DOI: 10.11648/j.ajae.20261201.12 ISSN: 2376-4821

Development of Algorithms and Computer Codes for the Aerodynamic Configurational Design

Satish Gupta
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Several algorithms and computer codes are developed for the configurational aerodynamic design. Mathematical background, physics involved and their applications are brought out. These range from subsonic to supersonic, including transonic Mach number. Vortex lattice method is applied for handling subsonic and supersonic flow conditions under the linearised flow regime. Finite difference methodology is applied for transonic flow nonlinearities. Matrix of optimization is formed through principles of calculus of variations. The codes developed provide capabilities for inverse design for given loading, aerodynamic drag reduction, high lift to drag designs, generation of morphed profiles, wing optimization in the presence of canard, control surfaces sizing, design of reflex camber wings, and effect of ground proximity on flare manoeuvre, Analysis and Design is made over larger domain of flow field. Details on Camber morphing of wings are elaborated. Camber-morphing aerofoils aim to achieve their camber changes in a smooth way to potentially reduce the drag penalty. Morphing is possible by applying optimisation while restraining variation in camber in certain portions of the wing. A matrix for morphing is developed and scheme so developed is applied herein. Morphing as a concept is also applied to optimise wing for minimum induced drag in the presence of canard, where the slopes of canard camber are made to remain invariant to changes. As the aircraft comes close to ground during landing, runway interferes with aircraft flow field. Some aspects of interference effects of solid boundary wall are established. The influence of wall boundaries on the wing is estimated. Wing is placed at different heights above a horizontal solid surface plane, and an equal opposite vortex system is placed at depth equal to height below this surface. Codes developed find a useful application for design of aircraft for several aspects.

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