Hypersonic Drag and Heat-Transfer Reduction Using a Forward-Facing Jet

Meyer, Benjamin; Nelson, H. F.; Riggins, David W.

doi:10.2514/2.2819

Cited by 84 publications

(16 citation statements)

References 6 publications

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“…Other experiments involving various forms of the bow shock perturbation have shown carbuncle-like pulsating flows. These perturbations include: the injection of a forward-facing jet along the stagnation line [7][8][9], the injection of dust particles along the stagnation line [10], the energy deposition ahead of the bow shock [11][12][13]. In many cases, the perturbation yields a pulsating flow which oscillates between the regular detached bow shock and a carbuncle-like shock pattern.…”

Section: A Physical Instability?mentioning

confidence: 99%

A matrix stability analysis of the carbuncle phenomenon

Dumbser¹,

Moschetta²,

Gressier³

2004

Journal of Computational Physics

160

108

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Section: A Physical Instability?mentioning

confidence: 99%

A matrix stability analysis of the carbuncle phenomenon

Dumbser¹,

Moschetta²,

Gressier³

2004

Journal of Computational Physics

160

108

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“…The variation of drag coefficient ratio C d /C d0 with P under D ¼ 7.6 is shown in Figure 4, where C d is the body drag coefficient with jet and C d0 the one without jet. With the increasing of P from 1.05, the drag coefficient ratio first falls until the jet pressure exceeds a critical value at P crit ¼ 1.52 where the coefficient ratio increases sharply and then sustains a continuously drop with the further increasing of P. Taking the consideration by Meyer et al 8 that the increase of jet total pressure will result in the increase in the exhaustion of jet thrust and, thus the net increase to the overall drag, the maximum drag reduction condition is reached at P crit ¼ 1.52. The overall drag including the thrust penalty of the opposing jet is reduced as high as 32.6% than the case without a jet.…”

Section: Effect Of Jet Pressurementioning

confidence: 96%

“…Although the maximum drag reduction is reached with the flow in steady motion mode, taking the same consideration by Meyer et al 8 of the high exhaustion of jet thrust at high value of P, the maximum overall drag reduction is obtained at the critical value of P crit , and the maximum overall drag reduction is 32.6%, 29.0%, 26.5%, and 25.3% for D ¼ 7. 6, 9.4, 16.4, and 33.3, respectively.…”

Section: Effect Of Jet Nozzle Sizementioning

confidence: 96%

“…the unsteady long penetration mode (LPM) and the steady short penetration mode (SPM) with the LPM jet giving a larger drag reduction and a longer shock stand-off distance. Meyer et al 8 studied the effects of a forward-facing jet located at the stagnation point of a blunt body on wave drag and found that the flow field is significantly modified by the jet. Among the condition tested, the wave drag including the drag penalty of the forward-facing jet was shown to be reduced by as much as 55%.Venukumar et al 9 made an experimental measurement on a large angle blunt cone with a different supersonic jet pressure at a hypersonic Mach number and their results also showed 30-45% reduction in drag coefficient.…”

Section: Introductionmentioning

confidence: 99%

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A three-dimensional numerical investigation on drag reduction of a supersonic spherical body with an opposing jet

Zhou

Wen-ying

2012

Proceedings of the Institution of Mechanical Engineers, Part G:

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A three-dimensional numerical simulation of a supersonic free-stream at Mach 2.5 over a spherical body with a sonic opposing jet from its stagnation point is carried out by solving the three-dimensional Navier-Stokes equations coupled with the standard k-" turbulence model. It is aimed to investigate the effects of the jet on the drag reduction on the body and the flow field around the body. The influences of the jet pressure, the nozzle size of the jet, and the angle of attack are systematically studied for the purpose. An unsteady oscillatory motion mode and a nearly steady motion mode are identified depending upon the jet total pressure. There exists a critical jet pressure where the flow mode transition from one to the other happens suddenly and this critical pressure value varies approximately linearly with the jet nozzle exit size inversely. For the zero angle of attack, the results show that there exists a maximum overall drag reduction as the jet pressure changes for each jet nozzle size and the maximum overall drag reduction always happens at the unsteady oscillatory motion mode. The main shock in front of the body is pushed backward by the jet and the displacement of the shock decreases with the increase of the angle of attack, and the drag reduction efficiency also decreases with the angle. Regarding to the mode transition, it is found that the drag rises suddenly when the transition happens for the angle of attack smaller than or equal to 5 but it does not result in the rise for the angle larger than 5 . The results show that the maximum overall drag reduction can be reached as high as 32.6% for the cases studied. The present results provide useful information for drag reduction applications using an opposing jet.

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“…Different techniques have been used to achieve these goals. Although some of these techniques are very efficient for reducing drag and aerodynamic heating, they require additional equipment installation or energy consumption [12][13][14]. This paper focuses only on the aero-thermodynamic shape optimization of blunt bodies without using any additional equipment or energy.…”

Section: Introductionmentioning

confidence: 99%

Aerothermodynamic Design Optimization in Hypersonic Flows

Eyi

2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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The objective of this study is to develop a reliable and efficient design tool that can be used in hypersonic flows. The flow analysis is based on the axisymmetric Euler and the finite rate chemical reaction equations. These coupled equations are solved by using Newton's method. The analytical and numerical methods are used to calculate Jacobian matrices. The effects of error in numerical Jacobians on the performance of flow and sensitivity analyses are studied. A gradient based numerical optimization is used. Sensitivities are calculated by using finite-difference, direct differentiation and adjoint methods. The objective of the design is to generate a hypersonic blunt geometry that produces the minimum pressure drag while keeping the maximum temperature smaller than the initial value. Bezier curves are used for geometry modification. The performance of the optimization method is demonstrated for different hypersonic flow conditions. Nomenclature B = Bernstein polynomials c = speed of sound i D = design variables e t = total internal energy H = total enthalpy fi k = forward reaction rate constant R = species gas constant R u = universal gas constant T = temperature u, v = velocity components U,V = contravariant velocity components W = molecular weight x,y = components of Cartesian coordinates  = finite-difference perturbation magnitude  = Lagrange multiplier , k i   , , k i   = stoichiometric coefficients

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Hypersonic Drag and Heat-Transfer Reduction Using a Forward-Facing Jet

Cited by 84 publications

References 6 publications

A matrix stability analysis of the carbuncle phenomenon

A matrix stability analysis of the carbuncle phenomenon

A three-dimensional numerical investigation on drag reduction of a supersonic spherical body with an opposing jet

Aerothermodynamic Design Optimization in Hypersonic Flows

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