Title

Boundary-Layer Transition for High Speed, Hypersonic Flight

Presenter Information

Thomas Knight

Department

Mechanical and Aerospace Engineering

Major

Aerospace Engineering

Research Advisor

Duan, Lian, 1983-

Advisor's Department

Mechanical and Aerospace Engineering

Funding Source

Joint USAF & NASA Research Grant; OURE Supplies Stipend

Abstract

This project is based on Dr. Duan’s proposal, titled “Numerical Simulation of Freestream Acoustic Disturbances in Hypersonic Ground Facilities and Their Effect on Boundary Layer Transition”.

Our research involves the effects of ‘noise’ created by the tunnel environment when subjected to hypersonic flow testing. This acoustic interference inhibits accurate prediction of boundary layer transition in the wind tunnel. Prediction of boundary-layer transition is a critical part of hypersonic vehicle design because of the large increase in surface heating associated with the transition during flight. Working closely with NASA and USAF supercomputers, Dr. Duan’s team conducts large scale simulations of noise at the tunnel wall in order to gain further understanding and develop prediction algorithms for future wind tunnel testing and design. Advances in the prediction of wind tunnel noise will allow for the development of lighter, more aerodynamically efficient thermal protection systems for hypersonic vehicles.

Biography

Thomas Knight is a junior in the Aerospace Engineering Department at Missouri S&T, he has recently begun an undergraduate research position under the direction of Dr. Lian Duan. His work in the acoustic disturbance analysis for hypersonic flight involves constructing three dimensional visual simulations of transition in the laminar to turbulent flow transition. In addition to his undergraduate research he is the president of the S&T chapter of AIAA (American Institute of Aeronautics and Astronautics) and a member of S&T’s unmanned mobile systems interest group.

Research Category

Engineering

Presentation Type

Poster Presentation

Document Type

Poster

Location

Upper Atrium/Hall

Presentation Date

15 Apr 2015, 1:00 pm - 3:00 pm

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Apr 15th, 1:00 PM Apr 15th, 3:00 PM

Boundary-Layer Transition for High Speed, Hypersonic Flight

Upper Atrium/Hall

This project is based on Dr. Duan’s proposal, titled “Numerical Simulation of Freestream Acoustic Disturbances in Hypersonic Ground Facilities and Their Effect on Boundary Layer Transition”.

Our research involves the effects of ‘noise’ created by the tunnel environment when subjected to hypersonic flow testing. This acoustic interference inhibits accurate prediction of boundary layer transition in the wind tunnel. Prediction of boundary-layer transition is a critical part of hypersonic vehicle design because of the large increase in surface heating associated with the transition during flight. Working closely with NASA and USAF supercomputers, Dr. Duan’s team conducts large scale simulations of noise at the tunnel wall in order to gain further understanding and develop prediction algorithms for future wind tunnel testing and design. Advances in the prediction of wind tunnel noise will allow for the development of lighter, more aerodynamically efficient thermal protection systems for hypersonic vehicles.