Journal of aerospace engineering & technology (vol4, issue3) by STM Journals Publication

ISSN: 2348-7887

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Dr. Subba Raju P.V Prof. & Chairman, Aeronautical & Mechanical Engineering Division, Institute of Aeronautical Engineering, Dundigal, Hyderabad, India.

Prof. Kalyan Prasad Sinhamahapatra Head, Department of Aerospace Engineering, IIT Kharagpur, India.

Prof. Murthy RL C Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India.

Dr Yuwaraj Marotrao Ghugal Department of Applied Mechanics, Govt. College of Engineering Station Road, Osmanpura, Aurangabad, India.

Vijayaraja Kengaiah Prof. , Head, Aeronautical Engg. Dept., P.B. College of Engg., Chennai, India.

Dr Ashok K Singh Department of Aerospace Engineering, Defence Institute of Advanced Technology, Girinagar, Pune, India.

Amarjeet Singh Department of Computer Applications, Institute of Environment and Management, Lucknow, Uttar Pradesh, India.

Dr. Tiauw Hiong Go Nanyang Technological University, Singapore.

Dr. Ravishekar Kannan Computational Fluid Dynamics (CFD), Research Corporation, United States.

Mr. Ravindranath Nayak Head, Aerospace Electronics & Systems Division, National Aerospace Laboratories (NAL), CSIR Airport Rd, Kodihalli, Bangalore India.

Dr. M. R. Nayak Head, Aerospace Electronics & Systems Division, and Advisor to Director National Aerospace Laboratories, India.

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I take the privilege to present the hard copy compilation for the [Volume 4 Issue (3)] of Journal of Aerospace Engineering & Technology (JoAET). The intension of JoAET is to create an atmosphere that stimulates creativeness, research and growth in the area of Aerospace Engineering & Technology. The development and growth of the mankind is the consequence of brilliant Research done by eminent Scientists and Engineers in every field. JoAET provides an outlet for Research findings and reviews in areas of Aerospace Engineering & Technology found to be relevant for National and International recent developments & research initiative. The aim and scope of the Journal is to provide an academic medium and an important reference for the advancement and dissemination of Research results that support high level learning, teaching and research in the domain of Aerospace Engineering & Technology. Finally, I express my sincere gratitude and thanks to our Editorial/ Reviewer board and Authors for their continued support and invaluable contributions and suggestions in the form of authoring writeups/ reviewing and providing constructive comments for the advancement of the journals. With regards to their due continuous support and co-operation, we have been able to publish quality Research/Reviesw findings for our customers base. I hope you will enjoy reading this issue and we welcome your feedback on any aspect of the Journal.

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Journal of Aerospace Engineering & Technology

Contents

1. Numerical Simulation of Flow Field, Fountain Flow and Associated Noise in Supersonic Impinging Twin Jet using Large Eddy Simulation Devi Archana Das, Nishant Madanagopal

2. Numerical Investigation of Drag and Lift Forces on Turbulent Flow on an Airfoil Shaped Body at Different Angles of Attack Suvanjan Bhattacharyya, Shramona Chakraborty, Sumanta Laha 9 3. Conceptual Design and Validation of Working of the Wing Morphing Mechanism Using Bellows Nandu Jith P. J., Akshay Pal

4. Displacements in Thick Beams Using Refined Shear Deformation Theory Ajay G. Dahake, Mahendra R. Chitlange

Journal of Aerospace Engineering & Technology ISSN: 2231-038X (online), ISSN: 2348-7887 (print) Volume 4, Issue 3 www.stmjournals.com

Numerical Simulation of Flow Field, Fountain Flow and Associated Noise in Supersonic Impinging Twin Jet using Large Eddy Simulation Devi Archana Das*, Nishant Madanagopal Amity Institute of Space Science and Technology, Amity University, Sector 125, Noida, Uttar Pradesh - 201303, India Abstract A three-dimensional flow field is produced by a supersonic twin-jet impingement. It is studied using the turbulence model Large Eddy Simulation (LES). The numerical model consists of two parallel jets of diameter 3D apart, which are issued from a plane which is at a distance H = 2D, 3D, 4D above the ground. The Nozzle Pressure Ratio (NPR) is kept at 3.7 for all the flow conditions. The study is based on the extent of rise of the fountain due to the impinging of the jets on the ground plane. The associated noise is calculated from the pressure distributions at certain important points defined. Instantaneous flow, mean velocity magnitude, RMS pressure data, mean centre line jet velocities and various fountain flow contours for the twin-jet impingement are produced and discussed. A high level of unsteadiness and strong interactions between the fountain and the jets are observed, which varies for the different H/D ratios.

