Experimental and Computational Investigation of the Close-Coupled Flow Field of Delta Wings and Vectoring Jets
Abstract
Leading edge vortices are routinely used for high-alpha lift augmentation. However, due to instabilities in the shear layer, these vortices are prone to breakdown of their organized structure, a phenomenon commonly referred to as vortex-burst. Asymmetric shedding and vortex burst has two detrimental effects, namely, loss of lift and un-commanded wing-roll. The flow field of these vortices has therefore been extensively documented for understanding the physics of the flow. This fluid dynamic phenomenon can have important implications when coupled with current propulsive configurations such as thrust vectoring. The use of thrust vectoring for increasing the agility of fighters has been successfully demonstrated in the recent years. However, limited research has been directed towards investigating the closed-coupled interaction of flow over delta wings at high angles of attack, and thrust vectoring configurations. In this 3-year project it is proposed to study the closed-coupled flow field of slender and non-sender delta wings with vectoring jets to understand the complex structure of the flow field. The study will be conducted in the 15in x 20in water tunnel and 2ft x 3ft wind tunnel facilities at the Aerospace Science Engineering Department, Tuskegee University. Mapping of the flow field will be accomplished using volumetric particle image velocimetry (VPIV) system, already available in the Department of Aerospace Science Engineering. The experimental study will be done in two phases. Phase-I will establish baseline qualitative flow field data for a roll-constrained and free-to-roll models with and without vectoring jets. Phase-II will conduct quantitative measurements using the VPIV system for the roll-constrained and free-to-roll models with and without jet vectoring. Flow fields of both slender and non-slender delta wings will be investigated. The various other parameters of the experimental study will include, vectoring jet angles, jet discharge coefficients and jet geometries. The experimental data will be analyzed using a variety of numerical techniques such as proper orthogonal diagonalization, dynamic mode decomposition and oscillating pattern decomposition methods to determine the dominant flow mechanisms. The line integral convolution technique will also be used to understand the vortical flow structures. Numerical techniques and computational procedures will also be developed for the experimental configurations. The computational effort will parallel the experimental phases and will use the flow boundary conditions of the experimental setup for code validation. Tuskegee University is the only HBCU with an ABET-accredited undergraduate Aerospace Engineering program. Over the years it has produced the largest number of African- American aerospace engineers in the United States. The project will significantly enhance the research capacity at Tuskegee University and will support the development of a multidisciplinary team of faculty from the Math and Aerospace Science Engineering Departments. The project will provide an excellent opportunity to undergraduate students to be involved with contemporary aspects of experimental and computational fluid dynamics. This research effort will also exemplify to them the increasingly integrative approach towards flight vehicle design and the use of modern experimental and computational techniques. The project will support two graduate students and partially support two undergraduate students. The research findings of the project will be disseminated through publications in professional journals and presentations at professional conferences.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Feb 14, 2019
- Source ID
- W911NF1810455
Entities
People
- Mohammad Wahiduzzaman Khan
Organizations
- Army Contracting Command
- Office of the Secretary of Defense
- Tuskegee University