An Iterative Solution to Aeroelastic Effects in Potential Flow

Abstract

The purpose of the study was to develop a method of incorporating static aeroelastic effects into a vortex paneling aerodynamic solution. The study had two basic objectives: (1) Devise a solution technique; (2) Implement the technique and analyze several test cases. An iterative solution is developed which uses MSC/NASTRAN to perform structural analysis, and a three-dimensional vortex paneling method to perform aerodynamic analysis. The theory behind the method and details of the implementation are presented. The method is tested for three bodies: a unit aspect ratio rectangular flat plate wing, a rectangular flat plate wing with aspect ratio 6, and a hollow sphere. Results of these tests are used to evaluate both the general performance of the implementation, and the performance for the specific test. The results indicate that the iterative solution method is robust and could potentially be used for solving a variety of aeroelastic problems. Recommendations for further development, evaluation, and use are made. Keywords: Fortran; Theses. (AW)

Open PDF

Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1989
Accession Number
ADA216291

Entities

People

  • Raymond C. Maple

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeroelasticity
  • Air Force
  • Aircrafts
  • Aspect Ratio
  • Computer Simulations
  • Dynamic Pressure
  • Engineering
  • Engineers
  • Finite Element Analysis
  • Mach Number
  • Mechanical Engineering
  • Plastic Explosives
  • Pressure Distribution
  • Structural Analysis
  • Structural Components
  • Three Dimensional
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Computational Fluid Dynamics (CFD)
  • Fluid Dynamics.
  • Systems Analysis and Design