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  • Model Deformation Measurement » Aircraft Research Association
    Store Separation Stability and Control Intake Performance Installed Store Loads Isolated Store Loads Data Quality and Repeatability Productivity Customer Facilities Other Test Facilities Balance Calibration Laboratory Mach Simulation Tank Propeller Test Cell Small Scale Transonic Tunnel 2 Dimensional Tunnel Large Scale Thrust Measuring Rig New Page tr Tasarım ve İmalat CAD Design Services Precision Model Manufacture Inspection Services Finite Element Analysis Strain Gauge Balance Design and Manufacture Hesaplamalı Akışkanlar Dinamiği CFD Software Code Development CFD Software Code Application Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research İnovasyon ve Teknoloji Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page tr Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page tr New Page tr New Page tr New Page tr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Model Deformation Measurement Aircraft Research Association Hizmetler İnovasyon ve Teknoloji Model Deformation Measurement It is very important to know the shape of the model during a test in the wind tunnel for the following reasons To ensure that the model is accurately representing the full scale aircraft To make sure that the geometry

    Original URL path: http://www.ara.co.uk/tr/hizmetler/inovasyon-ve-teknoloji/model-deformation-measurement/ (2016-02-17)
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  • New Page-tr » Aircraft Research Association
    Page tr Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page tr New Page tr New Page tr New Page tr Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact New Page tr Aircraft Research Association Hizmetler İnovasyon ve Teknoloji New Page tr What is DiPaRT The Airbus Flight Physics Distributed Partnership in R T DiPaRT was created in 2010 by Airbus UK as a mechanism for communicating with engaging and orchestrating the diverse UK Flight Physics R T community DiPaRT is creating a coherent well informed and motivated partnership that acts as a facilitator between Airbus and the UK Flight Physics community encouraging them to engage in more effective ways and supporting the UK centred capability in design and integration of wings landing gear and associated systems The DiPaRT UK network of organisations and partners identify potential technologies and deliver research aligned with Airbus s R T strategy Working through key partners such as Airbus Group Innovations AGI and ARA the Hub Leaders Airbus ensures the requisite time and effort is invested in fostering and operating DiPaRT Hub Leaders engage and coordinate between Airbus UK and the UK R T community Engagement in DiPaRT provides transparency of Airbus UK s strategic aspirations in Flight Physics R T to the UK R T community as well as giving the opportunity to shape and influence future directions DiPaRT also provides a gateway for joining the Airbus R T supply chain in the UK as well as a means to demonstrate the collaboration and impact value of research proposals which are of growing importance to funding agencies Further to this Airbus provides support to R T activities at a number of levels ranging from letters of support through to project funding DiPaRT key objectives Providing transparency

    Original URL path: http://www.ara.co.uk/tr/hizmetler/inovasyon-ve-teknoloji/new-page-tr/ (2016-02-17)
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  • Civil Aircraft » Aircraft Research Association
    Facilities Other Test Facilities Balance Calibration Laboratory Mach Simulation Tank Propeller Test Cell Small Scale Transonic Tunnel 2 Dimensional Tunnel Large Scale Thrust Measuring Rig New Page zh 设计与制造 CAD Design Services Precision Model Manufacture Inspection Services Finite Element Analysis Strain Gauge Balance Design and Manufacture 计算流体动力学 CFD Software Code Development CFD Software Code Application Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research 创新与技术 Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page zh Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page zh New Page zh New Page zh New Page zh Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Civil Aircraft Aircraft Research Association 服务 实验空气动力学 Transonic Wind Tunnel Testing Civil Aircraft Over the last 50 years ARA has continually evolved to maintain its reputation for providing the benchmark for the accurate and efficient production of high accuracy aerodynamic data required to support development programs ARA has been involved in the development of every major European civil transport aircraft including Concorde as well as a number from the Americas and the Far East Our customers have placed

