Hybrid electric propulsion is a promising solution to reduce aircraft emissions, thus improving the sustainability of air transport. In this work, hybrid configuration with rear-mounted boundary layer ingestion (BLI) engine has been investigated. The partial embedding into fuselage generates distortion ingested inflow causing additional tonal and broadband BLI noise sources, and, at same time, ...

Realization of laminated fiber reinforced composite structures through autoclave process is quite challenging. This is due to the complex geometries of the composite structure and also due to the bending and stretching coupling introduced by stacking of plies of different orientations. In the curing process due to the different coefficients of thermal expansion of the composite component and th...

To ensure flight safety of aircraft structures, it is necessary to have regular maintenance using visual and nondestructive inspection (NDI) methods. In this paper, we propose an automatic image-based aircraft defect detection using Deep Neural Networks (DNNs). To the best of our knowledge, this is the first work for aircraft defect detection using DNNs. We perform a comprehensive evaluation of...

The aerodynamic characteristics of an isolated MRH 90 helicopter fuselage have been investigated using Computational Fluid Dynamics (CFD). Simulations utilised an unstructured tetrahedral grid and both the k-ε and k-ω SST turbulence models were investigated. Standard ‘law of the wall’ wall functions were incorporated, along with a segregated finite volume solver. A wind tunnel testing program w...

The present methodological study aims to assess boundary layer ingestion (BLI) as a promising method improve propulsion efficiency. BLI utilizes the low momentum inflow of wing or fuselage for thrust generation in order minimize required propulsive power given amount fuselage-embedded engines. A multi-segment parallel compressor model (PCM) is developed calculate saving from full annular occurr...

SLJMMARY A rectangular intake having variable geometry compression surfaces and designed for supersonic operation has been tested at a Mach number of 0.9 and a Reynolds number based on intake entry height of approximately 106. Tests have been made on the intake in isolation and on the side of a fuselage. Maximum mass flow is less than estimates based on geometric throat size. The deficit corres...