Development of Velocity and Temperature of the Flow behind a Moving Shock Wave in a duct

1976 ◽  
Vol 190 (1) ◽  
pp. 437-446 ◽  
Author(s):  
B. E. L. Deckker ◽  
M. E. Weekes
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Velocity Profile ◽  
Temperature Profile ◽  
Wave Front ◽  
Rectangular Duct ◽  
Hot Wire ◽  
Atmospheric Air ◽  
Steady Velocity ◽  
Boundary Layer Edge

SYNOPSIS Development of the velocity and temperature of the flow behind a shock wave propagating in atmospheric air in a smooth rectangular duct has been followed by hot wire anemometry. Averaged data were analyzed iteratively to yield the velocity and temperature at several points. Property distributions close to the wave front are non-uniform. Far from the front, the steady velocity profile is approximately the same as for flow in a rectangular duct. The temperature profile develops in a similar manner to the velocity but it is difficult to define the boundary layer edge because the temperature decreases with time.

Wave reflexion near a wall

1951 ◽  
Vol 47 (3) ◽  
pp. 528-544 ◽  
Author(s):  
A. Robinson
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Velocity Profile ◽  
Shear Layer ◽  
Continuous Wave ◽  
Rigid Wall ◽  
Main Flow ◽  
Supersonic Velocity ◽  
Main Stream ◽  
Numerical Examples

AbstractThe field of flow due to a shock wave or expansion wave undergoes a considerable modification in the neighbourhood of a rigid wall. It has been suggested that the resulting propagation of the disturbance upstream is largely due to the fact that the main flow in the boundary layer is subsonic. Simple models were produced by Howarth, and Tsien and Finston, to test this suggestion, assuming the co-existence of layers of uniform supersonic and subsonic main-stream velocities. The analysis developed in the present paper is designed to cope with any arbitrary continuous velocity profile which varies from zero at the wall to a constant supersonic velocity in the main stream. Numerical examples are calculated, and it is concluded that a simple inviscid theory is incapable of giving an adequate theoretical account of the phenomenon. The analysis includes a detailed discussion of the process of continuous wave reflexion in a supersonic shear layer.

416 Shock Wave / Turbulent Boundary Layer Interaction in a Supersonic Rectangular Duct

2001 ◽  
Vol 2001 (0) ◽  
pp. 56
Author(s):  
Hiromu SUGIYAMA ◽  
Kazuhide MIZOBATA ◽  
Koichi FUKUDA ◽  
Li Qun Sun ◽  
Kiyokazu ENDO ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Turbulent Boundary Layer ◽  
Rectangular Duct ◽  
Layer Interaction ◽  
Boundary Layer Interaction

scholarly journals Evolution of artificial disturbances in a shear layer at M=1.43

2021 ◽  
Vol 2057 (1) ◽  
pp. 012085
Author(s):  
O I Vishnyakov ◽  
P A Polivanov ◽  
A A Sidorenko
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Mach Number ◽  
Barrier Discharge ◽  
Separation Zone ◽  
Incident Shock ◽  
Incident Shock Wave ◽  
Plate Model ◽  
Hot Wire ◽  
Dielectric Barrier

Abstract The evolution of artificial disturbances in a laminar boundary layer on a flat plate model in the presence of an incident shock wave is considered. The flow is supersonic with the freestream Mach number M = 1.43. The study is carried out by hot-wire anemometry. A dielectric barrier discharge is used to generate disturbances. Data on the distribution in space of the average and non-stationary components of the mass flow are obtained. Disturbances created by the discharge and their evolution along the separation zone are recorded.

Shock Wave/Boundary Layer Interaction in a Supersonic Rectangular Duct

2000 ◽  
Vol 2000 (0) ◽  
pp. 3
Author(s):  
Hiromu SUGIYAMA ◽  
Kazuhide MIZOBATA ◽  
Takakage ARAI ◽  
Kiyokazu ENDOH ◽  
Koichi FUKUDA ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Rectangular Duct ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Boundary Layer Interaction ◽  
Wave Boundary

520 Shock Wave / Boundary Layer Interaction in a Supersonic Rectangular Duct : PIV Measurement of the Shock Train

2001 ◽  
Vol 2001.41 (0) ◽  
pp. 186-187
Author(s):  
Takayuki HIROSHIMA ◽  
Hiromu SUGIYAMA ◽  
Kazuhide MIZOBATA ◽  
Koichi FUKUDA ◽  
Li Qun Sun ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Rectangular Duct ◽  
Shock Train ◽  
Layer Interaction ◽  
Wave Boundary Layer ◽  
Piv Measurement ◽  
Boundary Layer Interaction ◽  
Wave Boundary

Experimental Investigation on Boundary Layer Flow Under the Effect of Temperature Gradient in a Smooth Rotating Channel Using Hot-Wire

2018 ◽  
Author(s):  
Gangfu Li ◽  
Zhi Tao ◽  
Huijie Wu ◽  
Ruquan You ◽  
Haiwang Li
Keyword(s):  
Boundary Layer ◽  
Velocity Profile ◽  
Rotation Number ◽  
Viscous Sublayer ◽  
Effect Of Temperature ◽  
Hot Wire ◽  
Mean Velocity ◽  
Heating Section ◽  
Rotation Numbers ◽  
Layer Flow

This experiment measures the temperature and the velocity field synchronously in the boundary layer in a rotating smooth, wall-heated channel using hot-wire. The Reynolds number based on the bulk mean velocity and hydraulic diameter is 19000 and the rotation numbers are 0, 0.07, 0.14, 0.21, 0.28 and 0.35. Four streamwise stations (X/D = 4.06, 5.31, 6.56, 7.81) were investigated. To calibrate the parallel-array hot-wire probe, a heating section is added to the original wind tunnel that could only calibrate the hot-wire at room temperature. Different gas temperatures at the outlet could be obtained by changing the heating power of the heating section. The velocity profiles and the temperature profiles are obtained. It can be seen that the viscous sublayer also exists when the wall is heated, thus the viscous sublayer profile method is also valid when the wall is heated. It is found that the velocity profile near the leading side is more sensitive to the change of rotation number and X/D than the velocity profile near the trailing edge. The critical rotation number phenomenon of velocity profile has also been found in present work. By comparing with the previous work without the wall heated, the influence of both kinds of buoyancy under this condition is discussed. Some explanations are given for the experimental results.

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