Velocimetry Measurements of a Scramjet Cavity Flameholder with Inlet Distortion

Kirik, Justin W.; Goyne, Christopher P.; Peltier, Scott; Carter, Campbell D.; Hagenmaier, Mark A.

doi:10.2514/1.b35195

Cited by 33 publications

(20 citation statements)

References 28 publications

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“…It is reported that a low-speed recirculation region can be created in a cavity in supersonic combustion, and partial subsonic combustion within the recirculation flow acts as a continuous ignition source for the whole flow, thus eventually achieving flameholding in supersonic incoming flows [23][24][25]. Because of pressure oscillations resulting from the subsonic combustion, as shown in Fig.…”

Section: B Detonation Sustainment and Forward Propagationmentioning

confidence: 99%

Detonation Interaction with Cavity in Supersonic Combustible Mixture

Cai¹,

Liang²,

Deiterding

et al. 2018

AIAA Journal

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= depth of the cavity, cm L = width of the cavity, cm l ig = induction length of one-dimensional Zel'dovich-von Neumann-Döring model, mm Pts∕l ig = number of the grid points distributed in the induction length V CJ = Chapman-Jouguet velocity, m/s X 1 = length of the straight channel, cm X 2 = width of the hot jet, cm X 3 = distance from the hot jet edge to the front edge of the cavity, cm X 4 = distance from the rear edge of the cavity to the outflow boundary, cm Y 1 = height of the channel, cm

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Section: B Detonation Sustainment and Forward Propagationmentioning

confidence: 99%

Detonation Interaction with Cavity in Supersonic Combustible Mixture

Cai¹,

Liang²,

Deiterding

et al. 2018

AIAA Journal

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“…Most recently, an advantage of the scheme based on an impinging shock wave (SW) for flow control and promotion of fuel ignition in the cavity of a supersonic combustor has been demonstrated experimentally [6,7,8,9,10]. Typically the shock wave was initiated by a mechanical obstacle (short wedge) installed on the wall opposite the cavity which modified the flowfield inside of it.…”

Section: Introductionmentioning

confidence: 99%

Controllable Shock Wave Generation by Near-Surface Electrical Discharge

Leonov

Houpt

Hedlund

et al. 2016

47th AIAA Plasmadynamics and Lasers Conference

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This experimental work explores the physical processes related to an interaction of a nearsurface Quasi-DC (Q-DC) electrical discharge with supersonic airflow. The study is performed in the Supersonic Test Rig SBR-50 at the University of Notre Dame at Mach Number M = 2, stagnation pressure P0 = 0.9-2.6 Bar, stagnation temperature T0=300K, Reynolds Number ReL = 7-25 10 6 m -1 , test cell dimensions 76×76×610mm with 1º two walls divergence, and plasma power W= 5-16 kW. The plasma power and temperature are measured with current-voltage probes and optical emission spectroscopy. An unsteady pattern of interaction is depicted by high-speed image capturing. The result of the interaction is characterized by means of pressure measurements and schlieren visualization. It is demonstrated that the plasma generation causes the appearance of a wedge-shaped displacement layer and an oblique shock wave (SW). The strength of the SW is a rising function of the plasma power; the position of the impinged zone on the opposite wall can be electronically regulated. The resulting pressure amplification has been described for the configurations included; both a fixed SW generator and the plasma-based SW generator. It is considered that the Q-DC discharge may be employed for active control of duct-driven flows, cavity-based flow, and, finally, for control of ignition / flameholding in a supersonic combustor.

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“…5 Optical diagnostics applied to scramjet flows have included planar laser-induced fluorescence (PLIF), 6 coherent antiStokes Raman spectroscopy (CARS), 7 tunable diode laser absorption spectroscopy (TDLAS), 8 tunable diode laser absorption tomography (TDLAT), 9 laser Doppler velocimetry (LDV), 10 hydroxyl-tagging velocimetry (HTV), 11 and particle image velocimetry (PIV). 1,[12][13][14][15][16] Of the velocimetry techniques, both PIV and LDV are dependent on proper seeding of the flowfield with tracer particles. 17 These particles must be sufficiently large to scatter enough light to enable photographic detection, yet small enough to faithfully track the flow.…”

Section: Introductionmentioning

confidence: 99%