Experimental Study of Supersonic Boundary Layer Receptivity in Controlled Conditions

Семёнов, Н. В.; Kosinov, A. D.

doi:10.1007/978-3-662-03997-7_68

Cited by 7 publications

(14 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The spectra for a three-dimensional source are similar to the results of Semionov et al (1996) and Kosinov et al (1996). Phase β-spectra for different X 1 are also similar, it means that C is about the same for all β.…”

Section: Acoustic Waves In the Free Streamsupporting

confidence: 84%

See 1 more Smart Citation

Leading-edge receptivity of a hypersonic boundary layer on a flat plate

et al. 2001

View full text Add to dashboard Cite

Experimental investigations of the boundary layer receptivity, on the sharp leading edge of a flat plate, to acoustic waves induced by two-dimensional and threedimensional perturbers, have been performed for a free-stream Mach number M ∞ = 5.92. The fields of controlled free-stream disturbances were studied. It was shown that two-dimensional and three-dimensional perturbers radiate acoustic waves and that these perturbers present a set of harmonic motionless sources and moving sources with constant amplitude. The disturbances excited in the boundary layer were measured. It was found that acoustic waves impinging on the leading edge generate Tollmien-Schlichting waves in the boundary layer. The receptivity coefficients were obtained for several radiation conditions and intensities. It was shown that there is a dependence of receptivity coefficients on the wave inclination angles.

show abstract

Section: Acoustic Waves In the Free Streamsupporting

confidence: 84%

“…A comparison of receptivity coefficients obtained for M ∞ = 6 with the results of Semionov et al (1996) (M ∞ = 2) and Kosinov et al (1996) (M ∞ = 3.5) shows that the boundary layer receptivity to external acoustic disturbances increases as the Mach number increases.…”

Section: Discussionmentioning

confidence: 62%

Leading-edge receptivity of a hypersonic boundary layer on a flat plate

et al. 2001

View full text Add to dashboard Cite

show abstract

“…17,18 Essentially all of this work dealt with situations in which the perturbation co-propagated with the flow. In a very few instances, researchers in quiet tunnels have noted that disturbances can travel upstream in the subsonic region of laminar boundary layers.…”

Section: Non-resonant Transmissionmentioning

confidence: 99%

Application of Diode-Laser-Based Measurements in Hypersonic Flows

Brown

2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

View full text Add to dashboard Cite

The development of optical techniques capable of measuring in-stream flow properties of air breathing hypersonic engines is a goal of the Aerospace Propulsion Division at AFRL. This goal is motivated by the need for in-stream data to support both ground and flight tests of scramjet engine designs. While particular fundamental hypersonic flow problems are addressable using well-established laser-based techniques, advanced engine concepts using axisymmetric hardware typically have minimal optical access making some of the more traditional techniques difficult to deploy. To meet the need we have an ongoing in-house program to mature diode-laser-based techniques for application in hypersonic flows. Additional motivation for developing diode-laser-based measurement strategies comes from the need for flight sensors. Flight-worthy packages must be small, light, low-power and rugged. For measurement objectives in both ground and flight experiments we have adopted tunable diode laser absorption spectroscopy making heavy use of fiber coupling and integrated optomechanics. Water-based measurements of temperature, pressure, velocity, and water mole fraction are executed using time-multiplexed near-infrared diodes. These fundamental flow parameters can be combined to yield optical mass capture and thrust. Similar measurements can be made in inlets using an oxygen-based strategy employing visible diodes. In this paper we summarize the absorption sensor work done to date in AFRL. Particular attention will be paid to the fact that a single hardware platform can be used to capture absorption, non-resonant transmission, and optical emission signals all three of which provide relevant information.

show abstract

“…All these observations testify the crucial role of receptivity. However, there have been just a few detailed measurements of receptivity using controlled free-stream disturbances, and these were conducted by Maslov et al (2001) and Semionov & Kosinov (1999, 2008 for flat plates with sharp and blunt leading edges.…”

Section: Introductionmentioning

confidence: 99%

Response and receptivity of the hypersonic boundary layer past a wedge to free-stream acoustic, vortical and entropy disturbances

Qin

2016

J. Fluid Mech.

View full text Add to dashboard Cite

This paper analyses the response and receptivity of the hypersonic boundary layer over a wedge to free-stream disturbances including acoustic, vortical and entropy fluctuations. Due to the presence of an attached oblique shock, the boundary layer is known to support viscous instability modes whose eigenfunctions are oscillatory in the far field. These modes acquire a triple-deck structure. Any of three elementary types of disturbances with frequency and wavelength on the triple-deck scales interacts with the shock to generate a slow acoustic perturbation, which is reflected between the shock and the wall. Through this induced acoustic perturbation, vortical and entropy free-stream disturbances drive significant velocity and temperature fluctuations within the boundary layer, which is impossible when the shock is absent. A quasi-resonance was identified, due to which the boundary layer exhibits a strong response to a continuum of high-frequency disturbances within a narrow band of streamwise wavenumbers. Most importantly, in the vicinity of the lower-branch neutral curve the slow acoustic perturbation induced by a disturbance of suitable frequency and wavenumbers is in exact resonance with a neutral eigen mode. As a result, the latter can be generated directly by each of three types of free-stream disturbances without involving any surface roughness element. The amplitude of the instability mode is determined by analysing the disturbance evolution through the resonant region. The fluctuation associated with the eigen mode turns out to be much stronger than free-stream disturbances due to the resonant nature of excitation and in the case of acoustic disturbances, to the well-known amplification effect of a strong shock. Moreover, excitation at the neutral position means that the instability mode grows immediately without undergoing any decay, or missing any portion of the unstable region. All these indicate that this new mechanism is particularly efficient. The boundary-layer response and coupling coefficients are calculated for typical values of parameters.

show abstract

Experimental Study of Supersonic Boundary Layer Receptivity in Controlled Conditions

Cited by 7 publications

References 1 publication

Leading-edge receptivity of a hypersonic boundary layer on a flat plate

Leading-edge receptivity of a hypersonic boundary layer on a flat plate

Application of Diode-Laser-Based Measurements in Hypersonic Flows

Response and receptivity of the hypersonic boundary layer past a wedge to free-stream acoustic, vortical and entropy disturbances

Contact Info

Product

Resources

About