Boundary-Layer Transition for High Speed, Hypersonic Flight
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
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.
