Deployable Flow Effectors for Phantom Yaw Control of Missiles at High Alpha

Patel, Mitesh; Prince, Troy S.; Carver, Reed; DiCocco, Jack; Lisy, F.J.; Ng, Tammy

doi:10.2514/6.2002-2827

Cited by 8 publications

(3 citation statements)

References 7 publications

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“…7 These devices have also been proposed for practical configurations. [8][9][10][11][12][13][14] MVGs are thought to operate in the same manner as conventional vortex generators in energizing the boundary layer fluid through entrainment of the freestream by trailing vortices.…”

Section: Introductionmentioning

confidence: 99%

Review of Micro Vortex Generators in High-Speed Flow

Shih

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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A review of the state-of-the-knowledge of micro vortex generators (MVGs) and their effect on separated shock/boundary-layer interactions is provided. MVGs are thought to be effective for reducing the separation zone. However, details of how they affect the separation zone remain to be understood properly. In addition, metrics on how the MVGs affect the separation have not been well developed. Suggestions for further study are provided.

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Section: Introductionmentioning

confidence: 99%

Review of Micro Vortex Generators in High-Speed Flow

Shih

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Many researchers have observed this unwanted side force through experimental investigations and termed it a 'phantom yaw'. These large side forces and asymmetric flow-separations show very irregular patterns that vary with the prevailing conditions [1][2][3]. Thus, it is difficult to find out the reasons for and the flow structures of these phenomena.…”

Section: Introductionmentioning

confidence: 99%

The influence of Chine nose shapes on a slender body flight vehicle at high angles of attack

Lim

Kim²,

Song

2011

Proceedings of the Institution of Mechanical Engineers, Part G:

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The flow characteristics of asymmetric vortices and the side force of a slender body flight vehicle with chine nose at high angles of attack have been studied using a three-dimensional upwind Navier–Stokes method with the k– ω turbulence model and a simple laminar–turbulent transition model. Asymmetrically changing turbulent viscosities that arise from asymmetric laminar–turbulent transition conditions cause asymmetric cross-flow vortex structures and side forces at higher angles of attack. However, certain type of edges may cause fixed flow separations on these edges. In this study, the chine nose shape with chine edge on its both sides is considered for the method to reduce side force. The asymmetric flow control capacity of chine nose shapes at high angles of attack is studied.

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“…Large, unwanted, side forces that result from asymmetric separations and vortices decrease the flight vehicle's overall performance and limit flight domains. Thus, additional methods for yaw control might be required for stable vehicle operation [3][4][5][6].…”

mentioning

confidence: 99%

Influence of Asymmetric Transition Conditions on a Slender-Body Flight Vehicle

Lim

Kim²,

Song

2009

Journal of Spacecraft and Rockets

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The flow characteristics of asymmetric vortices and the side force of a tangent-ogive-cylinder flight vehicle at high angles of attack have been studied by using a three-dimensional upwind Navier-Stokes method with the k-! turbulence model and a simple laminar-turbulent transition model. Various patterns of asymmetric vortices and side forces are studied by using various asymmetric laminar-turbulent transition conditions. Asymmetrically changing turbulent viscosities that arise from asymmetric laminar-turbulent transition conditions cause asymmetric crossflow vortex structures and side forces at higher angles of attack. The magnitude and structure of the crossflow vortices and side forces were sensitive to changes in the factors of the model of laminar-turbulent transition. Nomenclature= cylinder diameter L n = length of the nose part Ma = Mach number q = freestream dynamic pressure R = cylinder radius Re D = Reynolds number, UD= x = axial distance from the nose tip = angle of attack = kinematic viscosity T = turbulent viscosity in the fully turbulent region TR = turbulent viscosity in the transition region

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Deployable Flow Effectors for Phantom Yaw Control of Missiles at High Alpha

Cited by 8 publications

References 7 publications

Review of Micro Vortex Generators in High-Speed Flow

Review of Micro Vortex Generators in High-Speed Flow

The influence of Chine nose shapes on a slender body flight vehicle at high angles of attack

Influence of Asymmetric Transition Conditions on a Slender-Body Flight Vehicle

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