JACK R. EDWARDS
Professor

Education
Ph.D., Aerospace Engineering , North Carolina State University , 1993
M.S., Aerospace Engineering, North Carolina State University, 1990
B.S., Aerospace Engineering, North Carolina State University, 1988

Research Interests
CFD, 2D & 3D compressible flows, Thermo-chamical/nonequilibrium flow, Turbulence modeling

Professional Experience
Aug.,1994 -- present Assistant Professor North Carolina State University, Raleigh, NC

Mar.,1994 -- Aug.,1994 Research Scientist High Technology Corporation, Hampton, VA

Jan.,1993 -- Mar.,1994 Research Associate, NASA Center of Research Excellence, North Carolina ALT State University, Greensboro, NC

Professional Societies
Member: AIAA Propellants and Combustion Technical Committee (1997-1998)

Senior Member: American Institute of Aeronautics and Astronautics

Member: The Combustion Institute

Selected Publications
Xiao, X., Edwards, J.R., Hassan, H.A., and Baurle, R.A. “Inflow Boundary Conditions for Hybrid Large-Eddy / Reynolds-Averaged Navier-Stokes Simulations”  AIAA Journal, Vol. 41, No. 8, 2003, pp. 1481-1490.

Baurle, R.A., Tam, J., Edwards, J.R., and Hassan, H.A. “Hybrid RANS/LES Approach for Cavity Flows: Blending, Algorithm, and Boundary Treatment Issues” AIAA Journal, Vol. 41, No. 8, 2003, pp. 1463-1480.

Mao, D., Edwards, J.R., Kuznetsov, A.V., and Srivastava, R.K. “Development of Low-Diffusion Flux-Splitting Methods for Dense Gas-Solid Flows,”  Journal of Computational Physics,  Vol. 185, No. 1, 2003, pp. 100-119.

Mao, D., Edwards, J.R., Kuznetsov, A.V, and Srivastava, R.K. “Particle Flow, Mixing, and Chemical Reaction in Circulating Fluidized Bed Adsorbers,”  Chemical Engineering Science, Vol. 57, No. 4, 2002, pp. 3107-3117.

Mao, D., Edwards, J.R., Kuznetsov, A.V, and Srivastava, R.K. “A Model for Fine Particle Agglomeration in Circulating Fluidized Bed Adsorbers,”  Heat and Mass Transfer, Vol. 38, No. 4, 2002, pp. 379-388.

Navier-Stokes simulation of hydrogen fuel injection into a model scramjet inlet / isolator / combustor configuration.

The animations illustrated herein are taken from a recent Navier-Stokes simulation of hydrogen fuel injection into a model scramjet inlet / isolator / combustor configuration. The experimental configuration was tested in the Vitiated Air Generator (VAG) facility at the National Aerospace Laboratory, Japan. The simulations are part of an AFOSR-funded effort directed toward understanding dynamic modes of scramjet operation, as resulting from fuel flow rate modulation, attitude changes, and mode transition scenarios. The simulations correspond to fuel injection at an equivalence ratio of 0.61, which was shown experimentally to result in inlet unstart for the straight-walled combustor. The simulations also display a progression toward inlet unstart, initiated primarily by the growth of large recirculation regions along the combustor sidewall, which block the inviscid core fluid. As the pressure levels in the combustor increase, a shock wave emanating from the trailing edge of the combustor separates the boundary layer along the combustor sidewall. Hydrogen is entrained into this recirculation zone where it ignites, initiating a flashback effect that forces multiple pockets of hot, recirculating fluid upstream of the injector exit. The shock system is eventually disgorged from the inlet as a result of flow blockage.

The calculations were performed on the North Carolina Supercomputing Center's IBM SP2. The mesh contains upwards of 2 million grid nodes, with 15 equations solved per grid point (9 species / 24 reaction hydrogen oxidation mechanism). The animations themselves display temperature, OH mass fraction, and pressure contours, extracted (from front to back) at the X-Z centerplane, the quarter-span location, and a location near the sidewall of the combustor.

Animation 1 : OH radical concentration

Animation 2 : pressure

Animation 3 : temperature