Results 61 to 70 of about 9,476,674 (192)

Methodology Development and Investigation of Turbofan Engine Response to Simultaneous Inlet Total Pressure and Swirl Distortion [PDF]

open access: yes, 2019
As a contribution to advancing turbofan engine ground test technology in support of propulsion system integration in modern conceptual aircraft, a novel inlet distortion generator (ScreenVaneTM) was invented.
Frohnapfel, Dustin Joseph
core  

Comparative Study on the Performance of S-Shaped Diffuser With Shorten Length

open access: yesMATEC Web of Conferences, 2018
This study presents numerical investigation on the performance of S-shaped air intake normal and aggressive diffuser with 22% length reduction. Both models have same area ratio of 3.1 with different total length, turning angle and radius of curvature ...
Jessam Raed A.   +2 more
doaj   +1 more source

Research on Unsteady Flow Field Characteristics of Submerged Inlet under Large Maneuver Condition [PDF]

open access: yesHangkong bingqi
In order to explore the differences in steady-state and transient aerodynamic characteristics of submerged inlets during high maneuvering flight, this study focuses on cruise missile and adopts CFD numerical methods to conduct steady-state and transient ...
Feng Yuhua, Zhang Junyao, Wang Limin, Mi Baigang
doaj   +1 more source

Distortion mechanisms in varactor diode-tuned microwave filters [PDF]

open access: yes, 2006
This paper examines the broadband distortion behavior in flexible filters employing varactor-diode tuning elements. Series- and parallel-resonant varactor-loaded transmission-lines, both commonly used in bandpass and bandstop microwave filters, are ...
Carey-Smith, BE, Warr, PA
core   +1 more source

Dimensionality Reduction Optimization of High Subsonic Unmanned Aerial Vehicles Intake

open access: yes气体物理
To address the problem of poor aerodynamic performance in the S-shaped intake duct of a subsonic unmanned aerial vehicle (UAV), the study investigates how to optimize its design to achieve the highest possible total pressure recovery coefficient and ...
Zeqi QI, Zheng GUO, Suqi CHEN, Ke YU
doaj   +1 more source

Numerical simulation of continuous penetration of spudcan based on SPH mesh-free method

open access: yesShuili Shuiyun Gongcheng Xuebao, 2020
The penetration process of spudcan in saturated soil concomitantly involves extremely large soil deformation and complex soil-water-structure interaction, which are difficult to simulate using traditional mesh-based methods due to mesh distortion. SPH is
MENG Xiang   +3 more
doaj   +1 more source

The Influence of Development and Fan/Screen Interaction on Screen-Generated Total Pressure Distortion Profiles

open access: yes, 2014
The rising interest in fan performance in the presence of total pressure distortion, a topic of fundamental interest for integrated airframe/engine architectures, has led to increased research in ground based testing environments.
Bailey, Justin Mark
core  

Turboelectric Distributed Propulsion System Modelling [PDF]

open access: yes, 2013
The Blended-Wing-Body is a conceptual aircraft design with rear-mounted, over wing engines. Turboelectric distributed propulsion system with boundary layer ingestion has been considered for this aircraft.
Liu, Chengyuan
core   +3 more sources

Lattice Distortion and Phase Stability of Pd-Doped NiCoFeCr Solid-Solution Alloys

open access: yesEntropy, 2018
In the present study, we have revealed that (NiCoFeCr)100−xPdx (x= 1, 3, 5, 20 atom%) high-entropy alloys (HEAs) have both local- and long-range lattice distortions by utilizing X-ray total scattering, X-ray diffraction, and extended X-ray ...
Fuxiang Zhang   +5 more
doaj   +1 more source

Effects of inlet total pressure distortion on fan performance

open access: yes, 2009
Experiments were performed at the AneCom AeroTest facility in Wildau, Germany to determine the effects of inlet total pressure distortions, representative of those expected for an inlet to a supersonic business jet, on fan performance. A Rolls-Royce fan,
Md Ishak, Nizam Haris
core   +1 more source

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