/19)

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NCSU American Institute for Aeronautics and Astronautics 2019 Design-Build-Fly Competition

Sponsor: National Aeronautics & Space Administration (NASA)

Start Date: 11/15/18

End Date: 7/31/19

Abstract

The American Institute of Aeronautics and Astronautics Design Build Fly Team (AIAA DBF) at NC State was founded in 2016 with the mission of inspiring collaboration within the engineering program through technical excellence and interdisciplinary challenges. In its debut competition last year, the NC State AIAA DBF team scored within the top 50% of teams with its report; this year, the team plans to place within the top quintile overall. The competition has a different objective each year which challenges students to present novel solutions to complex issues. This year's competition focuses on the design of a electrically-powered naval drone prototype with folding wings, a rotating 'radome', and the ability to drop a payload.

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