Numerical Simulation of Lateral Jet Interaction a Slender Body in Supersonic Flow

A numerical investigation has been conducted to research the interaction flowfield of lateral jet not in the longitudinal symmetry plane on a slender body with rudders in supersonic flow. The surface and space flow features of jet interaction flowfield with different angles of attack was analyzed. The paper also compared with and without jet interaction flowfield characteristics. As a result, the jet interaction destroys pressure distributions of the slender body, and causes normal and lateral loads. With angle of attack, the pressure distributions of the after body and rudders surfaces are change tempestuously. The results also show that the far-field interference played a major role in the lateral jet interaction. Besides, the force/moment amplification factors present highly nonlinear with angle of attack.

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Asymmetrical Lateral Jet Interaction on a Slender Body in Supersonic Flow

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.565.107 ◽

2014 ◽

Vol 565 ◽

pp. 107-112

Author(s):

Shi Jie Luo

Keyword(s):

Supersonic Flow ◽

Total Pressure ◽

Angle Of Attack ◽

The Body ◽

Slender Body ◽

Far Field ◽

Field Interaction ◽

Jet Interaction ◽

Pressure Distributions ◽

Highly Nonlinear

The lateral jet interaction on a slender body with rudders in supersonic flow had been investigated by numerical simulation, when the lateral jet is not in the longitudinal symmetry plane. It was called Asymmetrical lateral jet interaction in this paper. The flow features of jet interaction flowfield on the surface of the body or in the space far from the surface at different angles of attack and total pressure of jet was analyzed. As a result, the lateral jet interaction disturbed the pressure distributions of the slender body, and it was divided into near-field interaction near jet and far-field interaction aft-body on the basis of distance to jet. With the variety of the angle of attack and total pressure of jet, the pressure distributions at the aft-body change tempestuously, thereby the normal and lateral load will be from positive to negative, or reverse. The results also showed that the far-field interaction played a major role in the lateral jet interaction on a slender body in supersonic flow. The far-field interaction was caused by the changing of the outflow direction and intensity. Besides, the force/moment amplification factors presented highly nonlinear with the variety of angle of attack and total pressure of jet.

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Visualization of asymmetric separation induced by lateral jet interaction on a slender body in supersonic flow

International Journal of Modern Physics B ◽

10.1142/s0217979220400810 ◽

2020 ◽

Vol 34 (14n16) ◽

pp. 2040081

Author(s):

Shi-Jie Luo ◽

Yao-Feng Liu ◽

Yu-Wei Liu

Keyword(s):

Supersonic Flow ◽

Flow Characteristic ◽

Symmetry Plane ◽

Flow Characteristics ◽

Surface Flow ◽

Slender Body ◽

Separation Flow ◽

Field Interaction ◽

Jet Interaction ◽

Pressure Distributions

The lateral jet interaction on a slender body in supersonic flow was investigated by numerical simulation. The spatial and surface flow characteristics induced by jet interaction were shown. As a result, when the lateral jet is not in the longitudinal symmetry plane, the jet interaction causes asymmetric separation flow of surface and space, and destroys the pressure distributions of the slender body. With different angle of attack and circumferential positions of jet, the flow characteristic of the after body for jet in asymmetry plane changes greatly. The results with and without jet interaction also show that the far-field interaction played a major role in the lateral jet interaction.

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Strakes Effects on Asymmetric Flow Over a Blunt-Nosed Slender Body at a High Angle of Attack

Journal of Fluids Engineering ◽

10.1115/1.4041815 ◽

2018 ◽

Vol 141 (6) ◽

Author(s):

Qihang Yuan ◽

Yankui Wang ◽

Zhongyang Qi

Keyword(s):

Angle Of Attack ◽

Slender Body ◽

Axial Position ◽

High Angle ◽

Asymmetric Flow ◽

High Angle Of Attack ◽

Side Force ◽

Asymmetric Vortices ◽

High Angles Of Attack ◽

Blunt Nose

In general speaking, the missiles execute flight at high angles of attack in order to enhance their maneuverability. However, the inevitable side-force, which is caused by the asymmetric flow over these kinds of traditional slender body configurations with blunt nose at a high attack angle, induces the yawing or rolling deviation and the missiles will lose their predicted trajectory consequently. This study examines and diminishes the side-force induced by the inevitable asymmetric flow around this traditional slender body configuration with blunt nose at a high angle of attack (AoA = 50 deg). On one hand, the flow over a fixed blunt-nosed slender body model with strakes mounted at an axial position of x/D = 1.6–2.7 is investigated experimentally at α = 50 deg (D is the diameter of the model). On the other hand, the wingspan of the strakes is varied to investigate its effect on the leeward flow over the model. The Reynolds number is set at ReD = 1.54 × 105 based on D and incoming upstream velocity. The results verify that the formation of asymmetric vortices is hindered by the existence of strakes, and the strake-induced vortices develop symmetrically and contribute to the reduction in side-force of the model. In addition, the increase in strake wingspan reduces asymmetric characteristics of the vortex around the model and causes a significant decrease in side-force in each section measured. The strake with the 0.1D wingspan can reduce the sectional side-force to 25% of that in the condition without strakes.

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Asymmetric Vortices around a Body at High Angle of Attack Supersonic Flow

Journal of the Korean Physical Society ◽

10.3938/jkps.55.2159 ◽

2009 ◽

Vol 55 (5(2)) ◽

pp. 2159-2165 ◽

Cited By ~ 3

Author(s):

Sang Ho Kim ◽

Wansub Kim

Keyword(s):

Supersonic Flow ◽

Angle Of Attack ◽

High Angle ◽

High Angle Of Attack ◽

Asymmetric Vortices

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The Supersonic Flow Field Associated with a Conical Flame Sheet

Aeronautical Quarterly ◽

10.1017/s0001925900005527 ◽

1970 ◽

Vol 21 (4) ◽

pp. 368-378 ◽

Cited By ~ 2

Author(s):

J. F. Clarke ◽

D. G. Petty

Keyword(s):

Supersonic Flow ◽

Flow Field ◽

Base Flow ◽

Slender Body ◽

Conical Flow ◽

Slender Body Theory ◽

Deflagration Wave ◽

Flame Sheet ◽

Base Drag ◽

Body Theory

SummaryIt is shown that a pair of supersonic inviscid conical flow fields can exist on either side of a conical deflagration wave. The configuration is relevant to the base flow question and indicates how base drag may be alleviated by burning. Results of exact computations are presented as well as those derived from a slender-body theory.

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The Slender Wing with a Half Body of Revolution Mounted Beneath

The Aeronautical Journal ◽

10.1017/s0001924000085109 ◽

1968 ◽

Vol 72 (693) ◽

pp. 803-807 ◽

Cited By ~ 2

Author(s):

H. Portnoy

Keyword(s):

Supersonic Flow ◽

Slender Body ◽

Meridian Plane ◽

Pitching Moment ◽

Body Of Revolution ