Aerodynamic compatibility of aircraft/inlet/engine systems is a difficult design problem for aircraft that must operate in many different flight regimes. Takeoff, subsonic cruise, supersonic cruise, transonic maneuvering, and high altitude loiter each place different constraints on inlet design. Vortex generators, small wing like sections mounted on the inside surfaces of the inlet duct, are used to control flow separation and engine face distortion. The design of vortex generator installations in an inlet is defined as a problem addressable by numerical optimization techniques. A performance parameter is suggested to account for both inlet distortion and total pressure loss at a series of design flight conditions. The resulting optimization problem is difficult since some of the design parameters take on integer values. If numerical procedures could be used to reduce multimillion dollar development test programs to a small set of verification tests, numerical optimization could have a significant impact on both cost and elapsed time to design new aircraft.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Vortex generator design for aircraft inlet distortion as a numerical optimization problem


    Contributors:


    Publication date :

    1991-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Design of Aircraft Engine Inlet Radial Distortion Generator

    Fang, Boyang / Qiang, Xiaoqing | British Library Conference Proceedings | 2023


    The Aircraft Engine Inlet Vortex Problem

    Johns, Christopher | AIAA | 2002