Date of Award

3-2021

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

Michael M. Walker, PhD

Abstract

Utilizing computational fluid dynamic (CFD) simulations, the presented study is able to further the investigation of replicating and improving upon the performance of a NACA 0012 cropped half-span delta-wing at high angles-of-attack with an active flow control fluidic fence via wall-normal, steady blowing from an optimized single chordwise slot located at z/b = 70%,. The data is generated using CREATE-AV Kestrel v10.1rc5 CFD software on the Department of Defense High Performance Computing systems. The flight regime is held constant at a Mach number of 0.18 and a Reynolds number (Re) of 5.0 x 105, based on the root chord. Computational solutions are successfully compared to previously obtained experimental wind tunnel results of three configurations; baseline, passive boundary-layer fence (BLF) and AFC slot of a single momentum coefficients (Cµ = 0.49%), to validate the CFD model prior to slot optimization. Optimization parameters include five reduced slot widths, five slot velocities and eight slot length. Performance parameters compared for validation and optimization are coefficients of lift, drag and pitching moment at angles-of-attack ranging from 0° to 30°. Surface flow visualization was produced via Tecplot 360 to evaluate unique AFC flow characteristics. AFC slot optimization successfully produce an overall dimension reduction and reduction in momentum input of 33% when compared to the experimental result’s highest Cµ = 12%. With these reductions, the optimal AFC slot configuration yielded a CLmax,%Gain = 41% at α = 22◦ compared to the baseline configuration. The optimal AFC slot configuration indicate no destabilizing pitching moment present. Visualization of the compared results show that the AFC slot allow for delay in vortex breakdown for some configurations which provide improved vortex generating lift across the wing surface at increasing angles-of-attack.

AFIT Designator

AFIT-ENY-MS-21-M-322

DTIC Accession Number

AD1139801

Download

Share

COinS