The success of supersonic air-breathing propulsion systems will be largely dependent on efficient injection, mixing, and combustion inside the supersonic combustion chamber. Fuel/air mixing enhancement inside the combustion chamber will depend on the strategies used to control the fuel jet penetration and liquid fuel droplet size, trajectory, and dispersion. We present in this paper experimental results on the penetration and mixing of aerated liquid fuel jet in supersonic cross flow (M=1.5). The aerated liquid jet or the barbotage technique where a small amount of gas is added to the liquid fuel will accelerate the atomization of the liquid jet and offer a good fuel penetration. High speed imaging system is used in this study for the visualization of pure and aerated liquid jet. For the aerated liquid jet the gas/liquid mass ratio was varied between 0 and 9.9 %. The results presented in this paper shows the effect of jet/cross flow momentum ratio, and gas/liquid mass ratio on the structure and penetration of aerated liquid jet (methanol) in high speed cross flow. The data generated in this study are used for the development of active control strategies to optimize the liquid fuel jet penetration and supersonic fuel/air mixing.

1.
Lee
M. P.
,
McMillan
B. K.
,
Palmer
J. L.
, and
Hanson
R. K.
,
Planar fluorescence imaging of transverse jet in a supersonic cross-flow
,
Journal of Propulsion and Power
, Vol.
8
, No.
4
, July–Aug.
1992
, pp.
729
735
.
2.
B. Year, M. Kamel, C. Morris, and R.K. Hanson, Experimental investigation of hydrogen transverse jet combustion in hypersonic flows, AIAA Paper 97-3019, 33rd AIAA Joint Propulsion Conference, July 1997, Seattle, W.A., 1997.
3.
B. Yakar, and R.K. Hanson, Experimental Investigation of flame holding capability of a transverse hydrogen jet in supersonic cross flow, 27th International Symposium on Combustion, The Combustion Institute, 1998, pp. 2173–2180.
4.
Fric
T. F.
and
Roshko
A.
,
Vortical Structure in the wake of a transverse jet
,
J. Fluid Mech.
, Vol.
279
,
1994
, pp.
1
47
.
5.
Gruber
M. R.
,
Nejad
A. S.
,
Cheng
T. H.
, and
Dutton
J. C.
,
Bow Shock/Jet interaction in compressible transverse injection flowfields
,
AIAA Journal
, Vol.
4
, No.
10
,
1996
, pp.
2191
2193
.
6.
C. Ghenai, O.I. Smith, and A. Karagozian, Acoustical excitation of burning fuel droplets, 39th AIAA Aerospace Sciences Meeting and Exhibit, Reno, NV, January 2001.
7.
Dec
J. E.
,
Keller
J. O.
and
Arpaci
V. S.
,
Heat transfer enhancement in the oscillating turbulent flow of a pulse combustor tail pipe
,
International Journal of Heat and Mass Transfer
,
35
(
9
),
1992
,
2311
2325
.
8.
Arpaci
V. S.
,
Dec
J. E.
,
Keller
J. O.
,
Heat Transfer in pulse combustor tailpipes
,
Combustion Science and Technology
,
94
:
1993
,
131
146
.
9.
G. Yu, J.G. Li, L.G. Yue, J.R. Zhao, X.Y. Zhang, Characterization of Kerosene combustion in supersonic flow using effervescent atomization, AIAA 2002–5225, 11th AIAA/AAAF International Conference Space Planes and Hypersonic Systems and Technologies, Orleans, France, 2002.
10.
C. J. Tam, S. Cox-Stouffer, and K.C. Lin, Gaseous and Liquid injection in high speed cross flows, AIAA 2005–0301, Reno, NV, Jan. 2005.
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