Searched for: contributor%3A%22Vos%2C+R.+%28mentor%29%22
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van der Pluijm, Ricardo (author)
The Flying V is an innovative new aircraft concept currently being developed by the faculty of Aerospace Engineering at Delft University of Technology. This aircraft is a flying wing having a large sweep on the inner section, and a small sweep angle at the outer, giving the aircraft its characteristic V shape. The objective of this research is...
master thesis 2021
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Johnson, Nelson (author)
This report concerns an experimental investigation of the winglet integration, rudder deflection and aileron-rudder interaction effects on the Flying V aircraft configuration using a 4.6% scale model. The effects on the lift, drag, side-force, rolling moment, pitching moment and yawing moment coefficients are all described. The first results...
master thesis 2021
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van Uitert, Jeroen (author)
This research has been performed with the purpose of understanding the cause of the unstable pitch break experienced by the Flying V at a lift coefficient of CL = 0.95. Without understanding and possibly elimination of the pitch break, the flying V’s usable maximum lift coefficient is lower and the pitching moment behavior and gust response...
master thesis 2021
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Larkens, Robert (author)
Air transport is facing an important challenge when it comes to the reduction of its environmental footprint. Hybrid electric aircraft offer a potential solution to reduce in-flight emissions. The essence of hybrid electric aircraft is to combine multiple energy sources and energy conversion systems, in order to improve the overall energy...
master thesis 2020
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Hillen, Marleen (author)
The Flying-V, a flying wing being designed for air transport, has its wing designed around two cylindrical pressure cabins that are positioned such that they create a “V” shape. The objective of the research presented in this thesis is to create a parametrisation of the Flying-V Outer Mould Line that includes design flexibility and...
master thesis 2020
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Otting, M.M. (author)
The purpose was to develop a preliminary nacelle design method to evaluate the impact of the nacelle's geometry on the net propulsive force of an engine in multiple flight conditions. The 2D axisymmetric nacelle is parameterised and analysed for the cruise and take-off conditions using an Euler solver to find the optimum Pareto front. Several...
master thesis 2020
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Deshmukh, Piyush (author)
With the focus on the reduction of fossil fuel emissions, aircraft are continuously growing towards higher fuel efficiency. The traditional limits of aircraft performance can be surpassed through the use of composite materials which offer a reduction in aircraft weight. Due to the multidisciplinary nature of aircraft design, integration of...
master thesis 2020
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Leung, K.C. (author)
A low-speed aerodynamic analysis on the conventional NACA ram-air inlet of the Airbus A320 with a new closure flap was conducted. The conventional closure flap mechanism inside the NACA ram-air inlet is replaced by a morphing plate design. Steady-state Reynolds-Averaged Navier-Stokes (RANS) based Computational Fluid Dynamics (CFD) simulations...
master thesis 2020
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Harinarain, V.N. (author)
The Delft University Unconventional Concept (DUUC) is an innovative short take-off medium range aircraft design that utilizes a system of two ducted propellers, mounted on the aft part of the fuselage. The first design of this system consists of two axisymmetric ducts, each containing a propeller mounted to a centerbody that is attached to the...
master thesis 2017
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Brown, M.T.H. (author)
Blended wing body aircraft represent a paradigm shift in jet transport aircraft design. Stepping away from the conventional tube-and-wing philosophy, they promise benefits over existing or future conventional aircraft. The most significant challenge with the concept is the increased coupling between aircraft design disciplines that has...
master thesis 2017
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Van den Dungen, N.H.M. (author)
A study is done to investigate the feasibility of the conceptual design of the Delft University Unconventional Configuration (DUUC), an aircraft featuring a ducted-fan propulsive empennage. This research is focused on ducted-fan performance analysis and aircraft longitudinal static stability and balance estimation. The aircraft design Initiator...
master thesis 2017
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van Dommelen, D. (author)
The introduction of metal into the aeronautical industry made the wings and aerostructures stiff and rigid. High-lift devices and movable surfaces allow for discrete deflections to increase lift coefficient and control of the aircraft. Several researchers have proposed concepts for variable camber, allowing continuous deflections. This is...
master thesis 2017
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Van Wonderen, N.J. (author)
master thesis 2017
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Singh, B. (author)
A medium fidelity tool has been developed for the computation of a wing's maximum lift coefficient in low speed while adhering to conceptual aircraft details. This tool is part of the Initiator which is a conceptual/preliminary aircraft design tool developed by the FPP group. The methodology comprises out of a synergy between empirical...
master thesis 2017
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Cosenza, D. (author)
The handling qualities of an aircraft have always been a crucial field of study, being chiefly concerned with the safety and comfort of flight. Historically, the design-by-discipline approach has been used, thus relegating stability and control considerations to later stages of the design process. In recent years a new view emerged, which...
master thesis 2016
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Faggiano, F. (author)
Lately, commercial aviation has been moving towards the reduction of environmental impact and direct operating costs, due to the rapid increase in aircraft demand and air traffic congestion predicted for the next years. Several researchers have been abandoning the fully exploited conventional configuration and exploring novel arrangements, such...
master thesis 2016
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Orlita, M. (author)
In the era of increasing aviation traffic the conditions are right to promote design of ambitious concepts. At Fokker Aerostructures attention is drawn to smooth in-flight shape morphing to produce a structurally functional Variable Camber Trailing Edge Flap (VCTEF). The deployment mechanism would fit into the flap, not limiting other...
master thesis 2016
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Roelofs, M.N. (author)
A semi-analytical weight estimation method is proposed for composite, oval fuselages, but is also applicable to conventional fuselages and to metallic materials. Loads applied to the fuselage include pressurization, steady-state maneuver loads and inertial loads. The primary structure around the passenger cabin is sized, based on first-ply...
master thesis 2016
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Koch, R.M. (author)
Two approaches were used and compared to design a new medium-range passenger aircraft: a derivative design based on the A330-200 long-range aircraft and a completely new clean-sheet design. Four different derivative configurations, with different materials and levels of commonality to the A330-200, and one clean-sheet configuration were defined,...
master thesis 2016
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Geleyns, D. (author)
This report contains a study about the possible benefits of changing the way large airliners are controlled in flight. The goal is to save fuel by decreasing the structural weight of the aircraft. Over the last decades the conventional primary control surfaces in civil aviation have not deviated from elevators, ailerons/spoilers and rudder....
master thesis 2016
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