Aircraft layout design employing high-precision methods of computational aerodynamics and optimization

Aeronautical and Space-Rocket Engineering

Aerodynamics and heat-exchange processes in flying vehicles


Аuthors

Anisimov K. S., Kazhan E. V., Kursakov I. A., Lysenkov A. V.*, Podaruev V. Y., Savel’ev A. A.

Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: aleksandr.lysenkov@tsagi.ru

Abstract

Nacelle shape and engine position optimization was performed for Blended Wing Body aircraft (BWB). Aerodynamic characteristic computing method, used in the optimization procedure, is based on numerical calculations of the Reynolds-averaged Navier-Stokes equations. The EWT-TsAGI software, used for the flow computation, is based on the finite volume method of the second approximation order for all variables and includes monotonic modified Godunov scheme. The engine is simulated by the “active disks” method. Computations were performed on multi­block structured meshes with hexahedral cells. The power plant was designed with account for the initial requirements to the aircraft formulated in the AGILE project.

The developed optimization procedure consists of the two steps. At the first step, the isolated nacelle for the high bypass ratio engine is being developed and optimized for the cruise regime. Geometry of axially symmetric nozzle is described by the 11 parameters Parametric geometry of the inlet is specified by 7 control geometric parameters: 6 parameters specify the axially symmetric inlet, and one parameter (incidence angle) is employed for the air intake 3D design. The engine effective thrust is an objective function of optimization at the specified engine flow-rate constrains. To find the optimum solution, the Efficient Global Optimization method, based of simulation models, is used. It was shown, that SEGOMOE optimization method decreases the number of computed geometries.

At the second step, installation angles and the engines position over the airframe are optimized. A total of nine parameters is varied. The objective function is the effective thrust of the total layout (thrust minus layout drag) with the specified lift force constraint. An automatic structural mesh rebuilding is realized for the effective optimization procedure. The EGO based optimization algorithms require the initial points set calculating for the simulation model creation. It is shown, employing the large set of initial points (DOE) is more effective for the optimization process parallelization. Aerodynamic characteristics of the final layout with optimally installed engines were calculated. The main source of aerodynamic losses for the obtained configuration at the cruise flight’s Mach number of 0.85 is the compression shocks occurring due to the interference of the airframe with engine nacelle and between the neighboring engine nacelles. The subsequent studies should pay special attention to the aerodynamic interaction of the airframe and engine nacelles.

The described procedure was performed in the context of the third generation multidisciplinary optimization techniques, developed within the AGILE project. During the project, the new technologies were implemented for the novel aircraft configurations, selected as test cases for the AGILE technologies application.

Keywords:

aircraft design, computational aerodynamics, optimization, power plant, engine nacelle

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