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Flowfield characteristics of a transverse jet into supersonic flow with pseudo-shock wave

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Abstract

We performed an experimental investigation of the flowfield of a transverse jet into supersonic flow with a pseudo-shock wave (PSW). In this study, we injected compressed air as the injectant, simulating hydrocarbon fuel. A back pressure control valve generated PSW into Mach 2.5 supersonic flow and controlled its position. The positions of PSW were set at nondimensional distance from the injector by the duct height (x/H) of −1.0, −2.5, and −4.0. Particle image velocimetry (PIV) gave us the velocity of the flowfield. Mie scattering of oil mist only with the jet was used to measure the spread of the injectant. Furthermore, gas sampling measurements at the exit of the test section were carried out to determine the injectant mole fraction distributions. Gas sampling data qualitatively matched the intensity of Mie scattering. PIV measurements indicated that far-upstream PSW decelerated the flow speed of the main stream and developed the boundary layer on the wall of the test section. The flow speed deceleration at the corner of the test section was remarkable. The PSW produced nonuniformity in the main stream and reduced the momentum flux of the main stream in front of the injector. The blowing ratio, defined as the square root of the momentum flux ratio, of the jet and the main stream considering the effect of the boundary layer thickness was shown to be a useful parameter to explain the jet behavior.

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Abbreviations

A :

Area (m2)

d :

Injector diameter (mm)

H :

Height of test section (mm)

h :

Penetration height of injectant (mm)

J :

Jet-to-freestream momentum flux ratio, i.e., dynamic pressure ratio (2)

l :

Width of injectant (mm)

M :

Mach number

r :

Jet-to-freestream blowing ratio (2)

u, v, w :

Velocity components in x, y, z directions, respectively (m/s)

x, y, z :

Cartesian coordinates

ρ :

Density (kg/m3)

δ :

Boundary layer thickness (mm)

ω :

Vorticity (1/s)

c:

Core

e:

Effective

j:

Jet

PSW:

Pseudo-shock wave

sup:

Supersonic state

v:

Vortex

w:

Width

∞:

Freestream property

0:

Stagnation condition

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Authors and Affiliations

  1. Department of Aerospace Engineering, Tohoku University, Sendai, Miyagi, 980-8579, Japan

    H. Yamauchi, B. Choi, K. Takae, T. Kouchi & G. Masuya

Authors
  1. H. Yamauchi
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  2. B. Choi
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  3. K. Takae
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  4. T. Kouchi
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  5. G. Masuya
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Corresponding author

Correspondence to B. Choi.

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Communicated by F. Lu.

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Yamauchi, H., Choi, B., Takae, K. et al. Flowfield characteristics of a transverse jet into supersonic flow with pseudo-shock wave. Shock Waves 22, 533–545 (2012). https://doi.org/10.1007/s00193-012-0384-9

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  • DOI: https://doi.org/10.1007/s00193-012-0384-9

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