Keywords: LES, supersonic twin-jet impingement, acoustics, vortex formation, fast fourier transform *Author for Correspondence E-mail: deviarchanadas@gmail.com

Journal of Aerospace Engineering & Technology ISSN: 2231-038X (online), ISSN: 2348-7887 (print) Volume 4, Issue 3 www.stmjournals.com

Numerical Investigation of Drag and Lift Forces on Turbulent Flow on an Airfoil Shaped Body at Different Angles of Attack Suvanjan Bhattacharyya1*, Shramona Chakraborty2, Sumanta Laha1 1

Mechanical Engineering Department, MCKV Institute of Engineering, Liluah, Howrah, West Bengal, India 2 Computer Science Engineering Department, MCKV Institute of Engineering, Liluah, Howrah, West Bengal, India

Abstract Numerical analysis of drag and lift force on an airfoil shaped body at different angles is presented. Fundamentals of aircraft design are provided with detailed estimation of the aerodynamic drag and lift of airfoil is presented. This work presents the configuration optimization of an aerofoil body in air using SST computational fluid dynamics (CFD) modeling and compared with the experimental result. The governing equations are solved with a finite-volume-based numerical method. A three-dimensional non uniform grid was generated, in order to critically examine the flow. At different angle the coefficient of drag and lift is determine. Airfoil was placed in a low speed wind tunnel with pressure taps along its surface. The wind tunnel was operated at nominal velocities during the coefficient measurement, a Reynolds number of about 100â&#x20AC;&#x201C;2000. The airfoil, with a 10 inch chord, was analyzed at 0o, 5o, 10o, 15o, 20o, 25o angles of attack and with fixed load.

Keywords: CFD, drag force, coefficient of drag, coefficient of lift, wind tunnel

Journal of Aerospace Engineering & Technology ISSN: 2231-038X (online), ISSN: 2348-7887 (print) Volume 4, Issue 3 www.stmjournals.com

Conceptual Design and Validation of Working of the Wing Morphing Mechanism Using Bellows Nandu Jith P. J.*, Akshay Pal Amity Institute of Space Science and Technology, Amity University, Noida (U.P.), India Abstract The research on creating a smooth seamless wing which can literally morph its shape in mid-flight like birds has been in progress for many years. Such a wing will greatly enhance the flying capabilities of a normal aircraft. The wing can be morphed at different speeds to increase greater fuel efficiency. Our new design tends to create such a design without interfering with structural integrity of the wing.

Keywords: Morphing wing, bellows, pneumatic system

Journal of Aerospace Engineering & Technology ISSN: 2231-038X (online), ISSN: 2348-7887 (print) Volume 4, Issue 3 www.stmjournals.com

Displacements in Thick Beams Using Refined Shear Deformation Theory Ajay G. Dahake1*, Mahendra R. Chitlange2 1

Department of Civil Engineering, Marathwada Institute of Engineering, Maharashtra State, India 2 Government Polytechnic, Jalna, Maharashtra State, India

Abstract A trigonometric shear deformation theory for displacement of thick beams, by considering the transverse shear deformation effects, is presented. Variables in the present theory are same as that of in the first order shear deformation theory. The sinusoidal function is used in displacement field in terms of thickness coordinate to represent the shear deformation effects. Governing differential equations and various boundary conditions are obtained by using the principle of virtual work. The thick isotropic beams are considered for the numerical studies to demonstrate the efficacy of the theory. It has been shown that the theory is capable of predicting the local effect of stress concentration due to fixity of support. The cantilever and fixed isotropic beams subjected to various loads are examined using the present theory. Results obtained are discussed with those of other theories.

Keywords: Thick beam, trigonometric shear deformation, principle of virtual work, equilibrium equations, displacement, stress