scholarly journals Aerodynamics of High-Lift Configuration Civil Aircraft Model in JAXA

2007 ◽  
Vol 55 (647) ◽  
pp. 563-571 ◽  
Author(s):  
Yuzuru Yokokawa ◽  
Mitsuhiro Murayama ◽  
Takeshi Ito ◽  
Kazuomi Yamamoto
Keyword(s):  
High Lift ◽  
Aircraft Model ◽  
Civil Aircraft

scholarly journals High-fidelity simulations of unsteady civil aircraft aerodynamics: stakes and perspectives. Application of zonal detached eddy simulation

2014 ◽  
Vol 372 (2022) ◽  
pp. 20130325 ◽  
Author(s):  
Sébastien Deck ◽  
Fabien Gand ◽  
Vincent Brunet ◽  
Saloua Ben Khelil
Keyword(s):  
Turbulent Flows ◽  
Hybrid Methods ◽  
Landing Gear ◽  
High Fidelity ◽  
Detached Eddy Simulation ◽  
High Lift ◽  
Eddy Simulation ◽  
Civil Aircraft ◽  
Aircraft Aerodynamics ◽  
Transonic Buffet

This paper provides an up-to-date survey of the use of zonal detached eddy simulations (ZDES) for unsteady civil aircraft applications as a reflection on the stakes and perspectives of the use of hybrid methods in the framework of industrial aerodynamics. The issue of zonal or non-zonal treatment of turbulent flows for engineering applications is discussed. The ZDES method used in this article and based on a fluid problem-dependent zonalization is briefly presented. Some recent landmark achievements for conditions all over the flight envelope are presented, including low-speed (aeroacoustics of high-lift devices and landing gear), cruising (engine–airframe interactions), propulsive jets and off-design (transonic buffet and dive manoeuvres) applications. The implications of such results and remaining challenges in a more global framework are further discussed.

1305 Aerodynamic Design Optimization of Low Noise High-Lift Airfoil for Civil Aircraft

2013 ◽  
Vol 2013.23 (0) ◽  
pp. _1305-1_-_1305-10_
Author(s):  
Ryu SHINOMIYA ◽  
Masahiro KANAZAKI ◽  
Mitsuhiro MURAYAMA ◽  
Kazuomi YAMAMOTO
Keyword(s):  
Design Optimization ◽  
Low Noise ◽  
Aerodynamic Design ◽  
High Lift ◽  
Aerodynamic Design Optimization ◽  
Civil Aircraft

Esso Energy Award Lecture, 1987 - Application of aerodynamic research and development to civil aircraft wing design

1988 ◽  
Vol 416 (1850) ◽  
pp. 43-62
Keyword(s):  
Technological Progress ◽  
Computational Fluid Mechanics ◽  
Aerodynamic Design ◽  
Wing Design ◽  
High Lift ◽  
Business Jet ◽  
Civil Aircraft ◽  
Research Programmes ◽  
The Government

In the late 1950s the aerodynamicists at what is now the Hatfield site of British Aerospace accepted the challenge and met British European Airways’ demand for a 600 m. p. h. ( ca . 966 km h -1 ) short-haul jet airliner (the Trident). The experience and organization resulting from that project was the cornerstone on which the subsequent success story of civil wing design has been built. The substantial advances in efficiency achieved by the Hatfield team in the following designs for the 125 Business Jet, the 146 Feederliner and for the Airbus Industrie family of Wide-Body Mainline aircraft, has been supported by research programmes in the government establishments and universities as well as industry itself. Each project had its individual demands for fuel economy, high lift capability and structural efficiency, with commercial competition continually driving technological progress. The major highlights and achievements of the aerodynamic development programmes for these projects are reviewed. Turning to the present, the Hatfield team are currently working on the aerodynamic design for the combined Airbus A330/340 project. Technological progress continues apace with major investment in computational fluid mechanics, but the still essential role of experimental test techniques and facilities is emphasized.

