This paper presents the parameterization and optimization of two well-known airfoils. The aerodynamic shape investigation includes subsonic (NREL S-821) transonic airfoils (RAE-2822). class transformation is employed for parametrization while genetic algorithm used purposes. absolute scheme process carried out minimization drag coefficient maximization lift to ratio. In-house MATLAB code incorp...

Friction drag constitutes approximately half of the total subsonic civil transport aircraft at cruise conditions. Several means were examined to control flow over an and achieve laminar flow. Here, a new concept for friction reduction in form integration aerodynamics propulsion is put forward. Engines buried wing rear fuselage suck boundary layer entire surface, then, they used it as intake air...

Domain decomposition (Krylov-Schwarz) iterative methods are natural for the parallel implicit solution of multidimensional systems of boundary value problems that arise, for instance, in aerodynamics. They provide good data locality so that even a high-latency workstation network can be employed as a parallel machine. Matrix-free (Newton-Krylov) methods are natural when it is unreasonable to co...

this paper is a computational study of the behavior of aerodynamics  characteristics of an airfoil with blunt trailing edge and  studies the effects aerodynamic performance caused by modifications made to the trailing edge. blunt trailing edge airfoils are of interest in the engineering of large wind turbine blades because they allow for a strong structure with a high aerodynamic lift to struct...

Since the development of the IAS computer built from 1942 to 1951 at the Institute of Advanced Studies under the supervision of John von Neumann, computer engineers’ push to make the hardware more practical and efficient has been driven and challenged by a handful of applied fields. While it is widely recognized that Aerodynamics played a key role in the development of modern scientific computi...

Abstract: In this paper, we establish existence of global subsonic and subsonic-sonic flows through infinitely long axially symmetric nozzles by combining variational method, various elliptic estimates and a compensated compactness method. More precisely, it is shown that there exist global subsonic flows in nozzles for incoming mass flux less than a critical value; moreover, uniformly subsonic...

Since the introduction of large jet-powered transport aircraft, the majority of these vehicles have been designed by placing thrust-generating engines either under the wings or on the fuselage to minimize aerodynamic interactions on the vehicle operation. However, advances in computational and experimental tools along with new technologies in materials, structures, and aircraft controls, etc. a...

A Drag Prediction Workshop was held in conjunction with the 19th AIAA Applied Aerodynamics Conference in June 2001. The purpose of the workshop was to assess the prediction of drag by computational methods for a wing/body con guration (DLR-F4) representative of subsonic transport aircraft. This report details computed results submitted to this workshop using the Reynolds-averaged Navier-Stokes ...

Stage separation is a critical technical issue for developing two-stage-to-orbit (TSTO) launch systems with widebody carrier aircraft that use air-breathing propulsion and launch vehicle stages that use rocket propulsion. During conceptual design phases, this issue can be addressed with a combination of engineering methods, computational fluid dynamics simulations, and trajectory analysis of th...

A compensated compactness framework is established for sonic-subsonic approximate solutions to the two-dimensional Euler equations for steady irrotational flows that may contain stagnation points. Only crude estimates are required for establishing compactness. It follows that the set of subsonic irrotational solutions to the Euler equations is compact; thus flows with sonic points over an obsta...