Experimental Study of Supersonic Inlet Buzz

Trapier, Simon; Duveau, Philippe; Deck, Sébastien

doi:10.2514/1.20451

Cited by 126 publications

(52 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…In particular, Trapier et al [4] experimentally investigated both types of buzz using a rectangular external compression supersonic inlet, where they showed acoustic waves were associated with little buzz leading to external shock oscillations. Unsteady inlet events have previously been investigated in both experimental and computational studies [4][5][6][7][8][9][10][11].…”

mentioning

confidence: 98%

“…little buzz (small-amplitude and near-design mass flow rates) have been previously considered [1][2][3][4]. In particular, Trapier et al [4] experimentally investigated both types of buzz using a rectangular external compression supersonic inlet, where they showed acoustic waves were associated with little buzz leading to external shock oscillations.…”

mentioning

confidence: 99%

“…There have been several studies that investigated shock wave dynamics for a supersonic inlet [1][2][3][4][5][6][7][8][9][10][11]. A phenomenon known as inlet buzz [1] occurs when the mass flow rate drops below a critical limit, resulting in large streamwise oscillations of the external normal shock and significant flow separation.…”

mentioning

confidence: 99%

See 2 more Smart Citations

Acoustically Induced Shock Oscillations in a Low-Boom Inlet

et al. 2016

View full text Add to dashboard Cite

Experimental unsteady centerbody surface pressures measured in a low-boom inlet have been analyzed and compared with an unsteady computational flow approach. The experimental dataset was gathered at the 8 × 6 ft supersonic wind tunnel at the NASA John H. Glenn Research Center in 2010. The axisymmetric external compression inlet considered herein featured a relaxed isentropic centerbody compression spike followed by a short subsonic diffuser to the aerodynamic interface plane. The axisymmetric inlet computational domain comprised a 10 deg sector, starting with the freestream inflow region, and included both the internal flowpath up to the mass flow plug and the external flow past the sharp-edged cowl for external flow. The selected inlet test conditions were based on a 1.67 freestream Mach number at a zero angle of attack with a near-design spillage rate of approximately 4%. Both experiments and simulations revealed temporal shifts between pressure peaks at different streamwise locations, indicating upstream-running compression waves that moved at acoustic speeds. These waves became amplified near the geometric throat and produced streamwise oscillations of the external normal shock. The simulations also revealed a second smaller shock on the centerbody at the geometric throat, for which the complex dynamics suggested an opportunity for further study. Nomenclature a = speed of sound D = diameter L = length N = number of unsteady pressure readings p = pressure r = radial direction coordinate t = time u = streamwise velocity component x = streamwise direction coordinate y = normal direction coordinate z = spanwise direction coordinate τ = timescale Subscripts AC = acoustic AIP = aerodynamic interface plane CB = centerbody cowl = inner cowl diff = averaged over low-speed diffuser end = wave end peak = local peak RMS = root mean square sh = shock start = wave start tip = spike tip ∞ = freestream condition Superscripts 0 = fluctuation = normalized

show abstract

mentioning

confidence: 98%

mentioning

confidence: 99%

See 1 more Smart Citation

Acoustically Induced Shock Oscillations in a Low-Boom Inlet

et al. 2016

View full text Add to dashboard Cite

show abstract

“…Much information could be found in the literature on di erent aspects of various types of supersonic inlet models [3][4][5][6][7][8][9][10][11][12][13][14]. Performance characteristics of inlet in cases of extensive maneuvering range [3,4], unstart [5], buzz phenomenon, and application of boundary-layer bleed [6][7][8][9][10][11][12][13][14] have recently been investigated. In addition to these experiments, many computational studies have been accomplished on the supersonic inlet ow and buzz phenomenon as well as ow control methods [15][16][17][18][19].…”

Section: Introductionmentioning

confidence: 99%

Effects of Shock Wave/Boundary-Layer Interaction on Performance and Stability of a Mixed-Compression Inlet

Soltani¹,

Daliri²,

Sepahi-Younsi³

2016

Scientia Iranica

View full text Add to dashboard Cite

Abstract. Experiments were conducted to study various kinds of Shock wave/BoundaryLayer Interaction (SBLI) in an axisymmetric mixed-compression inlet. Experimental ndings were compared and veri ed by numerical solutions where possible. Di erent types of SBLI relevant to the mixed-compression inlets are classi ed. Interactions of normal shock wave/boundary-layer at subcritical condition and in buzz condition are investigated using Schlieren and shadowgraph ow visualization as well as unsteady pressure recordings. The data is compared with the CFD predictions. Interactions of cowl lip re ected oblique shock and the terminal normal shock with the spike boundary-layer at both critical and supercritical operations, which lead to pseudo-shock phenomena, are also studied. Experimental pressure recordings are used for validation and discussion. For near-critical throttling values, interaction of internal compression oblique shocks with boundary-layer and pseudo-shock phenomenon is dominant. Formation of lambda shock due to interaction of separated boundary-layer with normal shock wave is investigated. Each type of ow interaction phenomena has di erent e ects on the stability and performance of the inlet. Interaction of terminal normal shock with internal duct boundary-layer causes pseudoshock phenomenon that increases ow distortion and reduces total pressure recovery. Interaction of normal shock with cone boundary-layer causes buzz instability and degrades inlet performance.

show abstract

“…Each of the methods has its own merits and demerits as it involves incorporation of additional system e.g., installation of bleed system or movement and control of system, cooling system, etc, for efficient operation over wide range of operations of intake. 12 , et al, etc. The objective of the present investigation is to study the flow for a two-dimensional intake configuration used 1,2 through computations using the commercial software FLUENT.…”

mentioning

confidence: 99%

Cowl Deflection Angle in a Supersonic Air Intake

Das¹

2009

DSJ

View full text Add to dashboard Cite

Experimental Study of Supersonic Inlet Buzz

Cited by 126 publications

References 7 publications

Acoustically Induced Shock Oscillations in a Low-Boom Inlet

Acoustically Induced Shock Oscillations in a Low-Boom Inlet

Effects of Shock Wave/Boundary-Layer Interaction on Performance and Stability of a Mixed-Compression Inlet

Cowl Deflection Angle in a Supersonic Air Intake

Contact Info

Product

Resources

About