INFLUENCE OF THE DISTANCE TO THE INTERFACE AND THE SOLID COVER ON THE HYDRODYNAMIC CHARACTERISTICS OF THE WING PROFILE IN A TWO-LAYER FLOW

The motion of the hydrofoil in the liquid flow between the solid cover and the interface of liquids with significantly different densities is modeled. The method of boundary singularities is applied. The results of calculations of the lifting force, hydrodynamic moment, and wave amplitude at the interface depending on the immersion of the hydrofoil are obtained and analyzed.

Design And Analysis of CFD Geometry Configuration Canted Winglet Toward Aerodynamic Characteristic on Wing Profil of The UAV LSU-05

The wing is part of an aircraft or UAV which has a function as a major component of producing lift, therefore if a problem occurs such as a vortex at the end of the wing it will affect its performance capability. This study aims to determine the condition of the airflow, the value of induced drag, and the selection of the design of the wingtip devices on the wing profile of the UAV LSU-05. The method used is numerical or computational methods with CFD-based software to predict the aerodynamic characteristics and phenomenon of airflow around the wing with wingtip devices and without it. The model used in this study is a half-wing LSU-05 with NACA 4415 made with CATIA V5R20 software and the simulation uses ANSYS CFX 17.1. Based on the previous simulation results, it was found that the application of the canted winglet geometry to the wing profile of the UAV LSU-05 affects the coefficient lift (CL)/coefficient drag (CD) value and induced drag. Whereas the coefficient lift (CL)/coefficient drag (CD) value before using the canted winglet was 18.904 after application, increased to 21.616, this causes the induced drag value to change inversely with the coefficient lift (CL)/coefficient drag (CD) value where the value before the application was 30.4181 N to 29.0566 N.Keywords: Canted Winglet, CFD, Wing

The estimation of applicability concerning the methods for calculation of asimple wing with wingtips inductive resistance during the flight near the earth surface

One of the problems in the hovercrafts design is to dtermine the aerodynamic charactreistics of the wing near the earth surface. In this article, 4 methods for calculating the induced drag coefficient Cxi of a simple airfoil with an end plate at different relative heights were considered. Four methods of induced drag coefficient determination were considered for different relative flight’s heights. Calculations were performed according to the Phillips, Wieselsberge, Panchenkov-Surzhik, Mantle methods for the TsAGI-876 wing profile. The calculated values of induced drag coefficients were compared with the experimental wind tunnel’s data at the Central Aerohydrodynamic Institute.

МОДЕЛЮВАННЯ ВЗАЄМОДІЇ КРИЛЕВОГО ПРОФІЛЮ З ДОЩОВИМ ПОТОКОМ

The subject of the study is the analysis of the multilateral impact of rainfall on the flight of a modern aircraft. When considering various factors of this impact, it was found that the main negative consequences of the interaction of the aircraft with the rain flow are the formation of a thin layer of water on its surface, which under the influence of drops and surface tension forces changes the configuration of the wing profile, causing loss of load-bearing properties and an increase in frontal aircraft resistance. The influence of rain flowing around the bearing surfaces can be reduced to taking into account changes in the characteristics of the surface and the flow of the airflow. The goal is to develop a model for the interaction of modern wing profiles with rain flow. The task is to determine the amount of water deposited on the surface of the wing profile, calculate the parameters of the water film formed on its surface, and as a result of this, change the tangential stress at the liquid-air interface. The semi-empirical calculation method used reveals a significant dependence of the amount of precipitated rain water on the surface of modern wing profiles on their geometry and the conditions of interaction with the stream of raindrops. The result of this work is the resulting model, which allows you to simulate the flow conditions around the wing profile in the rain stream and evaluate the relationship of rain intensity with the parameters of the water film that forms on the profile. Conclusions. An analysis of the features of the rain film flow over the surface of the wing profile and its effect on the parameters of the boundary layer shows the negative nature of the effect of rainfall on the aerodynamics of the aircraft. The results obtained allow us to judge the reliability of using the adopted model to calculate the effect of rain on the aerodynamic characteristics of wing profiles, and the possibility of using the results to determine the dependence of the aerodynamic characteristics of wing profiles on the conditions of rainfall molasses.

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

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.