Publication:
MODELING FLOW OVER 3-D WING SPOILERS FOR MODEL B-52

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Authors
Palaski, Michael A.
Subjects
CFD
B-52
flow modeling
control surfaces
spoiler
Advisors
Jones, Kevin D.
Dobrokhodov, Vladimir N.
Date of Issue
2020-06
Date
Publisher
Monterey, CA; Naval Postgraduate School
Language
Abstract
Analyzation of flight vehicles using computational tools typically relies on a linear model of the aircraft control surfaces to calculate control derivatives and flight response. This information is used to inform the design of simulations and autopilot controls. However, some aircraft implement control surfaces are not well described by linear models, such as asymmetrically employed wing spoilers. This study aims to capture the non-linearity of wing spoilers for use on a 1/18th scale model B-52H through the use of the computational fluid dynamics software ANSYS/CFX. This study models the lift, drag, and moment responses of the wing spoilers at various spoiler angles and angles of attack. This study found that the response of the spoiler was linear from no deployment to half deployment, and beyond this point, the response was non-linear. Continuing research should be conducted to more accurately predict the exact transition point.
Type
Thesis
Description
Series/Report No
Department
Mechanical and Aerospace Engineering (MAE)
Other Units
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NPS Report Number
Sponsors
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Distribution Statement
Approved for public release. distribution is unlimited
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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