Accession Number : ADA310244

Title :   Thrust-Induced Effects on a Pitching-Up Delta Wing Flow Field.

Descriptive Note : Final rept. 1 Oct 92-30 Sep 95,

Corporate Author : FLORIDA AGRICULTURAL AND MECHANICAL UNIV TALLAHASSEE

Personal Author(s) : Lourenco, L. ; Shih, C. ; Van Dommelen, L. ; Krothapaili, A.

PDF Url : ADA310244

Report Date : 23 MAY 1996

Pagination or Media Count : 41

Abstract : Experimental study of thrust-induced effects on a pitching-up 60 deg. delta wing was conducted. A downward vectored trailing edge jet has a significant effect in delaying the vortex breakdown. Strong asymmetric vortex bursting can be induced using asymmetric jet control. Detailed PIV measurements are taken to characterize the vortex flow field with and without jet control. A parallel experiment of the vortex flow over a 75 deg. delta wing is made to further the understanding of th vortex breakdown phenomenon. Related investigations of dynamic stall phenomena over a pitching airfoil are also summarized. Concurrently, considerable efforts have been made in the development of an innovative computational scheme. A grid-free vortex distribution technique is introduced to simulate the diffusion process of a vortex-dominated flow. This allows the readily extension of the 2-D vortex method to be used in a 3-D flow field such as a pitching-up delta wing configuration. Several computational examples will be discussed.

Descriptors :   *PITCH(MOTION), *FLOW FIELDS, *DELTA WINGS, COMPUTATIONS, DYNAMICS, VORTICES, AIRFOILS, STALLING, ASYMMETRY, DIFFUSION, PARALLEL ORIENTATION.

Subject Categories : Aerodynamics
      Aircraft

Distribution Statement : APPROVED FOR PUBLIC RELEASE