NC State
Turbulent Shear Flow Laboratory

Development of Advanced Augmentor Ignition Modelling tools

The vision of this project is to help develop advanced ignition modelling tools for turbulent non-premixed and partially premixed fuel mixtures by using state of the art experimental tools. The core idea is to perform detailed experiments in a validation type experimental setup (see figure below of the jet in coflow burner) to provide high quality data for model development as well as physical insights into turbulence chemisty interactions that accompany a firing and misfiring kernel. Using a suite of high-speed flame luminosity and chemiluminescence imaging, PIV and PLIF measurements, comprehensive insights into the aerothermochemical interactions that occur at various stages of ignition kernel evolution. This project is done in collaboration with an industry partner who brings in novel modelling approaches that will help augment the predictive capabilities and experimental findings. The movie below is a 20 kHz imaging of plasma/flame kernel luminosity of a laser spark initiated ignition of a turbulent fuel/air mixture. The different phases of kernel evolution and the aerodynamic stretching effects during the evolution can be clearly discerned.



Students: Kevin Ley

1. Ley, K. and Narayanaswamy, V., “Parametric Study of Forced Ignition in Laminar and Turbulent Methane Jets”, AIAA 2017-4770, 2017

Shock wave boundary layer interactions during inlet unstart

Development of low/no bleed inlets hold the key to future hypersonic technology. Without bleed the inlets are highly prone unstart, which is the disgorging of shock train within the inlet/isolatorsection of the scramjet to cause massive loss in thrust and fatal accidents. The initiation and perpetuation of the unstart event and the resulting transient loads involve complex interactions between separated flow along the inlet floor and corners. Uncovering the interactions between primary separation and corner separation is the central theme of this project. We bring state of the art multidimensional flow field quantification tools coupled with wall pressure measurements in the separated flows to obtain a physical and statistical understanding of the interactions.


Students: Morgan Funderburk


  1. Funderburk, M., and Narayanaswamy, V., “Experimental Investigation of Primary and Corner Shock Boundary Layer Interactions at Mild Back Pressure Ratios,” Physics of Fluids, Vol. 28, 086102, 2016.