Unsteady Viscous Transonic Flow Computations Using the LTRAN2-NLR Code Coupled with Green's Lag-Entrainment Method,

Abstract

Results of unsteady inviscid and viscous transonic flow computations are presented and compared with experimental data for the NACA64A3006 airfoil with oscillating in pitch. The computations were performed using the NLR version of the NASA-Ames computer code LTRAN2, coupled with the lag-entrainment method of Green for a turbulent boundary layer. The computed effect of the boundary layer on the unsteady airloads (reduction of the magnitude and a positive phase shift) generally leads to a better agreement with experimental data. The remaining differences may be due to the low frequency small perturbation potential approximation, the weak interaction modelling and wall interference effects.

Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1982
Accession Number
ADP001945

Entities

People

  • R. Houwink

Organizations

  • National Aerospace Laboratory

Tags

DTIC Thesaurus Topics

  • Agreements
  • Boundaries
  • Boundary Layer
  • California
  • Computations
  • Computers
  • Entrainment
  • Experimental Data
  • Flow
  • Frequency
  • Layers
  • Phase Shift
  • Transonic Flow
  • Turbulent Boundary Layer

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Dynamics.
  • Fluid Mechanics and Fluid Dynamics.