This paper describes an experimental study of supersonic internal flow over a riblet surface mounted on a channel wall to reduce pressure loss and improve the performance of a supersonic nozzle. The magnitude of the static pressure in the pressure-rise region observed in channels with riblet surface became lower than that for a smooth surface, and the significance of its difference was indicated by uncertainty analysis estimated at 95 percent coverage. The Mach number distributions obtained by traversing a Pitot-tube showed that the separation point moved downstream and the size of the separation region became small when using riblets. Furthermore, it was found that the stagnation pressure loss reduction was as large as 56 percent in the uniform supersonic flow field at a Mach number of 2.0, and 29 percent in the separation region. [S0098-2202(00)00103-6]

Issue Section:
Technical Papers
Keywords:
nozzles, supersonic flow, Mach number, pressure measurement, Dragon computers, channel flow, flow control
Topics:
Flow (Dynamics), Mach number, Nozzles, Pressure, Supersonic flow, Separation (Technology)
1.
Walsh, M. J., 1982, “Turbulent Boundary Layer Drag Reduction Using Riblets,” AIAA Paper, 82-0169.
2.
Bacher, E. V., and Smith, C. R., 1985, “A Combined Visualization-Anemometry Study of the Turbulent Drag Reducing Mechanisms of Triangular Micro-Groove Surface Modifications,” AIAA Paper, 85-0548.
3.
Choi
,
K.-S.
,
1989
, “
Near-Wall Structure of a Turbulent Boundary Layer with Riblets
,”
J. Fluid Mech.
,
208
, pp.
417
–
458
.
4.
Suzuki
,
Y.
, and
Kasagi
,
N.
,
1994
, “
Turbulent Drag Reduction Mechanism Above a Riblet Surface
,”
AIAA J.
,
32
, No.
9
, pp.
1781
–
1790
.
5.
Chu
,
D. C.
, and
Karniadakis
,
G. E.
,
1993
, “
A Direct Numerical Simulation of Laminar and Turbulent Flow over Riblet-Mounted Surfaces
,”
J. Fluid Mech.
,
250
, pp.
1
–
42
.
6.
Choi
,
H.
,
Moin
,
P.
, and
Kim
,
J.
,
1993
, “
Direct Numerical Simulation of Turbulent Flow over Riblets
,”
J. Fluid Mech.
255
, pp.
503
–
539
.
7.
Squire, L. C., and Savill, A. M., 1987, “Some Experiences of Riblets at Transonic Speeds,” Proc. Intl. Conf. on Turbulent Drag Reduction by Passive Means, Royal Aero. Soc., pp. 392–407.
8.
Gaudet
,
L.
,
1989
, “
Properties of Riblets at Supersonic Speed
,”
Appl. Sci. Res.
,
46
, No.
6
, pp.
245
–
254
.
9.
Walsh, M. J., and Lindemann, A. M., 1984, “Optimization and Application of Riblets for Turbulent Drag Reduction,” AIAA Paper, 84-0347.
10.
Winter
,
K. G.
, and
Gaudet
,
L.
,
1973
, “
Turbulent Boundary-Layer Studies at High Reynolds Numbers at Mach Numbers between 0.2 and 2.8
,”
Aeronautical Research Council Reports and Memoranda, No.
3712.
11.
Clauser
,
F. H.
,
1954
, “
Turbulent Boundary Layers in Adverse Pressure Gradients
,”
J. Aeronaut. Sci.
,
21
, pp.
91
–
108
.
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