Hypersonic flow over a cone with nose cavity

Sambamurthi, Jay K.; Huebner, Lawrence D.; Utreja, L. R.

doi:10.2514/6.1987-1193

Cited by 20 publications

(14 citation statements)

References 4 publications

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“…This is evidence that the mechanism previously thought to decrease heat flux (Engblom 1996) does indeed work to some extent. Consistent with the findings of previous experimental and computational studies (Sambamurthi, Huebner & Utreja 1987;Spring & Smith 1993), the mean heat flux at the base of the cavity (figure 13a) is much lower than that at the lip for all of these geometries. Because of the large differences in body geometries, comparable maximum mean surface heat flux may not lead to comparable ablation onset times.…”

Section: Computationssupporting

confidence: 91%

Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow

Silton

Goldstein

2005

J. Fluid Mech.

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A forward-facing cavity is examined as a means of reducing the severe heating and delaying ablation onset at the nose-tip of a hypersonic vehicle. Whereas previous studies have concentrated on the nature of flow-induced Hartmann-whistle oscillations or on heating rates alone, the present study addresses the effect of the cavity on ablation onset times through experiments and coupled flow field/heat conduction simulation. Using our previously developed experimental technique, a parametric study is undertaken to optimize the forward-facing cavity geometry for the most delayed ablation onset. The geometric parameters of cavity length, lip radius and diameter are independently optimized for a given nose-tip diameter. Then using benchmarked linked flow field/heat conduction simulations, numerical simulations are conducted for each parametrically optimized configuration in order to investigate the flow physics.

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Section: Computationssupporting

confidence: 91%

Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow

Silton

Goldstein

2005

J. Fluid Mech.

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“…In addition, he saw no correlation of this instability to the fundamental acoustic frequency of oscillation, In contrast to Johnson's hypothesis, the existence of vortices and their periodic formation and shedding was suggested as a mechanism for shock oscillation by Sambamurthi et.al. 8 for test runs employing no air injection. The corresponding shock oscillations did follow the fundamental acoustic frequency.…”

Section: Bow-shock Behavior (Periodic Oscillations)mentioning

confidence: 99%

“…They also noted that the shock oscillation frequency was related to the distance from the cavity base to the shock equilibrium position. Sambamurthi et al 8 investigated a two-dimensional conical-walled cavity with a flat base at Moo =10 using a time-dependent Navier-Stokes code. Their results predicted a shock that oscillated at a frequency corresponding approximately to the fundamental acoustic frequency of the cavity, with a wavelength that was four times the distance from the cavity base to the mean shock position.…”

Section: Introductionmentioning

confidence: 99%

Mach 10 bow-shock behavior of a forward-facing nose cavity

Huebner

Utreja

1993

Journal of Spacecraft and Rockets

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A detailed description of the bow-shock behavior associated with a conical-walled cavity with a flat circular base at MOO = 10 is presented. An experimental test was performed on this configuration, and measurements of shock-oscillation frequency and amplitude, as well as shock shape, were recorded by a number of techniques, one being a laser-interferometer system used for the first time during this test to determine bow-shock oscillation frequency in a nonintrusive manner. The primary behavior was a stable, periodically oscillating bow shock. Discussions are also made on a violent bow-shock instability that occurred for one set of conditions during the test. Nomenclature Moo= freestream Mach number m = mass-flow rate, Ibm/s Re^ -freestream Reynolds number, I/ft a = angle of attack, deg

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“…As the cavity length increases, the resonant frequency decreases. Sambamurthiet et al [9] investigated the flow field behaviour around a cone with a cavity at hypersonic flows. The results indicated that the frequency of the bow shock is inversely proportional to the cavity depth.…”

Section: Introductionmentioning

confidence: 99%

Prediction of Shock-Standoff Distance and Entropy Distribution for Forward-Facing Cavity

Wang¹

2018

IJASS

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Experiments are performed on a cylinder with a forward-facing cavity at M ∞ = 10 in the FD-14A shock tunnel. The shock-standoff distance and oscillation characteristics are recorded by a high-speed movie, and the dynamic pressure transducer is used to capture the unsteady signal of cavity base. Based on experimental and numerical results, a prediction method for estimating the shock-standoff distance is proposed. Results of shock-standoff distance and oscillation frequency are obtained for experiments in the shock tunnel. The predicted oscillation frequency is in accordance with experimental results. Furthermore, the relation of shock shape and the entropy increase are combined to obtain the characteristics of entropy distribution. As the shock-shape of flat-nosed cylinders is more liable to be influenced than blunt-nosed cylinders with increasing Mach number, the location of the extreme value moves to the surface as the Mach number increases for flat-nosed cylinders, while it remains the identical location for blunt-nosed cylinders.

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Hypersonic flow over a cone with nose cavity

Cited by 20 publications

References 4 publications

Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow

Use of an axial nose-tip cavity for delaying ablation onset in hypersonic flow

Mach 10 bow-shock behavior of a forward-facing nose cavity

Prediction of Shock-Standoff Distance and Entropy Distribution for Forward-Facing Cavity

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