The study of aerodynamic characteristics of the wing with tips of different shapes

2019 ◽  
Author(s):  
V.O. Moskalenko ◽  
A.V. Tsoy ◽  
A.A. Nedogarok
Keyword(s):  
Numerical Calculation ◽  
Numerical Experiment ◽  
Fuel Efficiency ◽  
Base Material ◽  
Aerodynamic Characteristics ◽  
Research Teams ◽  
Different Shapes ◽  
Aerodynamic Quality

Winglets or wingtips of various types are a common means of improving fuel efficiency of a modern aircraft. Aircraft manufacturers and research teams are actively searching for new types of winglets. The purpose of this work is to compare the efficiency of a number of used and promising end superstructures of different shapes. The paper presents the results of a numerical experiment to assess the effect of the four types of wingtips on the isolated wing aerodynamic characteristics. The increase in aerodynamic quality and the change in the inductive resistance of the wing, as well as the intensity of the end vortices, are compared. Validation of the numerical calculation and analysis of the results are performed. The article can be used as a base material for further research of methods for reducing inductive resistance and improving the efficiency of aircraft of different configurations.

scholarly journals Aerodynamic characteristics of detachable fairing shells in a subsonic incompressible flow

2019 ◽  
Author(s):  
Yu.V. Grebeneva ◽  
A.Yu. Lutsenko ◽  
A.V. Nazarova
Keyword(s):  
Flow Simulation ◽  
Aerodynamic Characteristics ◽  
Simulation Software ◽  
Stream Velocity ◽  
Normal Forces ◽  
Pitch Moment ◽  
Lift Off ◽  
Windward Surface ◽  
Aerodynamic Quality

The purpose of the work was to mathematically simulate the flow around the fairing shell of the launch vehicle at a low subsonic free-stream velocity in the α = 0...360° angle-of-attack range. The calculations were performed using the SolidWorks Flow Simulation software package and the open source OpenFoam package based on the use of numerical methods for simulating the motion of liquid and gas. Within the research, we obtained the flow patterns and the aerodynamic coefficients of the longitudinal and normal forces, the pitch moment, and calculated the aerodynamic quality of the shell. Furthermore, we determined the positions of the stable equilibrium of the model and revealed the features of the flowing around the shell of the combined form at flow from the convex and concave sides. Next, we analyzed the leeward lift-off zones and the zones with increased pressure on the windward surface during flow from the concave side. Finally, we compared the obtained characteristics with the experimental data of TsAGI.

scholarly journals Experiments and numerical calculation to determine aerodynamic characteristics of flows around 3D wings

2014 ◽  
Vol 36 (2) ◽  
pp. 133-143 ◽  
Author(s):  
Nguyen Hong Son ◽  
Hoang Thi Bich Ngoc ◽  
Dinh Van Phong ◽  
Nguyen Manh Hung
Keyword(s):  
Numerical Calculation ◽  
Wind Tunnel ◽  
Pressure Distribution ◽  
Numerical Method ◽  
Aerodynamic Characteristics ◽  
Numerical Results ◽  
Computational Method ◽  
Wing Surface ◽  
Thickness Profile

The report presents method and results of experiments in wind tunnel to determine aerodynamic characteristics of 3D wings by measuring pressure distribution on the wing surfaces. Simultaneously, a numerical method by using sources and doublets distributed on panel elements of wing surface also is carried out to calculate flows around 3D wings. This computational method allows solving inviscid problems for wings with thickness profile. The experimental and numerical results are compared to each other to verify the built program that permits to extend the range of applications with the variation of wing profiles, wing planforms, and incidence angles.

Improving Design of Muffler Based on Three-Dimension Numerical Calculation of Fluid and Sound Field

2011 ◽  
Vol 295-297 ◽  
pp. 2300-2303
Author(s):  
Hai Jun Zhao ◽  
Jia Dong Chang ◽  
Hong Jie Zhao
Keyword(s):  
Numerical Calculation ◽  
Environmental Pollution ◽  
Rotational Speed ◽  
Pressure Loss ◽  
Sound Field ◽  
Original Structure ◽  
Three Dimension ◽  
Vehicle Noise ◽  
Important Method ◽  
Aerodynamic Quality

Presence problem of exhaust muffler is anal sized, using three three-dimension numerical calculation of fluid and sound field improvement on original structure is performed, and improving results are certificated. It is shown that insert loss under every rotational speed all reach to the standard of 28dB（A）, and the noises of stationary end tube on the attention frequency band are all smaller than 5 dB（A） , and its pressure loss is decreased by about 32% than 7.6kPa of original structure muffler. So performance of the muffler is evidence increased, an important method is provided for decreasing whole vehicle noise, improving aerodynamic quality and reducing environmental pollution.