scholarly journals Research Civil Aircraft Model (RCAM) Dengan Metode Dinamis 6 Derajat Kebebasan Menggunakan MATLAB

2021 ◽  
Vol 3 ◽  
pp. 11-22
Author(s):  
Aulia Widya Prameswari ◽  
Arief Suryadi Satyawan ◽  
Denden Mohamad Ariffin
Keyword(s):  
Center Of Gravity ◽  
3D Animation ◽  
Aircraft Model ◽  
Civil Aircraft ◽  
Control Limits

Model Pesawat merupakan suatu usaha untuk menciptakan atau membuat simulasi pesawat yang sebenarnya dan model ini bisa disebut Research Civil Aircraft Model (RCAM), yaitu model pesawat sipil bermesin ganda yang dikembangkan oleh Group for Aeronautical Riset dan Teknologi di Eropa (GARTEUR). Model pesawat ini mirip dengan Boeing 757-200. Research Civil Aircraft Model yang dibuat menggunakan 6 derajat kebebasan. 6 derajat kebebasan terdiri dari 3 translasi yaitu 3 derajat untuk koordinat kartesian pada sumbu (x,y,z) dan 3 rotasi yaitu 3 derajat (pitch, roll, dan yaw) yang digunakan untuk mengontrol defleksi surface dan posisi throttle. Untuk membuat model, diperlukan parameter, yaitu parameter dari massa pesawat dan parameter dari chord aero dan juga CoG (Center of Gravity) dari suatu pesawat. Algoritma yang dimasukkan berasal dari control limits/Saturasi, Variabel Intermediate, Koefisien Force, Koefisien Momen, Efek Propulsi,  Efek Gravitasi hingga akhirnya disimulasikan menggunakan “Simulink” pada MATLAB. Agar yang dihasilkan tidak hanya grafik maka diperlukannya animasi untuk melihat sikap pesawat sehingga digunakanlah 3D Animation pada MATLAB. Hasil dari permodelan pesawat sipil ini untuk melihat simulasi stabilitas dari aileron, rudder, elevator, dan throttle saat pesawat itu terbang. Hasil yang ada dapat berubah-ubah karena pada 3D Animation, pesawat dapat dikendalikan dari sikap pesawat saat miring kanan atau kiri dan juga saat pesawat berguling. Dengan adanya hal ini diharapkan simulasi tersebut bisa effective untuk melihat hasil yang sebenarnya saat pesawat terbang dan juga bisa dijadikan untuk simulator sebelum pesawat tersebut lepas landas.

scholarly journals Numerical investigation of porous materials for trailing edge noise reduction

2020 ◽  
Vol 19 (6-8) ◽  
pp. 347-364
Author(s):  
Lennart Rossian ◽  
Roland Ewert ◽  
Jan W Delfs
Keyword(s):  
Noise Reduction ◽  
Porous Materials ◽  
Collaborative Research ◽  
Smooth Transition ◽  
Trailing Edge ◽  
High Lift ◽  
Trailing Edge Noise ◽  
Numerical Investigations ◽  
Civil Aircraft ◽  
Numerical Approaches

In the framework of the German Collaborative Research Center CRC 880: Fundamentals of High Lift for Future Civil Aircraft porous materials as a means towards the reduction of airfoil trailing edge noise are investigated. At DLR, both experimental and numerical approaches are pursued to understand the physics behind the noise reduction. The present paper focuses on the numerical investigations, for which the experimental data serves as an evaluation basis. From the analysis of homogeneous materials, first steps are made towards the design of aeroacoustically tailored materials. It is assumed that materials with locally varying permeability may be suitable to achieve maximum noise reduction, as they provide a smooth transition from the solid airfoil to the free flow in the wake. The simulation results support this understanding, however it is revealed that high local gradients in the material properties themselves may act as acoustic sources.

Sign in / Sign up

Export Citation Format

Share Document