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experimental investigations of a full model with adaptive elasto-flexible membrane wings

Chinese Journal of Aeronautics 2021年第7期34卷 211-218页

作者： Jonathan PFLU GER Christian BREITSAMTER Chair of aerodynamics and Fluid Mechanics Technical University of MunichGarching 85748Germany

The morphing wing concept aims to constantly adapt the aerodynamics to different flight *** wing is able to adapt to different flight conditions by an adjustable Aspect Ratio(AR)and sweep.A high AR configuration provides high aerodynamic efficiency,while a low AR configuration,with highly swept wings offers a good ***,the flexible membrane allows the wing surface to stretch and contract in-plane as well as the airfoil to adapt to different aerodynamic *** the context of this work,the aerodynamic characteristics of a full model with form-adaptive elasto-flexible membrane wings are investigated *** focus is on the high-lift regime and on the analysis of the aerodynamic coefficients as well as their ***,the lateral aerodynamic derivatives at asymmetric wing positions are of interest.

关键词： experimental aerodynamics Flexible wing surface Force and moment measurements Morphing wing Particle image velocimetry

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experimental STUDY OF HIGH SUBSONIC CAVITY FLOW OSCILLATION AND ITS SUPPRESSION BY ACOUSTIC EXCITATION

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Chinese Journal of Aeronautics 1998年第3期11卷 2-5页

作者：罗柏华胡章伟戴昌晖 Sch. of Power and Energy Engineering Shanghai Jiao Tong University Shanghai 200030 China Nanjing Univ. Aero. and Astronaut. Nanjing 210016 China

An experimental study of cavity oscillating flow carried out on subsonic wall jet facilities in an anechoic room is summarized. The jet exit Mach number range is from 0.2 to 0.8. The effects of the flow Mach number ( Ma ) and the cavity depth ( D ) on the oscillation are studied. It is found that for L/D =4, (shallow cavity), the oscillation is mainly due to the self exciting of the free shear layer above the cavity opening, for L/D =2, the acoustic resonance is responsible for the oscillation. Preliminary tests are performed to study the suppression effect of the leading edge tone excitation on cavity flow, and considerable reduction of oscillation has been achieved when Ma ≤0.6.

关键词： cavity flow experimental aerodynamics acoustic excitation

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experimental Investigation of the Aerodynamic Flow in the Aircraft Carrier Ski-jump by means of PIV

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Journal of Mathematics and System Science 2017年第12期7卷 353-362页

作者： R. Bardera M. Leon-Calero A. A. Rodriguez-Sevillano lnstituto Nacional de Tecnica Aeroespacial (INTA). Ctra. Ajalvir km 4.5. Torrejon de Ardoz 28850 Madrid Spain Instituto Nacional de Tecnica Aeroespacial (INTA). Ctra. Ajalvir km 4.5. Torrejon de Ardoz 28850 Madrid Spain Escuela Tecnica Superior de Ingenieria Aeronautica y del Espacio. Universidad Politecnica de Madrid (UPM). Plaza delCardenal Cisneros 28040 Madrid Spain

Computational Fluid Dynamics （CFD） methods have opened a new field to perform aerodynamic studies saving money and time. The difficulties presented by this method to calculate complex flow field problems imply that CFD validation is needed to provide correct results. experimental data have recently been used to validate the accuracy of CFD predictions. Particle Image Velocimetry （PIV） has shown to be a powerful tool in the investigation of complex flows. The aim of this paper is to present results from PIV experiments that would be interesting for CFD validation. Regarding aircraft operations, the short runway available implies the necessity of equipment which helps to take-off performances. Ski-jump ramp system improves aircraft performances by an increment of lift resulting in successful take-off operations. The ski-jump ramp presence generates a complex flow bounded by a turbulent shear layer and a low velocity recirculation bubble over the end of the flight deck. The adverse effects on the aircraft aerodynamics affect to pilot safe operations, so this region is an interesting problem to be studied by means of wind tunnel experimental tests.

关键词： experimental aerodynamics PIV CFD validation ski-jump ramp

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