Research for Transonic Aircraft

Oblique Wing: Future Generation Transonic Aircraft

A Composite Finite Difference Scheme for Subsonic Transonic Flows (RESEARCH NOTE).

This paper presents a simple and computationally-efficient algorithm for solving steady two-dimensional subsonic and transonic compressible flow over an airfoil. This work uses an interactive viscous-inviscid solution by incorporating the viscous effects in a thin shear-layer. Boundary-layer approximation reduces the Navier-Stokes equations to a parabolic set of coupled, non-linear partial diff...

Free-To-Roll Analysis of Abrupt Wing Stall on Military Aircraft at Transonic Speeds

LE leading edge Transonic free-to-roll and static wind tunnel tests for four military aircraft – the AV-8B, the F/A-18C, the pre-production F/A-18E, and the F-16C – have been analyzed. These tests were conducted in the NASA Langley 16-Foot Transonic Tunnel as a part of the NASA/Navy/Air Force Abrupt Wing Stall Program. The objectives were to evaluate the utility of the freeto-roll test techniqu...

Aerodynamic and Structural Optimisation of Powerplant Integration under the Wing of a Transonic Transport Aircraft

Multi-disciplinary optimisation (MDO) of the outboard engine pylon of a large transonic transport aircraft is reported in this paper. The disciplines involved were structure and aerodynamics, although this paper focuses on the aerodynamic aspect. A two-level strategy was followed to solve this problem: three parameters are identified as playing a coupling role between disciplines and are addres...

AIAA -86-0103 Calculation of Inviscid Transonic Flow over a Complete Aircraft

We present preliminary results for the calculation of inviscid transonic flow over a complete aircraft. These results have been obtained by a novel approach that combines a new procedure for mesh generation with a new finite element method for solving the Euler equations. Introduction A principal goal of computational aerodynamics has been the calculation of transonic flow over a complete aircr...