Effect of Distributed Suction on the Development of Disturbances on the Wing Profile

2020 ◽  
Vol 65 (4) ◽  
pp. 157-160
Author(s):  
G. R. Grek ◽  
M. M. Katasonov ◽  
V. V. Kozlov ◽  
V. I. Kornilov
Keyword(s):  
Wing Profile

Line mixing effects in the 0003–0000 band of CO2 in helium. III. Energy corrected sudden simultaneous fit of linewidths and near wing profile

1994 ◽  
Vol 101 (8) ◽  
pp. 6552-6558 ◽  
Author(s):  
J. Boissoles ◽  
F. Thibault ◽  
R. Le Doucen ◽  
V. Menoux ◽  
C. Boulet
Keyword(s):  
Mixing Effects ◽  
Wing Profile ◽  
Line Mixing

Thermal and Fluid Dynamic Analysis on Impinging Jet for Aircraft Anti-Icing

2010 ◽  
Author(s):  
Assunta Andreozzi ◽  
Fabio Lucibello ◽  
Oronzio Manca ◽  
Sergio Nardini ◽  
Mario Roma
Keyword(s):  
Fluid Dynamic ◽  
Three Dimensional ◽  
Impinging Jet ◽  
Impinging Jets ◽  
Wing Surface ◽  
Temperature Fields ◽  
Ice Formation ◽  
Computational Domain ◽  
System A ◽  
Wing Profile

Ice formation on airplane wing profile is a very dangerous condition because of the change in the profile aerodynamic, so it’s necessary to avoid ice formation on the wings. The hardest condition ice formation are at altitudes between 10.000 and 15.000 ft and at temperature between 0° C and −15° C, because they are particularly suitable for ice formation. In this paper an anti-icing system based on hot air impinging jets on internal wing surface is analyzed in order to check the efficiency of the system. A numerical model is given in order to evaluate the thermal and fluid dynamic behaviors of the impinging jet inside the wing panel. A wing profile with an angle of attack of 4.50° is taken into account with a free stream temperature of 258 K. A piccolo tube with a diameter of 1.00 inch and air temperature of 523 K and at variable distance from the wall of the wing profile, is considered for anti-icing system. A structured mesh is used in the discretization of the computational domain for the two-dimensional and three-dimensional case. A steady state solution with k-ε RNG turbulent model has been found. Numerical simulations of a two and a three dimensional model of an aircraft wing has been carried out taking into account the external convective exchange by means of an average coefficient on the external surface and thermo-fluid dynamic field inside the wing due to the anti-icing system. The analysis is performed by means of the FLUENT code in order to find the optimal geometrical configuration to avoid the ice formation on the external wing surface. Results are presented in terms of temperature fields and wall temperature and air velocity profiles along the wing surfaces.

scholarly journals МОДЕЛЮВАННЯ ВЗАЄМОДІЇ КРИЛЕВОГО ПРОФІЛЮ З ДОЩОВИМ ПОТОКОМ

2020 ◽  
pp. 36-41
Author(s):  
Сергей Евгеньевич Aгеев ◽  
Юрий Петрович Миляев
Keyword(s):  
Water Film ◽  
Aerodynamic Characteristics ◽  
Negative Consequences ◽  
Wing Profile ◽  
Air Interface ◽  
Adopted Model ◽  
Semi Empirical ◽  
Relationship Of ◽  
Surface Tension Forces ◽  
The Relationship

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.

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

2020 ◽  
pp. 58-69
Author(s):  
Andrey N. Luchkov ◽  
Evgeny V. Zhuravlev ◽  
Egor Y. Cheban
Keyword(s):  
Drag Coefficient ◽  
Earth Surface ◽  
Drag Coefficients ◽  
End Plate ◽  
Induced Drag ◽  
The Earth ◽  
Wing Profile

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.

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.

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