scholarly journals Numerical Simulation for Engine/Airframe Interaction Effects of the BWB300 on Aerodynamic Performances

2019 ◽  
Vol 2019 ◽  
pp. 1-15 ◽  
Author(s):  
Gang Yu ◽  
Dong Li ◽  
Yue Shu ◽  
Zeyu Zhang
Keyword(s):  
Numerical Simulation ◽  
High Speed ◽  
Separated Flow ◽  
Simulation Method ◽  
Interaction Effects ◽  
Surface Flow ◽  
Concept Design ◽  
Aerodynamic Forces ◽  
Low Speed ◽  
Aerodynamic Performances

The engine/airframe interaction effects of the BWB300 on aerodynamic performances were analyzed by using the numerical simulation method. The BWB300 is a 300-seat Blended Wing Body airplane designed by the Airplane Concept Design Institute of Northwestern Polytechnical University. The engine model used for simulation was simplified as a powered nacelle. The results indicated the following: at high speed, although the engine/airframe interaction effects on the aerodynamic forces were not significant, the airframe’s upper surface flow was greatly changed; at low speed, the airframe’s aerodynamic forces (of the airplane with/without the engine) were greatly different, especially at high attack angles, i.e., the effect of the engine suction caused the engine configuration aerodynamic forces of the airframe to be bigger than those without the engine; and the engine’s installation resulting in the different development of flow separation at the airframe’s upper surface caused greater obvious differences between the 2 configurations at high angles and low speed. Moreover, at low-speed high attack angles, the separated flow from the blended area caused serious distortion at the fan inlet of the engine.

scholarly journals Simulation on Powered Effects of BWB at Take-off Condition

2020 ◽  
Vol 38 (2) ◽  
pp. 231-237
Author(s):  
Gang Yu ◽  
Dong Li ◽  
Zeyu Zhang
Keyword(s):  
Numerical Simulation ◽  
Boundary Conditions ◽  
Simulation Method ◽  
Aerodynamic Characteristics ◽  
Concept Design ◽  
Aerodynamic Forces ◽  
Design Institute ◽  
Power Effect ◽  
Flow Through ◽  
Engine Power

The influence of engine powered effects on aerodynamic characteristics of BWB300, which was designed by the Airplane Concept Design Institute of Northwestern Polytechnical University, at take-off condition was analyzed by using the numerical simulation method. Firstly, the method of using the inlet and exhaust boundary conditions to analyze the powered engine was validated. Then, the engine powered effects on BWB300 aerodynamic characteristics at take-off condition were researched with flow through nacelle and with powered nacelle. The results indicated that though the powered effect changing the value of aerodynamic forces, there was no change in the aerodynamic curve trend. It's recommended that the engine power effect should be considered in numerical simulation by using with powered nacelle to gain more accurate values of aerodynamic forces. Nevertheless, with flow nacelle also could be used to gain some regular results.

Numerical Simulation Method for 3D Low Speed Micro Flapping-Wing with Complex Kinematics

2011 ◽  
Vol 308-310 ◽  
pp. 332-335
Author(s):  
Wen Qing Yang ◽  
Bi Feng Song ◽  
Wen Ping Song ◽  
Zhan Ke Li ◽  
Ya Feng Zhang
Keyword(s):  
Numerical Simulation ◽  
Numerical Method ◽  
Stokes Equations ◽  
Simulation Method ◽  
Flapping Wing ◽  
Design Tool ◽  
Navier Stokes ◽  
Low Speed ◽  
Wing Motion ◽  
Numerical Simulation Method

A numerical simulation method is presented in this paper for 3D low speed micro flapping-wing with complex kinematics. The main characteristics for the numerical simulation of Flapping-wing Micro Air Vehicle (FMAV) include: low speed, big range of wing motion, and complex kinematics. The low speed problem is solved by preconditioning method. The big range of wing motion problem is solved by chimera grid system. The problem of complex kinematics is solved by decomposed into three main motions, i.e. plunging, pitching, and swing respectively. The numerical method is solving the Reynolds Averaged Navier-Stokes equations for the viscous flow over micro flapping-wing. The numerical method of this paper is validated by good accordance with experimental results of reference. This method can used to simulate the aerodynamic performance of micro flapping-wing with complex kinematics in low speed and is helpful to the FMAV designers as a design tool.

