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Optimized design of the inlet and calculated the UAV inside and outside the flow field coupling

Author: ZhengYong
Tutor: YangQingZhen
School: Northwestern Polytechnical University
Course: Engineering Thermophysics
Keywords: Inlet Flow Field N-S equation Nonlinear optimization Finite volume method Complex algorithms High Altitude Long Endurance UAV Flying wing Coupled flow field calculation
CLC: V211.4
Type: Master's thesis
Year: 2006
Downloads: 353
Quote: 1
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Abstract


Modern aircraft such as fighter aircraft , cruise missiles and other demands on the engine is getting higher and higher , and the inlet has a great impact on the engine , therefore , reasonably designed inlet, to improve the overall performance of the engine is of practical significance . This article attempts to design aerodynamic optimization design method Inlet . First in mesh generation , to quickly generate computational grid , using algebraic method to generate a three-dimensional structure of the grid ; then the calculation of the flow field , using the finite volume method to solve the Navier-Stokes equations , turbulence model of Baldwin-Lomax algebraic model ; optimization algorithm using a direct search for solving nonlinear optimization algorithms - complex method ; model for the optimization process is easy to control , using parametric spline curves to construct the model part of the line of control ; constructed set of inlet aerodynamic optimization of the design process . Set to optimize the design process optimized S-shaped inlet rectangular imports than the initial inlet greatly improved by optimizing the inlet performance calculated . UAV aircraft research has become a new hot spot for the strategic considerations of high-altitude long endurance UAV is attracting much attention . As another part of this paper, the research projects using commercial CFD software FLUENT flying wing of a certain type of high - altitude , long-endurance unmanned aerial vehicle flow around the flow field . First, the in vitro fusion of design changes before and after the wing and wing-body flow field is calculated , compare the lift coefficient , drag coefficient and torque coefficient characteristic curve changes , thus proving the overall aerodynamic performance of the modified wing has been greatly improved. Second , the combination of wing-body fusion and inlet coupled analysis of the flow field inside and outside of the flying wing and Inlet , analysis and comparison of the interaction between the two . The results show that an increase of the inlet , the fusion of the upper and lower surface pressure distribution more uniform , improved lift characteristics , moments, certain changes .

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CLC: > Aviation, aerospace > Aviation > Basic theory and experiments > Aerodynamics > Aircraft aerodynamics
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