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

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

Leading-edge flow criticality as a governing factor in leading-edge vortex initiation in unsteady airfoil flows

Ramesh, K., Granlund, K., Ol, M. V., Gopalarathnam, A., & Edwards, J. R. (2018), Theoretical and Computational Fluid Dynamics, 32(2), 109–136. https://doi.org/10.1007/s00162-017-0442-0

Numerical simulation of aero-optical effects in a supersonic cavity flow

Zilberter, I. A., Edwards, J. R., & Wittich, D. J. (2017), AIAA Journal, 55(9), 3095–3108. https://doi.org/10.2514/1.j055402

Numerical simulations of turbulent flow over airfoils near and during static stall

Ke, J. H., & Edwards, J. R. (2017), Journal of Aircraft, 54(5), 1960–1978. https://doi.org/10.2514/1.c034186

Scramjet combustion efficiency measurement via tomographic absorption spectroscopy and particle image velocimetry

Busa, K. M., Rice, B. E., McDaniel, J. C., Goyne, C. P., Rockwell, R. D., Fulton, J. A., … Diskin, G. S. (2016), AIAA Journal, 54(8), 2463–2471. https://doi.org/10.2514/1.j054662

View all publications via NC State Libraries

Grants

Tailored Supersonic Flowfields

US Dept. of Defense (DOD)(12/12/19 - 9/12/20)

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Tailored Supersonic Flowfields

Sponsor: US Dept. of Defense (DOD)

Start Date: 12/12/19

End Date: 9/12/20

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 - 5/15/20)

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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: 5/15/20

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.

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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 - 6/30/20)

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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: 6/30/20

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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NCSU American Institute of Aeronautics and Astronautics Design Build Fly Senior Design Team Space Grant Proposal

NCSU NC Space Grant Consortium(11/30/17 - 8/31/18)

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NCSU American Institute of Aeronautics and Astronautics Design Build Fly Senior Design Team Space Grant Proposal

Sponsor: NCSU NC Space Grant Consortium

Start Date: 11/30/17

End Date: 8/31/18

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 is led by seniors completing their capstone projects and 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. For instance, in previous years, aircraft had to fit inside tubes, carry heavy payloads, and takeoff in less than ideal conditions such as a short or uneven takeoff surface. This year, the goal is to create a dual purpose regional and business aircraft.

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NCSU American Institute of Aeronautics and Astronautics Design Build Fly Space Grant Proposal

NCSU NC Space Grant Consortium(11/30/17 - 7/30/18)

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NCSU American Institute of Aeronautics and Astronautics Design Build Fly Space Grant Proposal

Sponsor: NCSU NC Space Grant Consortium

Start Date: 11/30/17

End Date: 7/30/18

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, the goal is to create a dual purpose regional and business aircraft.

Close

Modeling of Air, Surface, and Underwater burst Phenomena within Complex Environments after High Energy Explosion

Defense Agency of Technology and Quality (DTaQ)(7/05/17 - 5/31/20)

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Modeling of Air, Surface, and Underwater burst Phenomena within Complex Environments after High Energy Explosion

Sponsor: Defense Agency of Technology and Quality (DTaQ)

Start Date: 7/05/17

End Date: 5/31/20

Abstract

The proposed work is designed to develop a comprehensive prediction strategy for 3D blast wave propagation interacting with complex surface terrain. Air, surface, and underwater explosions will be modeled, as will water /air interfaces and shock diffraction from topologically-complex surfaces. NCSU’s activities will center on the development of a two-phase flow modeling strategy for compressible liquid /reactive gas mixtures that will be integrated into Yonsei University’s gas-dynamics code. Features will include sharp interface capturing and cavitation modeling. A second objective is to extend NCSU / Yonsei’s immersed boundary methodology to account for physics associated with blast-wave propagation through different media. This will enable prediction of blast-wave propagation through complex terrain that may include bodies of water, ground features, and buildings.

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Improved Numerical Simulations of Barbotage Atomization

Air Force Research Laboratory (AFRL)(10/15/16 - 11/12/18)

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Improved Numerical Simulations of Barbotage Atomization

Sponsor: Air Force Research Laboratory (AFRL)

Start Date: 10/15/16

End Date: 11/12/18

Abstract

This work will continue to develop new computational models for simulating 'barbotage' fuel injection. Results will be compared with experimental data collected by Taitech personnel at AFRL and at Argonne National Laboratories.

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Research Area 1, Section 1.4.1: Engines: Mesh-sequenced Realizations for Evaluation of Subgrid-Scale Models for Turbulent Combustion (Short Term Innovative Research Program)

US Army - Army Research Office(1/17/17 - 12/31/17)

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Research Area 1, Section 1.4.1: Engines: Mesh-sequenced Realizations for Evaluation of Subgrid-Scale Models for Turbulent Combustion (Short Term Innovative Research Program)

Sponsor: US Army - Army Research Office

Start Date: 1/17/17

End Date: 12/31/17

Abstract

This project will refine the concept of mesh-sequenced realizations as used to assess and improve subgrid-scale models for turbulent combustion. Particular attention will be paid to the closure of the filtered species production rates, which can be calculated at the molecular level using the law of mass action. New closure ideas based generally on 'least-squares modeling' concept will be assessed using modified a priori and enhanced a priori analyses, facilitated by simultaneous large-eddy simulations conducted on multiple mesh levels.

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