Modeling Flow Over 3-D Wing Spoilers for Model B-52

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.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 2020
Accession Number
AD1114692

Entities

People

  • Michael A. Palaski

Organizations

  • Naval Postgraduate School

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aerodynamic Characteristics
  • Air Force
  • Aircrafts
  • Airframes
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computer-Aided Design
  • Control Surfaces
  • Dynamic Pressure
  • Dynamics
  • Fluid Dynamics
  • Fluid Flow
  • Geometry
  • Models
  • Scale Models
  • Schools
  • Simulations
  • Software Prototyping
  • Spoilers
  • Stagnation Point
  • Three Dimensional
  • Turbulent Flow
  • Two Dimensional
  • United States
  • Unmanned Aerial Vehicles

Readers

  • Aerospace Engineering
  • Computational Fluid Dynamics (CFD)
  • Control Systems Engineering.