This paper experimentally investigates a highly-loaded 1.5-stage transonic axial compressor, which comprises variable inlet guide vane, BLISK rotor, and stator in tandem arrangement. A detailed comparison between the newly designed compressor stage reference with conventional design was conducted by using extensive instrumentation. Thus, steady unsteady phenomena—focusing on aerodynamic aeroela...

Designs for future aero engines aim increased efficiency with reduced exhaust gas and noise emissions. To achieve these goals, comprehensive physical understanding highly innovative solutions are necessary. Even though computational capabilities rising, the required confidence level is restrained. understand validate theoretical numerical models, extensive experiments at realistic operating con...

Designs for future aero engines aim increased efficiency with reduced exhaust gas and noise emissions. To achieve these goals, comprehensive physical understanding highly innovative solutions are necessary. Even though computational capabilities rising, the required confidence level is restrained. understand validate theoretical numerical models, extensive experiments at realistic operating con...

Three-dimensional unsteady computations of the flow past a fruit fly Drosophila under hovering and free flight conditions are computed. The kinematics of the wings and the body of the fruit fly are prescribed from experimental observations. The computed unsteady lift and thrust forces are validated with experimental results and are in excellent agreement. The unsteady aerodynamic origin of the ...

This article presents a comprehensive mapping of wall-pressure fluctuations over an airfoil under three different inflow conditions to shed light on some basic assumptions taken for granted the recent aeroacoustic and aerodynamics experimental studies in noise prediction models. Unsteady steady pressure measurements were performed heavily instrumented airfoil, which was exposed smooth inflow, g...

Abstract. This paper describes the growing use of computational fluid dynamics (CFD) at the Lockheed Martin Aeronautics Company to assess and design for unsteady loads. The experience in development and in use of CFD for unsteady loads is presented in four sections: (1) background and motivation leading to the development of this capability, (2) an overview of the tools and processes utilized i...

2 Discretization 9 2.1 The Discontinuous Galerkin Method . . . . . . . . . . . . . . . . . . . . . 9 2.1.1 Conservation Equations . . . . . . . . . . . . . . . . . . . . . . . . 9 2.1.2 Solution Approximation . . . . . . . . . . . . . . . . . . . . . . . . 9 2.1.3 Weak Form . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . . 10 2.1.4 Discrete System . . . . . . . . . . . . . . . . . ....

An output-based dynamic order re nement strategy is presented for unsteady simulations using the discontinuous Galerkin nite element method in space and time. A discrete unsteady adjoint solution provides scalar output error estimates and drives adaptive re nement of the space-time mesh. Space-time anisotropy is measured using projection of the adjoint onto semi-re ned spaces and is used to all...

Abstract Boundary layer ingestion (BLI) offers potential reductions in fuel burn and emissions. The propulsive fuselage concept features an aft fan that ingests the 360 deg boundary layer. A critical condition for this configuration occurs when a sideslip angle arises between aircraft longitudinal axis freestream velocity. flow combination with airframe generates inlet distortion depends on dir...