(YIP) NOVEL CONCEPTS FOR TRANSITION DELAY IN HYPERSONIC BOUNDARY LAYERS AND THEIR OPTIMIZATION
Abstract
Accurate prediction and control of boundary-layer transition (BLT) is a critical factor in the design of hypersonic vehicles because of the large increases in skin friction and heat transfer accompanying the process of BLT. The proposed study will investigate novel concepts for transition delay in hypersonic boundary layers via multifidelity computations that would combine stationary and unsteady solutions to Navier-Stokes equations, multidimensional instability analysis techniques, and physics-based transition modeling integrated into Reynolds-Averaged Navier-Stokes calculations. The proposed strategy will seek to attenuate the modal amplification of flow instabilities by modulating the boundary layer flow via wall-mounted vortex generators or other equivalent means of modifying the effective wall shape. This concept utilizes intrinsic flow characteristics to amplify the effects of relatively small control input via transient growth; is easy to implement; can be introduced either in standalone mode or in conjunction with other laminar flow devices such as 2D surface deformations or porous wall strategies to augment the overall laminar flow; and does not incur the penalties associated with suction based laminar flow control. Preliminary studies indicate the potential to reduce the Mack mode amplification by 1.5 to 2 orders with a resulting increase in laminar flow length by up to 50-100 percent. The proposed investigation will address the optimization of the transition control strategies to maximize the laminar flow benefit, improve robustness, and facilitate integration into the vehicle design – a crucial aspect of hypersonic vehicle design.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Aug 12, 2021
- Source ID
- FA95502010023
Entities
People
- Pedro Paredes Gonzalez
Organizations
- Air Force Office of Scientific Research
- National Institute of Aerospace
- United States Air Force