Passive Morphing Airfoil With Honeycombs

2011 ◽  
Author(s):  
Hyeonu Heo ◽  
Jaehyung Ju ◽  
Doo-Man Kim ◽  
Chang-Soo Jeon
Keyword(s):  
Shape Change ◽  
Fuel Efficiency ◽  
Aerodynamic Characteristics ◽  
Structural Performance ◽  
Element Analysis ◽  
Structural Shape ◽  
Aerodynamic Loads ◽  
Structure Interaction ◽  
Morphing Structure ◽  
Passive Morphing

A passive morphing may improve the aerodynamic characteristics through structural shape change by aerodynamic loads during the flight, resulting in improving fuel efficiency. The passive morphing structure should have a capability to be highly deformed while maintaining a sufficient stiffness in bending. Honeycombs may be good for controlling both stiffness and flexibility. This paper investigates a honeycomb airfoil’s static deformations through the fluid-structure interaction using computational fluid dynamics and structural finite element analysis. The structural performance will be investigated with varying honeycomb geometries including regular, auxetic and chiral meso-structures.

scholarly journals Numerical investigation of hybrid blend design target bullets

2018 ◽  
Vol 172 ◽  
pp. 01006 ◽  
Author(s):  
V R Muruganantham ◽  
T Babin
Keyword(s):  
Dissipation Rate ◽  
Dynamic Performance ◽  
Aerodynamic Characteristics ◽  
High Energy ◽  
Aerodynamic Design ◽  
Turbulent Dissipation ◽  
The Past ◽  
Different Shapes ◽  
Performance Capability ◽  
Materials Used

In the past few decades, researchers are involved in the studies of high-energy penetrator geometry and also the materials used for causing brutal damages on enemy targets. The highly focused area in this field is the shape of the nose and penetration angle of the penetrator. Hybrid blend design target bullets is one among the best aerodynamic design as it is having two different shapes within the nose. The design of these bullets plays an influential role in terms of aerodynamic characteristics and its dynamic performance capability on hitting the targets. Objective of this research is to perform a comparative analysis of 3 different geometrically varied shapes of these bullets by numerical simulation using CFD, based on its performance characteristics such as aerodynamic co-efficients, shock wave existence, Turbulent dissipation rate and normal drag force on the bullet surface.

CALCULATION OF THE AERODYNAMIC CHARACTERISTICS OF A UAV TAKING INTO ACCOUNT THE INSTALLED ELEMENTS OF ANTI-ICE SYSTEM IN A VIRTUAL ENVIRONMENT XFLR5

2019 ◽  
Vol 12 (2) ◽  
pp. 66-71
Author(s):  
А. Мельников ◽  
A. Mel'nikov
Keyword(s):  
Virtual Environment ◽  
Unmanned Aerial Vehicle ◽  
Aerodynamic Characteristics ◽  
Wing Profile ◽  
Aerial Vehicle ◽  
Aerodynamic Quality

Based on the geometric dimensions of the CLARK-Y wing profile used in the design of various aircraft models, the calculations of its main aerodynamic characteristics were carried out. Taking into account the developed method of protecting the wing of an unmanned aerial vehicle (UAV) from icing, changes were made to the profile structure taking into account the installation features of the anti-icing system (AIS) elements. Both profiles are digitally entered into the XFLR5 program, where the aerodynamic quality of the wing was calculated before installing the AIS elements and with the elements installed. Wing polarities were obtained, on the basis of which conclusions were drawn about the possibility of using the developed AIS.

The Analysis of Aerodynamic Characteristics of the High-Speed Train in Different Railway Conditions under Crosswinds

2013 ◽  
Vol 774-776 ◽  
pp. 58-63
Author(s):  
Kun Ye ◽  
Ren Xian Li
Keyword(s):  
Numerical Calculation ◽  
Wind Speed ◽  
Traffic Safety ◽  
Linear Relation ◽  
High Speed ◽  
Aerodynamic Characteristics ◽  
High Speed Train ◽  
Transverse Loads ◽  
Train Speed ◽  
Calculation Models

The numerical calculation models of the high-speed train in the straight and different radius curve railway are established. Author calculated transverse forces (moments) acting on the three sections (first train, middle train and rear train). At the same time, under with the shelter wind wall and without the wall, the change trends of side forces coefficients and rolling moments coefficients of trains with the train speed and the transverse wind speed are analyzed. Results show that, in the straight railway and curve railway, transverse loads coefficients increase with the increase of the transverse wind speed and decrease with the increase of the train speed. The transverse forces (moments) of the three sections of the train with the shelter wind wall are opposite to that without the wall. Traffic safety under crosswinds focuses on the rear train with the shelter wind wall and focuses on the first train without the wall. At the same train speed and transverse wind speed, side forces and rolling moments of trains in curve railway is greater than that of trains in straight railway. Absolute values of transverse loads coefficients decreased gradually with the increase of the radius of the curve, and their relationship basically is the linear relation.

scholarly journals A Study of the Aerodynamic Characteristics of the Rocket Fairing Door Using Conical Means of Passive Stabilization

2019 ◽  
pp. 66-75
Author(s):  
A.Y. Lutsenko ◽  
D.K. Nazarova ◽  
D.M. Slobodyanyuk
Keyword(s):  
Video Camera ◽  
Aerodynamic Characteristics ◽  
Angle Sensor ◽  
Flow Models ◽  
Subsonic Wind Tunnel ◽  
Visualization Experiment ◽  
Measuring Experiment ◽  
Passive Stabilization ◽  
Aerodynamic Quality

In the article, the aerodynamic characteristics of a detachable fairing door model are investigated with the use of passive stabilization means, which are conical bodies with flexible and rigid connections. Two types of experiments were conducted in a subsonic wind tunnel to determine the balancing angles of attack: a visualization experiment (using a video camera) and a measuring experiment (using the angle sensor). Mathematical flow models and aerodynamic quality values were obtained. The change in the balancing angle of attack and the corresponding aerodynamic quality of the studied combinations with respect to the base model were analyzed. Comparative characteristics of the considered stabilization variants were presented.

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