Development and Validation of a Fluidic Sweep Diverter
Abstract
The purpose of this action is to add FY23 funds in the amount of $650K for a new start Grant award. GRANT13782353. The TAV is $1,317,329.00.--The boundary layer characteristics in the captured streamtube upstream of the engine inlet of a modern military aircraft can dramatically affect the pressure recovery, distortion, and stability of the inlet system flow over a wide range of flight speeds. The utility of a variety of passive and active boundary layer control approaches that have been developed over the years for addressing these inlet performance challenges has been limited by integration and operation challenges. A novel approach for active, efficient boundary layer control termed the Fluidic Sweep Diverter (FSD) that was recently conceived at Northrop Grumman has the potential to overcome limitations of earlier approaches. The proposed FSD methodology is based on a #virtual# diverter, generated fluidically, byforming two primary single-sign surface-bounded streamwise vortices using arrays of pitched and yawed surface actuation jets that divert low momentum boundary layer fluid over the surface transversely to thefree stream. Significant advantages of the FSD system over earlier approaches include low-weight, surface shape conformity and minimal drag penalty, and lower actuation mass flow rate. The proposed 2-year joint experimental and numerical investigations by the Georgia Institutes of Technology (GT) and Northrop GrummanAeronautics Systems (NGAS) will focus on exploring the fundamental aspects of implementing NGAS# novel FSD boundary layer control approach in inlet systems of future Navy aircraft. The development of this novel approach which overcomes several limitations of theearlier methods will be rooted in NGAS# experience and understanding of the characteristics boundary layer-ingesting propulsion systems flows and will build on earlier investigations at GT that demonstrated hybrid active/passive flow control technologies for mitigating the resulting total pressure distortions. The proposed investigations will develop and test reconfigurable flow control testbed modules whose characterization in a canonical turbulent boundary layer at GT#s Woodruff Wind Tunnel will help establish extensive predictive numerical simulations tools of the FSD performance using NGC/NGAS HPC clusters in Q1-Q6. The joint, interactive experimental and numerical investigations will illustrate the interactions of single and multi-jet actuators with the boundary layer flowand the formation and evolution of a streamwise streamwise vortex clusters with emphasis on spatial distributions of jets having different yaw, pitch, and momentum. These investigations will culminate in larger-scale higher speed validation tests in NGAS# 7# ยด 10# Low Speed Wind Tunnel (LSWT). It is anticipated that along with fundamental insight into flow physics and utility of FSD boundary layer control technology, the proposed work will provide validated, high-fidelity numerical tools that will enable the developmentof design guidelines for implementation of this new, efficient AFC technology on future Navy flight platforms and improve their airframe/propulsion integration. The GT/NGAS partnership brings to bear broad research experience in applications of AFC in Navy-relevant inlet systems and will help support transition paths of the new technology with lower risk and research cost. Approved for Public Release.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Jun 29, 2023
- Source ID
- N000142312500
Entities
People
- Ari Glezer
Organizations
- Georgia Tech Research Corporation
- Office of Naval Research
- United States Navy