    Original URL path: http://www.ara.co.uk/zh/services/page-11/transonic-wind-tunnel-testing/civil-aircraft/ (2016-02-17)
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  • Drag Performance » Aircraft Research Association
    Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research 创新与技术 Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page zh Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page zh New Page zh New Page zh New Page zh Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Drag Performance Aircraft Research Association 服务 实验空气动力学 Transonic Wind Tunnel Testing Civil Aircraft Drag Performance The increasing demand for improved fuel economy along with evermore stringent environmental constraints has resulted in a renewed effort by commercial aircraft manufacturers to design increasingly efficient aircraft through the reduction of drag Why ARA ARA has considerable experience in the accurate measurement of drag on a range of civil aircraft As a company we utilise highly accurate instrumentation such as thermally insensitive strain gauge balances for the measurement of overall model loads and inclinonometers for the measurement of the model s attitude to the airflow These measurements are augmented by base pressure measurements from within the model cavity Transition fixation is achieved through the use of strategically located surface roughness in the form of ballotini or discrete transition dots A number of visualisation techniques are available to aid in the understanding of the flow physics and therefore aid in the design for minimised drag Pressure Interpolation Oil Flows Pressure Sensitive Paint A Typical Test During the wind tunnel test a number of aerodynamic configurations and components are tested in order to determine their effect on the overall model drag through a range of model incidence s roll angles and Mach numbers Drag is calculated from the aerodynamic loads on the model measured by the internal strain gauge balance The base pressure measurement is utilised to correct the

    Original URL path: http://www.ara.co.uk/zh/services/page-11/transonic-wind-tunnel-testing/civil-aircraft/drag-performance/ (2016-02-17)
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  • Stability and Control » Aircraft Research Association
    CAD Design Services Precision Model Manufacture Inspection Services Finite Element Analysis Strain Gauge Balance Design and Manufacture 计算流体动力学 CFD Software Code Development CFD Software Code Application Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research 创新与技术 Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page zh Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page zh New Page zh New Page zh New Page zh Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Stability and Control Aircraft Research Association 服务 实验空气动力学 Transonic Wind Tunnel Testing Civil Aircraft Stability and Control A typical civil aircraft is kept stable by a horizontal tail and a vertical fin The aircraft is controlled in roll by ailerons on the wings in pitch by an elevator on the horizontal tail plane and in yaw by a rudder on the vertical fin It is critical to the safety of the aircraft that the control surfaces perform their function throughout the operational envelope at all speeds and attitudes A Typical Test Wind tunnel tests enable aircraft designers to check how an aircraft model performs both within and beyond its operational envelope in a safe and controlled environment A typical test may involve the design and manufacture of control surfaces such as spoilers or ailerons larger items such as engine nacelles and pylons or the complete aircraft model followed by a wind tunnel test The aerodynamic loads on individual components can be measured by attaching each component to the parent aircraft with a purpose built balance there can be up to 19 balanced components in addition to the main balance which measures the loads on that component The model loads are tested to the C L MAX and

    Original URL path: http://www.ara.co.uk/zh/services/page-11/transonic-wind-tunnel-testing/civil-aircraft/stability-and-control/ (2016-02-17)
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  • Rear Fuselage Performance » Aircraft Research Association
    zh New Page zh New Page zh New Page zh Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Rear Fuselage Performance Aircraft Research Association 服务 实验空气动力学 Transonic Wind Tunnel Testing Civil Aircraft Rear Fuselage Performance The nature of the airflow over the rear fuselage and empennage the horizontal and vertical tail surfaces of a civil aircraft is fundamental to the effective operation of the tail control surfaces and has a significant affect on overall aerodynamic efficiency It is difficult to predict the airflow of the rear fuselage without using wind tunnels due to complexity Why ARA Two alternative twin sting support designs are available at ARA the Standard Twin Sting Rig STSR and the Enhanced Twin Sting Rig ETSR The STSR is the original twin sting support system and is extensively used for the measurement of empennage characteristics because it is free from central sting interference Together with panel loads on the horizontal tailplane vertical stabilisers rudders and elevators for models which can be easily split both aerodynamically and mechanically the empennage can be mounted on an internal balance The STSR booms incorporate balances to enable some of the overall forces or moments acting on the model to be monitored for safety However for close coupled aircraft layouts such as many modern executive jets which incorporate engines mounted to the rear fuselage aft of the wings there is strong mutual aerodynamic interaction between the complex fuselage shape wing nacelles empennage and central support sting and therefore the model fuselage can be neither aerodynamically or mechanically split in a sensible fashion for testing on the STSR For these cases ARA developed an Enhanced Twin Sting Rig which can measure the aerodynamic characteristics of different rear fuselage designs empennages and rear fuselage nacelle installations together with the determination of central sting corrections The basic concept of the ETSR is that the foces and moments acting on the whole model are accurately measured by two six component balances one mounted in each of the twin stings To ensure the highest possible data quality the whole model or ETSR system is calibrated as an assembly prior to testing in the TWT Uniquely both of our support systems can move in yaw as well as in pitch which enables both lateral and longitudinal stability and control to be investigated during a test In addition the horizontal separation of the support booms can be adjusted to our customer s specification A Typical Test When testing rear fuselage performance models are supported via the wings with a twin sting arrangement rather than via a central single sting This is because a twin sting allows for a more representative fuselage shape to be modelled The focus of the test is on the performance of the rear of the aircraft meaning that the support booms have no influence During a typical test the aerodynamic loads on the rear fuselage can be measured by creating a small gap between the rear fuselage and the rest of the model

