scholarly journals Hot-wire measurements of the evolution of total temperature and mass flow pulsations in a modulated 3D supersonic boundary layer

2018 ◽  
Author(s):  
A. D. Kosinov ◽  
G. L. Kolosov ◽  
A. A. Yatskikh ◽  
N. V. Semionov ◽  
Yu. G. Yermolaev ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Mass Flow ◽  
Supersonic Boundary Layer ◽  
Hot Wire ◽  
Total Temperature ◽  
Flow Pulsations

Structure of Acoustic Radiation from an Artificially Excited Supersonic Boundary Layer

2005 ◽  
Vol 4 (3) ◽  
pp. 353-362
Author(s):  
Nickolay V. Semionov ◽  
Alexander D. Kosinov
Keyword(s):  
Boundary Layer ◽  
Free Stream ◽  
Acoustic Radiation ◽  
Supersonic Boundary Layer ◽  
Local Source ◽  
Hot Wire ◽  
Supersonic Wind Tunnel ◽  
Local Disturbance ◽  
Wave Characteristics ◽  
Disturbance Field

An experimental study of the controlled disturbance field, introduced into the free stream with the help of the local source of disturbances, was carried out. The controlled disturbances were excited in the supersonic boundary layer by using a local disturbance generator designed based on the amount of discharge in the chamber in the plate. This process was accompanied by radiation of controlled disturbances into the free stream. This radiation from the system “discharge-boundary layer” was used as controlled disturbances in the free stream. The acoustic nature of the radiation was obtained. The levels, wave characteristics and modes of the artificial fluctuations have been obtained by hot-wire measurements in the free stream of the supersonic wind tunnel at a Mach number of 2.

Quantitative Hot-Wire Measurements in Supersonic Boundary Layers

2003 ◽  
Author(s):  
Eric H. Matlis ◽  
Thomas C. Corke
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Experimental Measurements ◽  
Hot Wire ◽  
Suction System ◽  
Time Resolved ◽  
Wave Numbers ◽  
The Mean ◽  
Sharp Cone ◽  
Langley Research Center

Mean and time-resolved measurements in a supersonic boundary layer were performed in the Mach 3.5 quiet tunnel facility at the NASA Langley Research Center. This facility uses an annular bleed suction system to remove the turbulent boundary layer, thus reducing the disturbance intensities in the measurement region. A frequency-compensatedconstant current hot-wire anemometer was used to obtain fluctuation data in the boundary layer of a sharp cone at zero angle of attack. The hotwire was calibrated against the mean mass-flux profiles provided by solutions of the similarity profiles for compressible Blasius flow. A stability analysis code provided by Langley was used to solve parabolized stability equations to provide predictions of the most amplified wave-numbers, frequencies, and N-factors for the Tollmien-Schlicting instability. The results from these computations are compared to the experimental measurements performed with the anemometer. In addition, these measurements are compared to spectra obtained in high-disturbance conditions with the bleed system turned off.

Laser Velocimeter and Hot-wire Anemometer Comparison in a Supersonic Boundary Layer

AIAA Journal ◽  
1975 ◽  
Vol 13 (4) ◽  
pp. 512-515 ◽  
Author(s):  
DENNIS A. JOHNSON ◽  
WILLIAM C. ROSE
Keyword(s):  
Boundary Layer ◽  
Supersonic Boundary Layer ◽  
Hot Wire

scholarly journals The evolution of mass flow and total temperature pulsations in flat plate boundary layer at M=2.5

2017 ◽  
Author(s):  
Aleksey A. Yatskikh ◽  
Gleb L. Kolosov ◽  
Alexander D. Kosinov ◽  
Yury G. Yermolaev ◽  
Nickolay V. Semionov ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Mass Flow ◽  
Plate Boundary ◽  
Temperature Pulsations ◽  
Total Temperature ◽  
Flat Plate Boundary Layer

scholarly journals Development of Disturbances in the Supersonic Boundary Layer under Helium Injection from the Surface

2022 ◽  
Vol 16 (2) ◽  
pp. 41-47
Author(s):  
V. I. Lysenko ◽  
B. V. Smorodsky ◽  
A. D. Kosinov
Keyword(s):  
Boundary Layer ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Supersonic Boundary Layer ◽  
Natural Disturbances

Experiments on the influence of distributed injection of helium on the development of the supersonic boundary layer unstable disturbances have been performed. It is revealed, that injection of helium in a certain range of blowing mass flow rate, leads to a certain decrease of spatial amplification rates of natural disturbances.

scholarly journals Исследование влияния параметров импульсного разряда на порождаемые в сверхзвуковом пограничном слое локализованные возмущения

2019 ◽  
Vol 45 (5) ◽  
pp. 59
Author(s):  
А.А. Яцких ◽  
Ю.Г. Ермолаев ◽  
А.Д. Косинов ◽  
Н.В. Семенов
Keyword(s):  
Boundary Layer ◽  
Pulse Discharge ◽  
Experimental Studies ◽  
Supersonic Boundary Layer ◽  
Oncoming Flow ◽  
Hot Wire ◽  
Flow Pulsation ◽  
Pulsed Glow Discharge ◽  
Impulse Function ◽  
Mach Numbers

AbstractThe results of experimental studies of the effect of the duration and current of a pulsed glow discharge on the generation of localized disturbances in the supersonic boundary layer of a flat plate at Mach numbers of the oncoming flow M = 3 and 4 have been presented. Flow pulsation measurements were performed by a hot-wire anemometer. It has been found that an increase in the duration of the impulse function leads to an increase in the amplitude and time scales of the perturbations that are generated in the boundary layer. An increase in the current of the pulse discharge leads to an increase in the amplitude of the generated pulsations. The propagation velocities in the boundary layer of localized perturbations at different Mach numbers of the oncoming flow have been estimated.

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