Defence Research and Development Laboratory

About: Defence Research and Development Laboratory is a facility organization based out in Hyderabad, India. It is known for research contribution in the topics: Mach number & Turbulence. The organization has 404 authors who have published 420 publications receiving 4183 citations. The organization is also known as: DRDL.

Simulation of supersonic base flow: Effect of computational grid and turbulence model

Abstract: The supersonic base flow of a blunted cone-cylinder rocket model in the presence of a central propulsive jet is investigated numerically by solving three-dimensional Reynolds averaged Navier—Stokes equations in an unstructured mesh using a commercial computational fluid dynamics software. The effect of the computational grid and the turbulence model in predicting the radial variation of base pressure has been brought out. Very fine grid (y+∼ 2) is required to correctly predict the base pressure. The renormalized group k—ɛ turbulence model performs better compared to the k—ω turbulence model in predicting the base pressure. It was observed that the base flow characteristics in the lower and upper portions of the base are significantly different due to the influence of model support.

Separation Dynamics of Air-to-Air Missile Using a Grid-Free Euler Solver

Abstract: The study of separation dynamics of a missile from a fighter aircraft is a prime requirement to ensure the safety of the aircraft before flight testing the missile. An integrated store-separation-dynamics suite has been developed and applied to study the separation of an air-to-air missile from a fighter aircraft. The suite consists of a preprocessor to generate connectivity using overlapped unstructured grids, a three-dimensional grid-free Euler solver to obtain aerodynamic forces and moments on the missile and a six-degrees-of-freedom solver to integrate the equations of motion. A quasi-steady approach has been used to simulate the separation dynamic of rail-launched missile. The motion of the missile guided by the rail launcher has been modeled using constrained-force method and implemented in the six-degrees-of-freedom code. The surface transpiration boundary condition has been incorporated in the Euler solver to mimic the aerodynamic damping and the relative motion of the missile with respect to the ...

Bibliometric Analysis of the Journal of Propulsion and Power (1985-2013)

Abstract: Journal of Propulsion and Power (JPP) is a bi-monthly peer reviewed journal published by American Institute of Aeronautics and Astronautics (AIAA). The present bibliometric analysis is based on 4047 articles published from 1985 to 2013. The study is aimed to assess the growth pattern of research output, authorship pattern, institutional productivity, and geographical distribution of output. The highest number (194) articles were published in year 1992 and lowest (81) in 1987. Out of total articles, 1330 were produced by two authors and 1098 by three authors. It is found that 1205 different institutions were involved in publication of articles. ‘Purdue University’ contributed highest number of 163 articles. Out of ranked list of 21 affiliations which produced more than 50 articles, 18 institutions were from USA, 2 from Japan, and 1 from Germany, etc. It is observed that highest numbers of 2672 articles were contributed by USA. Country-wise collaborative research productivity of articles reveals that maximum number of articles, i.e., 3760 were produced by one country. International collaboration was involved in producing 287 articles. Out of 287 articles, 171 articles were produced by USA in collaboration with other countries. From top 27 ranked list of authors who have contributed alone or co-authored along with other authors, it is found that Fleeter, S. from Purdue University, USA has authored and co-authored highest number of 54 articles. http://dx.doi.org/ 10.14429/djlit.34.5438

Numerical Simulation of Supersonic Jet Impingement on Inclined Plate

Abstract: Supersonic jet impinging on an inclined plate is explored numerically by solving Reynolds Averaged Navier Stokes (RANS) equations using a commercial solver. The numerical uncertainty is quantified by grid convergence index parameter analysis. Simulations capture crisply all the essential features of the flow field including jet boundary, jet shock, upper tail shock, front and behind plate shocks. Good agreement between computational and experimental results for different plate angles forms the basis of further analysis. Four different two equations turbulence models predict similar jet structures. Effect of plate angles, pressure ratio, nozzle-plate distance on impinged jet structures are evaluated from numerical results. It has been observed that with increase in the plate angle, the maximum pressure zone in the plate changed from crescent shape to round shape. Well resolved RANS simulations are capable of capturing finer details of supersonic impinging jets on inclined plate. Defence Science Journal, 2013, 63(4), pp.355 -362 , DOI:http://dx.doi.org/10.14429/dsj.63.2545