    Original URL path: http://www.ara.co.uk/zh/services/page-11/transonic-wind-tunnel-testing/civil-aircraft/rear-fuselage-performance/ (2016-02-17)
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  • Installed Propulsion Performance » Aircraft Research Association
    New Page zh New Page zh New Page zh New Page zh Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Installed Propulsion Performance Aircraft Research Association 服务 实验空气动力学 Transonic Wind Tunnel Testing Civil Aircraft Installed Propulsion Performance A typical civil aircraft is most often propelled by propeller engines or jet engines More advanced engines such as open rotors jet engines with fan blades on the outside are under active development Whatever means the aircraft uses to propel itself will have significant effects on the airflow around the aircraft The challenge aircraft designers face is to prevent these effects from disrupting the aerodynamic efficiency or stability and control of the aircraft Propeller Simulation We have a world leading capability in propeller testing for half span models built on decades of pioneering work into balance hub and blade design as well as telemetry and data acquisition We offer both single propeller twin propeller and contra prop configurations The propellers are powered by air motors driven by a high pressure air supply Our advanced health monitoring system for the air motors and propeller blades is very successful in detecting potential problems before they occur providing significant advances in reliability and productivity Our one stop service includes the manufacture of the rotary balances followed by calibration in our Balance Calibration Laboratory as well as fine tuning the balancing of propeller assemblies in our Propeller Test Cell Jet Simulation ARA has been a pioneer in jet propulsion testing since TPS units turbine powered simulators driven by high pressure air were first developed over 40 years ago TPS units allow a high fidelity simulation of inlet conditions and bypass flow through a jet engine model Our one stop service includes the design and manufacture of the engine models followed by calibration of the assembled

    Original URL path: http://www.ara.co.uk/zh/services/page-11/transonic-wind-tunnel-testing/civil-aircraft/installed-propulsion-performance/ (2016-02-17)
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  • Isolated Propulsion Performance » Aircraft Research Association
    Balance Design and Manufacture 计算流体动力学 CFD Software Code Development CFD Software Code Application Applied Aerodynamics Integrated CFD Wind Tunnel Weapons and Weapon Bay Analysis Wing Design Process Aerodynamic Research 创新与技术 Clean Sky Project Strain Gauge Balance Developments Pressure Sensitive Paint Model Deformation Measurement New Page zh Media Centre Image Library Video Gallery Document Downloads Newsletter Registration Careers Vacancies New Page zh New Page zh New Page zh New Page zh Benefits Apprentices Personal Experiences Graduates Industrial Placements Work Experience Contact Isolated Propulsion Performance Aircraft Research Association 服务 实验空气动力学 Transonic Wind Tunnel Testing Civil Aircraft Isolated Propulsion Performance Large Scale Isolated Propeller Testing The Acoustic Liner The continuous drive for reductions in fuel burn for commercial aircraft means that the development of open rotor propulsion systems will be one of the most important areas of research now and in the long term The acoustic signatures of such systems and the acquisition of noise data is a very important part of these development programs ARA has an unique capability within Europe for noise measurements on large scale propeller and open rotor systems at speeds up to Mach 0 8 An acoustic liner is mounted in the Transonic Wind Tunnel working section providing sufficiently anechoic conditions to allow the measurement of acoustic tones on open rotor configurations Acoustic measurements are made using either a microphone traversing rig or fixed microphone arrays Open rotor systems of up to 1 metre diameter are tested mounted on 440 kW induction or electric motors The motors can be configured to drive either single or contra rotating open rotors Each rotor is mounted on a strain gauge balance to measure thrust torque and off axis loads Near and far field acoustic characteristics are measured using high quality microphones along with rotor performance and pressure data Isolated Cowl Test

    Original URL path: http://www.ara.co.uk/zh/services/page-11/transonic-wind-tunnel-testing/civil-aircraft/isolated-propulsion-performance/ (2016-02-17)
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web-archive-uk.com, 2017-12-11