Numerical Investigation of a Naca Air Intake for a Canard Type Aircraft

Silveira, B.H. da; Souza, Pedro Ricardo Corrêa; Almeida, Odenir de

doi:10.22161/ijaers.4.5.7

Cited by 3 publications

(4 citation statements)

References 2 publications

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“…By following this procedure, the new NACA air intake design was targeted to mass flow instead of designing it for maximum efficiency. With the intake dimensions determined, the calculation of the drag coefficient for the flush intake C Dfl and ram pressure efficiency h fl proceeded in an identical manner to that set out in Silveira et al (2017). The values are summarized below:…”

Section: Naca Air Intakementioning

confidence: 99%

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A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

Almeida

Souza

Cunha³

2021

J. Aerosp. Technol. Manag.

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This work presents selected results of an unconventional aircraft development campaign. Engine installation at the rear part of the fuselage imposed design constraints for air intakes that should be used for cooling purposes. Trial and error flight tests increased the development cost and time which required a more sophisticated analysis through computational fluid dynamics (CFD) techniques and robust semiempirical approach. The carried-out investigation of the air intakes started with an empirical approach from guidelines for designing NACA and scoops. Numerical studies via computational fluid dynamics were performed with the air intakes installed in the aircraft fuselage. An analysis based on the air intake efficiency, drag and the effect of angle of attack are detailed in this work. Different air intakes designs, such as scoops of different shapes, were evaluated seeking for improved air intake efficiency and low drag while providing enough air for cooling the engine compartment. The results showed that the numerical approach used herein decreased the development cost and time of the aircraft, providing a reasonable low-cost approach and leading to a design selection more easily. Based on the current approach the canard airplane geometry was changed to account for the new selected air intake for engine cooling purposes.

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Section: Naca Air Intakementioning

confidence: 99%

“…As a half-domain simulation, the symmetry condition was considered in the mid-plane of the aircraft fuselage. The sizing of the computational domain as well as the boundary conditions have been adjusted based on previous experiences as described by Silveira et al (2017) and Almeida and Souza (2017).…”

Section: Computational Domain and Boundary Conditionsmentioning

confidence: 99%

A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

Almeida

Souza

Cunha³

2021

J. Aerosp. Technol. Manag.

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“…Different studies in the aeronautical field go through aerodynamic and aeroacoustics analysis of subsonic jets through experimental tests and numerical simulations [9], [10] and [11], comparative studies for the design of propellers [12], characterization of the flow in NACAS and SCOOPS in unconventional aircraft [13] and [14]. These last works developed by CPAERO was in partnership with the aircraft manufacturer FABE Ltda, through the development of a methodology for the design, verification and validation of air intakes for a canard type aircraft (unconventional), as described by [15].…”

Section: Aeronautics and Automobilesmentioning

confidence: 99%

The development of an experimental aerodynamics research center in Brazil

Almeida¹

2021

IJAERS

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The present work describes the recent activities of the Experimental Aerodynamics Research Center (CPAERO) concerning all the efforts devoted to develop capacities on both experimental and numerical aerodynamic and aeroacoustic techniques applied for solving fundamental and industrial flows.Despite the low investment of resources by the Brazilian government and ruptures in institutional policies in the last decade, over the past 05 years it has been possible to build a mediumsize low-speed subsonic wind tunnel and acquire, as well as design and build, various apparatus for laboratory and open field studies.The main activities are developed in the sectors of aeronautical, automobile and alternative energy sources such as wind energy. However, other applications are under development in fields such as fluid-structure interaction, drone noise and calibration of wind tunnels and anemometric sensors.To support the experimental studies, special attention was given to computational aerodynamics through the use of open source codes for the design of airfoils, wings and more complex flow-body simulations in computational fluid dynamics (CFD).Growing interface with local and national companies is taking place, as well as research partners with other universities and research centers. Some results are presented for unconventional aircraft analyses, commercial vehicles such as sedan and pick-up's aerodynamics, flow over cylinders with different aspect ratios as well as experimental and numerical data for finite-height surface-mounted cylinders. Recent and new approaches are provided for designing biomimetic blades for small-scale horizontal axis wind turbine (HAWT). Aeroacoustics numerical data is also compared with experimental data for subsonic jets at free-stream and cross-flow conditions showing the flexibility of tools and capabilities at CPAERO. However, there has been a progressive advance of numerical methods through CFD (Computational Fluid Dynamics) in the last 4 decades, which has changed the

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“…For instance, an investigation of improvement of this type of air inlets has been achieved in [11]. Moreover, specific analyses have been proposed on air inlets for turboprops [12] or canard-type aircraft [13,14]. Electrical components were also studied.…”

Section: Introductionmentioning

confidence: 99%

Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

et al. 2023

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The aircraft environmental control system (ECS) is the second-highest fuel consumer system, behind the propulsion system. To reduce fuel consumption, one research direction intends to replace conventional aircraft with more electric aircraft. Thus, new electric architectures have to be designed for each system, such as for the ECS. In this paper, an electric ECS is modeled and then sized and optimized for different sizing scenarios with the aim of minimizing fuel consumption at the aircraft level. For the system and for each component, such as air inlets and heat exchangers, parametric models are developed to allow the prediction of relevant characteristics. These models, developed in order to be adapted to aircraft design issues, are of different types, such as scaling laws and surrogate models. They are then assembled to build a preliminary sizing procedure for the ECS by using a multidisciplinary design analysis and optimization (MDAO) formulation. Results show that the ECS design is highly dependent on the sizing scenario considered. An approach to size the ECS globally with respect to all the sizing scenarios leads to an ECS that accounts for around 200 N of drag, 190 kW of electric power, and 1500 kg of mass for the CeRAS aircraft.

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Numerical Investigation of a Naca Air Intake for a Canard Type Aircraft

Abstract: Abstract-The

Cited by 3 publications

References 2 publications

A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

A Numerical Approach for Implementing Air Intakes in a Canard Type Aircraft for Engine Cooling Purposes

The development of an experimental aerodynamics research center in Brazil

Modeling and Design Optimization of an Electric Environmental Control System for Commercial Passenger Aircraft

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