Wind tunnel interference on oscillating airfoils in low supersonic flow

1973 ◽  
Vol 16 (1-2) ◽  
pp. 115-126
Author(s):  
M. F. Platzer
Keyword(s):  
Supersonic Flow ◽  
Wind Tunnel

Calculation of the Flow Properties Up- and Downstream of and Within a Supersonic Turbine Cascade

1972 ◽  
Author(s):  
O. K. Lawaczeck
Keyword(s):  
Supersonic Flow ◽  
Wind Tunnel ◽  
Pressure Distribution ◽  
Theoretical Method ◽  
Experimental Results ◽  
Turbine Cascade ◽  
Flow Properties ◽  
Flow Through

This paper deals with the flow through cascades, which have a supersonic flow up- and downstream. A theoretical method is described to calculate, under certain conditions, the flow quantities up- and downstream of and within the cascade and to determine the pressure distribution on the blades. The method is compared with experimental results, carried out in the cascade wind tunnel of the Aero dynamische Versuchsanstalt Göttingen (AVA), Germany.

Solution to Optimize the Airfoils Shapes Placed Into a Supersonic Viscous Flow

2018 ◽  
Author(s):  
Victorita Radulescu
Keyword(s):  
Supersonic Flow ◽  
Wind Tunnel ◽  
Wind Velocity ◽  
Stokes Equations ◽  
Lift Coefficient ◽  
Leading Edge ◽  
Boundary Layer Separation ◽  
Thin Layers ◽  
Supersonic Wind Tunnel ◽  
Edge Zone

To improve the airfoils performances placed in supersonic flow is proposed a method of optimization for their shapes, in order to minimize the effect of the landing vortices. The theoretical modeling starts with the Navier-Stokes equations applied for thin layers, supplemented with additional conditions related to the profile shape. For a proper estimation of efficiency and responses at different flow regime’s conditions, were considered four aerodynamics airfoils, with different shapes and functioning characteristics. Two of them are special shapes of supersonic profiles and the other two deduced by theoretical assessments with an efficient behavior at high Reynolds numbers. The main purpose of this selection was to identify the essential aspects needed to be considered in numerical modeling of the airfoil’s wing shapes, as to assure an optimization of their behavior for different flow conditions. In the supersonic flow, the cross-sections of the wings are thin profiles, mainly symmetric, as to reduce the drag coefficient and to maximize, as possible, the lift coefficient. A supplementary method for the shape calculation of the aerodynamic profiles with small curvature, based on the Fredholm integral equation of the second kind, with a good behavior in the supersonic flow, is presented. Some aspects referring to unsteady flows and air compressibility are considered, as to simulate as much as possible the real, natural conditions. All profiles were tested, firstly, into a subsonic wind tunnel at incidences between 00 – 40 for different values of wind velocity, and secondly, into a supersonic wind tunnel, at the same incidences. The objective was to better understand and analyze the main factors, which influence the aerodynamic of shapes with curvature, and to assure an optimization of their behavior. The purpose of testing these profiles was to estimate a solution to improve the main characteristics, especially into the trailing and leading edges zones. There were also considered the effects of the attack angle, the influence of the wind velocity, air viscosity, and the shape’s curvature, on the vortices development. The obtained results allow a better functioning in supersonic flow regime, by eliminating the adverse pressure gradient and the boundary layer separation, assuring an optimum behavior especially into the leading edge zone.

RESEARCH OF CONICAL BODIES INTERACTIONS WITH IRREGULAR SUPERSONIC FLOW AT SMALL ATTACK ANGLES

2020 ◽  
Author(s):  
Евгений Алексеевич Прокопенко ◽  
Артем Васильевич Шевченко ◽  
Сергей Алексеевич Яшков ◽  
Игорь Анатольевич Дема ◽  
Тимофей Андреевич Житников ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Wind Tunnel ◽  
Stokes Equations ◽  
Navier Stokes ◽  
Perfect Gas ◽  
Navier Stokes Equations ◽  
Mach Numbers ◽  
Experimental Researches

В статье представлены теоретические и экспериментальные исследованиях сверхзвукового потока вблизи конических тел при различных числах Маха. Экспериментальные исследования выполнены с помощью сверхзвуковой атмосферно-вакуумной аэродинамической трубы Военно-космической академии имени А.Ф.Можайского. В основу теоретического исследования положена модель вязкого совершенного газа, описываемая уравнениями Навье-Стокса. The article presents theoretical and experimental researches of supersonic flow near conical bodies at various Mach numbers. Experimental researches were carried out using a supersonic atmospheric-vacuum wind tunnel of Mozhaisky Military Space Academy. The theoretical researches is based on the model of a viscous perfect gas described by the Navier-Stokes equations.

scholarly journals A Study of the Pulsations of Flow in the Settling Chamber and Their Relationship with the Pulsations of the Supersonic Flow

2019 ◽  
Vol 14 (2) ◽  
pp. 77-85
Author(s):  
L. V. Afanasev ◽  
A. A. Yatskih ◽  
A. D. Kosinov ◽  
Yu. G. Yermolaev ◽  
N. V. Semionov ◽  
...  
Keyword(s):  
Experimental Study ◽  
Supersonic Flow ◽  
Wind Tunnel ◽  
Test Section ◽  
Free Stream ◽  
Settling Chamber ◽  
Flow Pulsation ◽  
Supersonic Wind Tunnel ◽  
Flow Pulsations

Experimental study of the influence of flow pulsation in settling chamber on the supersonic free stream disturbances was carried out. Data on the pulsations in the settling chamber and the efficiency of deturbulization system as well as the correlation of pulsations of the flow of settling chamber and flow pulsations in test section of T-325 supersonic wind tunnel of ITAM SB RAS were obtained.

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