Accession Number : ADA294782
Title : Unsteady Aerodynamics - Work Unit 2300-FF-07.
Descriptive Note : Final rept. Oct 91-Sep 95,
Corporate Author : FRANK J SEILER RESEARCH LAB UNITED STATES AIR FORCE ACADEMY CO
Personal Author(s) : Stephen, Eric J.
PDF Url : ADA294782
Report Date : SEP 1995
Pagination or Media Count : 113
Abstract : This task addressed basic research to better understand unsteady, separated flows and to utilize this understanding to develop innovative concepts to control unsteady aerodynamic phenomena to enhance flight vehicle maneuverability. This effort sought to expand the flight performance boundaries by developing a capability to maneuver in the high-angle-of-attack, post-stall flight regime. The research was organized around two broad topical areas: (1) understanding and predicting the dynamics of unsteady, separated flows and (2) controlling unsteady, separated flows to enhance aerodynamic performance. Several types of flow fields were studied to gain an understanding of unsteady, separated flows. These included flow over rectangular wings, flow over delta wing, flow over forebodies and flow in the vicinity of the tail on a fighter type aircraft. The studies were both computational and experimental. Control efforts focused on the pulsed blowing to maintain attached flow, continuous blowing to control vortex breakdown on delta wing, and the use of neural networks to predict and control unsteady aerodynamic forces. (AN - analyst's abstract; delete this message when done)
Descriptors : *AERODYNAMIC FORCES, *UNSTEADY FLOW, *WING BODY CONFIGURATIONS, COMPUTERIZED SIMULATION, FIGHTER AIRCRAFT, EXPERIMENTAL DATA, NEURAL NETS, PITCH(MOTION), AERODYNAMIC STABILITY, COMPARISON, BOUNDARY LAYER, VORTICES, COMPUTATIONAL FLUID DYNAMICS, ANGLE OF ATTACK, FLOW VISUALIZATION, FLOW FIELDS, STALLING, WAKE, FLIGHT ENVELOPE, TWO DIMENSIONAL FLOW, FLIGHT MANEUVERS, NAVIER STOKES EQUATIONS, FLOW SEPARATION, DELTA WINGS, PRESSURE DISTRIBUTION, GAS SURFACE INTERACTIONS, THREE DIMENSIONAL FLOW, TAILS(AIRCRAFT).
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE