APPLICATION OF THE NASA KERNEL-FUNCTION PROCEDURES TO GENERALLY DEFORMING WINGS

Abstract

A method is described for obtaining generalized aerodynamic forces by utilizing the NASA KernelFunction Procedures. An evaluation of the generalized aerodynamic forces and the consequent flutter conditions is made for the particular case of a uniform, cantilevered, 70 degree delta wing. The supersonic Kernel-Function Procedure was found to be inadequate for treating the elastic modes on this low-aspect-ratio wing; the subsonic procedure, however, appears to work satisfactorily. The theoretical flutter predictions are compared with the experimental results of NASA Report TM X-53 (AD-222 902). The Kernel-Function predictions for quasi-steady flow (k approaches O) appear to be superior to those for the complete unsteady case k = omega sub fc sub r/2V sub f. Based on this limited comparison, it appears that for this low-aspect-ratio wing the large transient effects predicted by linearized theory in the transonic regime may not actually exist. (Author)

Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1962
Accession Number
AD0289882

Entities

Organizations

  • Aerojet Rocketdyne Holdings

Tags

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aspect Ratio
  • Delta Wings
  • Flow
  • Kernel Functions
  • Steady Flow
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Computational Modeling and Simulation
  • Fluid Mechanics and Fluid Dynamics.
  • Structural Dynamics.

Technology Areas

  • Hypersonics