Experiment and Numerical Simulation of Extrudate Swell in the Polymer Extrusion Process

2011 ◽  
Vol 314-316 ◽  
pp. 401-404 ◽  
Author(s):  
Min Zhang ◽  
Chuan Zhen Huang ◽  
Guo Wen Chen ◽  
Yu Xi Jia
Keyword(s):  
Numerical Simulation ◽  
High Speed ◽  
Three Dimensional ◽  
Simulation Method ◽  
Extrusion Process ◽  
High Speed Photography ◽  
The Finite Element Method ◽  
Polymer Extrusion ◽  
Extrudate Swell ◽  
Rate Profile

The extrudate swell of the polymer extrusion process was studied with the experiment and simulation method. The extrudate swell process was recorded by the high-speed photography apparatus. The swell rate at the different time was calculated. It is found that the extrudate swell rate increase at the first five seconds. The maximum swell rate is about 4.37%. The three-dimensional numerical simulation model of the experiment die path was founded. The extrusion process including the extrudate swell was simulated used the Finite Element Method. Such simulated results as the velocity vector, the shear rate profile and the end of the swell zone were analyzed. The extrudate swell end got by the simulation is similar with the experiment result.

Aerodynamic Heating Numerical Simulation of Terminal-Sensitive Projectile at Deceleration and Despinning Trajectory

2013 ◽  
Vol 376 ◽  
pp. 317-322
Author(s):  
Jun Zhang ◽  
Rong Zhong Liu ◽  
Rui Guo ◽  
Xiao Dong Ma
Keyword(s):  
Numerical Simulation ◽  
High Speed ◽  
Thermal Protection ◽  
Thermal Characteristics ◽  
Simulation Method ◽  
Aerodynamic Heating ◽  
Transient Temperature ◽  
Physical Parameters ◽  
Temperature Distributions ◽  
Infrared Signature

Aero-heating problem severely affects the performance of terminal-sensitive projectile (TSP) when projected out of the carrier capsule by the gunpowder gas at a high speed. In this paper, based on the typical ballistic data and airflow physical parameters at deceleration and despinning trajectory, the aerodynamic thermal characteristics of a TSP was simulated by Fluent, and the transient temperature distributions were obtained under the different flying conditions. Finally, we got stagnation temperatures by the numerical simulations which were similar to those by the engineering evaluation, and demonstrate the effectiveness of the simulation method. The results are valuable to the research of thermal protection and infrared signature of TSP.

scholarly journals A method of numerical simulation of flow separation at the inlet of a circular thin-walled pipe

2016 ◽  
pp. 189-196
Author(s):  
К.И. Логачев ◽  
О.А. Аверкова ◽  
А.К. Логачев ◽  
Е.И. Толмачева ◽  
А.С. Горлов
Keyword(s):  
High Speed ◽  
Separated Flow ◽  
Simulation Method ◽  
Quantitative Agreement ◽  
Vortex Rings ◽  
Incident Flow ◽  
Discrete Vortex ◽  
Qualitative And Quantitative ◽  
Thin Walled Pipe ◽  
Thin Walled

Разработан метод математического моделирования, вычислительный алгоритм и программа для расчета отрывного течения на входе в круглый всасывающий патрубок с тонкими стенками при наличии как высокоскоростного, так и низкоскоростного набегающего потока. Для построения дискретной модели используются стационарные дискретные вихревые кольца. Адекватность разработанного метода подтверждается удовлетворительным качественным и количественным согласованием с результатами расчетов других авторов. A mathematical simulation method, a computational algorithm and a software program are developed to calculate a separated flow at the inlet of a circular thin-walled pipe in the case of a high-speed or low-speed incident flow. In order to construct a discrete model, the stationary discrete vortex rings are used. The adequacy of the proposed method is confirmed by the satisfactory qualitative and quantitative agreement with the numerical results obtained by other authors.

scholarly journals Features of high-speed aircraft numerical simulation

2020 ◽  
Author(s):  
M.M. Alekseeva ◽  
N.A. Brykov ◽  
I.A. Vikhrova
Keyword(s):  
Numerical Simulation ◽  
Gas Dynamics ◽  
High Speed ◽  
Simulation Method ◽  
High Speed Flow ◽  
Flight Tests ◽  
High Speeds ◽  
Physical Experiments ◽  
Speed Flow ◽  
Flow Around A Body

