Development of a Panel Method for Modeling Configurations with Unsteady Component Motions. Phase 1

Abstract

This report reviews the background to the calculation of unsteady rotor and fuselage loads and presents results from an analysis of a typical helicopter configuration made using a panel method operated in a time-stepping mode. The method models the fuselage and blades using surface singularities and the shed and trailing wakes with doublet lattice sheets. Unsteady local pressures and component forces are presented and the ability of the analysis to determine dynamic phenomena such as fuselage/blade-passage events and blade/ vortex interactions is demonstrated.

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Document Details

Document Type
Technical Report
Publication Date
Apr 15, 1988
Accession Number
ADA200255

Entities

People

  • Brian Maskew
  • David R. Clark

Tags

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Boundary Layer
  • Computational Fluid Dynamics
  • Computations
  • Flow
  • Flow Fields
  • Flow Visualization
  • Fuselages
  • Helicopters
  • Leading Edges
  • Lifting Surfaces
  • Pressure Distribution
  • Shape
  • Vehicles
  • Viscous Flow
  • Wake

Fields of Study

  • Physics

Readers

  • Aerodynamics.
  • Business Analytics
  • Finite Element Method (FEM) for solving Partial Differential Equations (PDEs)