Flow Control for Improved Tailless Vehicle Aerodynamics During Takeoff and Landing via LE Vortex Manipulation
Abstract
A detailed experimental fundamental research is proposed, aiming at understanding, characterizingand controlling the physical mechanisms that lead to the formation of leading-edge (LE) vorticeson a chined forebody/wing configuration. The objective of the proposed project is to explore waysto control the onset, formation, and development of the leading edge-type vortices on a highlyswept chined-forebody. This will significantly reduce the nose-up pitching moment contributionat moderate to high angles of attack during takeoff and landing, as well as lateral control in theseflight regimes. An overall design solution would simultaneously consider the forebody, strake,wing, and control surfaces. The ability of small inputs to manipulate the vortices on a forebody ofrevolution is well established. The question of interest here is: can something similar be done forchined forebodies in longitudinal and lateral control? It is proposed to explore 3 flow controlactuators. These actuators include: (i) momentum/vorticity addition using distributed finite spansynthetic jets, (ii) distributed dynamic surface modification via low aspect ratio static or dynamiccircular pins, and (iii) hybrid actuation using a combined dynamic surface modification and jets,such as the Jet Assisted Surface Modification Actuator (JASMA). From the proposed experiments,it should be possible to: (1) quantify the baseline flow field at a range of angles of attack withoutside slip angle, (2) explore the effect of side slip angle on the formation of 3-D vortical structures,and (3) determine, based on (1) and (2), where should actuators be placed, and what should be thespacing between them such that flow control will be most effective. Further, the flow controlmethodologies proposed herein will lead to the alteration of integral aerodynamic quantitiesinfluenced by the appearance and breakdown of these structures. From an applied point of view,the proposed research is directly relevant to future naval applications by improving theperformance of tailless vehicle aerodynamics during takeoff and landing via LE vortexmanipulation, especially for aircraft carriers.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- May 08, 2020
- Source ID
- N000142012388
Entities
People
- Michael Amitay
Organizations
- Office of Naval Research
- Rensselaer Polytechnic Institute
- United States Navy