Currently, the creation of new high-speed aircraft is of great interest. The development of such aircraft is associated with the need for experiments and flight tests. The organization of real physical experiments in the field of high speeds is fraught with significant difficulties that can be solved using the numerical simulation method, which makes it possible to significantly simplify the process of creating new products. When developing a high-speed aircraft, it is necessary to take into account the specific aerodynamic and thermophysical features of the processes occurring on the surface of the aircraft and in the shock layer. In this paper, the features of the processes at high speeds are considered on the example of solving the external and internal problems of the gas dynamics of an aircraft. Based on the specifics of these processes, we built a mathematical model that allows us to study the aerodynamics of a high-speed flow around a body in dense layers of the atmosphere and the processes that occur in the combustion chamber.

scholarly journals Dimensioning of Fairway Bends—Kinematic Method of Numerical Simulation

2020 ◽  
Vol 8 (2) ◽  
pp. 138
Author(s):  
Stanisław Gucma ◽  
Marcin Przywarty ◽  
Jan Dzwonkowski ◽  
Mateusz Bilewski
Keyword(s):  
Numerical Simulation ◽  
Numerical Simulations ◽  
Simulation Method ◽  
High Accuracy ◽  
Concept Design ◽  
Exact Simulation ◽  
Centre Of Gravity ◽  
Kinematic Method ◽  
Low Costs ◽  
Simulation Results

The article presents a new kinematic method of numerical simulation intended for establishing dimensions of safe manoeuvring areas of bends in various types of fairways for vessels of specific parameters. The method consists of multiple numerical simulations of a ship’s passage (ship’s centre of gravity) through a bend, representing the entire physically possible movement of the ship, and an analysis of simulation results. The developed method was verified on the bends of the Świnoujście–Szczecin fairway, by comparing the results to the exact simulation method of a ship’s movements. The relatively high accuracy and low costs of the method allow it to be used in a concept design of built or modern waterway systems.

scholarly journals The Design and Testing of a Radial Flow Turbine for Aerodynamic Research

1991 ◽  
Author(s):  
I. Huntsman ◽  
H. P. Hodson ◽  
S. H. Hill
Keyword(s):  
High Speed ◽  
Large Scale ◽  
Three Dimensional ◽  
Surface Flow ◽  
Stream Line ◽  
Flow Visualisation ◽  
Gas Generator ◽  
Low Speed ◽  
Scaling Parameters ◽  
Design And Testing

This paper describes the design of a high-speed radial inflow turbine for use as part of a gas-generator, and the design of a large-scale (1.2 m tip dia.) low-speed model of the high-speed turbine. Stream-line curvature throughflow, two-dimensional blade-to-blade and fully three-dimensional inviscid and viscous calculation methods have been used extensively in the analysis of the designs. The use of appropriate scaling parameters and their impact on turbine performance is discussed. A simple model shows, for example, how to model the blade lean in the inducer which serves to balance the effect of meridional curvature at inlet to the rotor and can be used to unload the rotor tip. A brief description of the low speed experimental facility is followed by a presentation and discussion of experimental results. These include surface flow visualisation patterns on both the rotor and stator blades and blade row exit traverses.

Numerical Simulation of Dynamic Response of Planing Craft Sailing in Calm Water

2014 ◽  
Vol 590 ◽  
pp. 37-41
Author(s):  
Yu Min Su ◽  
Yun Hui Li ◽  
Hai Long Shen
Keyword(s):  
Numerical Simulation ◽  
Empirical Formula ◽  
High Speed ◽  
Evaluation Method ◽  
Simulation Method ◽  
Experimental Results ◽  
Planing Craft ◽  
Calm Water ◽  
Performance Evaluation Method ◽  
Good Agreement

In order to forecast the sailing response of planing craft at high speed rapidly and accurately, CFD code Fine/Marine solver was used to calculate the resistance and sailing attitude of a high-speed planing craft, then the numerical results were compared with experimental results and empirical formula results. The results showed that resistance error calculated by Fine/Marine was between 5% and 10%, trim and heave results were in good agreement with experimental results, and had greater accuracy compared with the empirical formula results. The feasibility of this numerical simulation method was validated and this method provided an effect performance evaluation method for new designing planing crafts.

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