Closed-Loop Control Systems for Unsteady Forebodies and Three-Dimensional Pitching Airfoils at High Reynolds Number.
Abstract
Progress made on closed loop control systems with application to aircraft forebodies and pitching airfoils is described in this report. The three main areas of the investigation included: (1) development of suitable control law algorithms for control of pitching wings and forebodies, (2) vorticity control on three-dimensional swept wings at high angles of attack, and (3) vortex control on forebody models at high angles of attack with unsteady motions. The three areas were investigated in parallel by laboratory experiment and numerical simulations. The numerical simulations examined the ability of distributed suction to control the flow over an airfoil undergoing a pitch-up motion and sinusoidal oscillation. Experiments on the feasibility of controlling dynamic stall using leading-edge suction were conducted. By studying the influence of different parameters such as pitch rate, Reynolds number, suction timing, suction slot size and location, a scaling law for the suction flow rate was developed. The third area of. investigation involved closed-loop control of forebody flow vortex asymmetry. By incorporating a closed- loop system, the desired side force could be maintained under a variety of different pitching. The relative performance of linear, nonlinear and neural network control algorithms was explored.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1995
- Accession Number
- ADA305405
Entities
People
- A. F. D'souza
- David R. Williams
- Mukund Acharya
Organizations
- Illinois Institute of Technology