Self-sustained oscillations with acoustic feedback take place in a flow over a two-dimensional two-step configuration: a small forward-backward facing step, which we hereafter call a bump, and a relatively large backward-facing step (backstep). These oscillations can radiate intense tonal sound and fatigue nearby components of industrial products. We clarify the mechanism of these oscillations by directly solving the compressible Navier-Stokes equations. The results show that vortices are shed from the leading edge of the bump and acoustic waves are radiated when these vortices pass the trailing edge of the backstep. The radiated compression waves shed new vortices by stretching the vortex formed by the flow separation at the leading edge of the bump, thereby forming a feedback loop. We propose a formula based on a detailed investigation of the phase relationship between the vortices and the acoustic waves for predicting the frequencies of the tonal sound. The frequencies predicted by this formula are in good agreement with those measured in the experiments we performed.

1.
H. H.
Heller
and
W. M.
Dobrzynski
, “
Sound radiation from aircraft wheel-well/landing-gear configurations
,”
J. Aircr.
14
,
768
(
1977
).
2.
O. W.
Mcgregor
and
R. A.
White
, “
Drag of rectangular cavities in supersonic and transonic flow including the effects of cavity resonance
,”
AIAA J.
8
,
1959
(
1970
).
3.
G. B.
Brown
, “
The vortex motion causing edge tones
,”
Proc. Phys. Soc. London
49
,
493
(
1937
).
4.
A.
Powell
, “
On the edge tone
,”
J. Acoust. Soc. Am.
33
,
395
(
1961
).
5.
J. E.
Rossiter
, “
Wind-tunnel experiments on the flow over rectangular cavities at subsonic and transonic speeds
,” Aero. Res. Counc. R&M, No. 3438 (
1964
).
6.
M. A.
Kegerise
,
E. F.
Spina
,
S.
Garg
, and
L. N.
Cattafesta
, “
Mode-switching and nonlinear effects in compressible flow over a cavity
,”
Phys. Fluids
16
,
678
(
2004
).
7.
A. J.
Bilanin
and
E. E.
Covert
, “
Estimation of possible excitation frequencies for shallow rectangular cavities
,”
AIAA J.
11
,
347
(
1973
).
8.
C. K. W.
Tam
and
P. J. W.
Block
, “
On the tones and pressure oscillations induced by flow over rectangular cavities
,”
J. Fluid Mech.
89
,
373
(
1978
).
9.
D. G.
Crighton
, “
The jet edge-tone feedback cycle; linear theory for the operating stages
,”
J. Fluid Mech.
234
,
361
(
1992
).
10.
M. S.
Howe
, “
Edge, cavity and aperture tones at very low Mach numbers
,”
J. Fluid Mech.
330
,
61
(
1997
).
11.
L.
Larcheveque
,
P.
Sagaut
,
I.
Mary
,
O.
Labbe
, and
P.
Comte
, “
Large-eddy simulation of a compressible flow past a deep cavity
,”
Phys. Fluids
15
,
193
(
2003
).
12.
C. W.
Rowley
,
T.
Colonius
, and
A. J.
Basu
, “
On self-sustained oscillations in two-dimensional compressible flow over rectangular cavities
,”
J. Fluid Mech.
455
,
315
(
2002
).
13.
T.
Colonius
and
S. K.
Lele
, “
Computational aeroacoustics: progress on nonlinear problems of sound generation
,”
Prog. Aerosp. Sci.
40
,
345
(
2004
).
14.
S. K.
Lele
, “
Compact finite difference schemes with spectral-like resolution
,”
J. Comput. Phys.
103
,
16
(
1992
).
15.
K.
Matsuura
and
C.
Kato
, “
Large-eddy simulation of compressible transitional flows in a low-pressure turbine cascade
,”
AIAA J.
45
,
442
(
2007
).
16.
D. V.
Gaitonde
and
M. R.
Visbal
, “
Pad-type higher-order boundary filters for the Navier-Stokes equations
,”
AIAA J.
38
,
2103
(
2000
).
17.
K. W.
Thompson
, “
Time dependent boundary conditions for hyperbolic systems
,”
J. Comput. Phys.
68
,
1
(
1987
).
18.
T. J.
Poinsot
and
S. K.
Lele
, “
Boundary conditions for direct simulations of compressible viscous flows
,”
J. Comput. Phys.
101
,
104
(
1992
).
19.
J. W.
Kim
and
D. J.
Lee
, “
Generalized characteristic boundary conditions for computational aeroacoustics
,”
AIAA J.
38
,
2040
(
2000
).
20.
J. B.
Freund
, “
Proposed inflow/outflow boundary condition for direct computation of aerodynamic sound
,”
AIAA J.
35
,
740
(
1997
).
21.
J.
Larsson
,
L.
Davidson
,
M.
Olsson
, and
L.
Eriksson
, “
Aeroacoustic investigation of an open cavity at low mach number
,”
AIAA J.
42
,
2462
(
2004
).
You do not currently have access to this content.