Simulation Study of VISTA/F-16 Maneuverability Enhancement Using Forebody Vortex Control.
Abstract
A piloted experimental study of potential enhanced task performance resulting from improved high angle-of-attack aerodynamic and flight control capability was conducted in the Air Force Research Laboratory's engineering flight simulator facility. The simulation database used was representative of the aerodynamics and inertias of the Variable-stability In-flight Simulator Test Aircraft (VISTA)/F-16. The VISTA variable-stability control laws were not used. Three flight test pilots evaluated both baseline and three modified versions of the simulated aircraft using a variety of high angle-of-attack tasks. Aerodynamic modifications were based on wind tunnel data from a previous effort which examined various means of extending the aircraft angle-of-attack limits. These focused primarily on the lateral-directional characteristics in the twenty-nine to thirty-seven degree range. Flight control modifications came from a new approach to control of lateral-directional dynamics which used variable structure control and describing functions. This controlled the forebody vortices to achieve improved roll coordination. This paper presents the results of analyzing the entire set of experimental output data for the effects of the configuration changes on high angle-of-attack maneuverability and departure resistance. The results show that use of the modifications greatly increases departure resistance and provides significant improvement in roll maneuverability for flight up to the maximum lift angle of attack.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 01, 1997
- Accession Number
- ADA327802
Entities
People
- Phillip D. Mckeehen
- Thomas J. Cord
Organizations
- Wright Laboratory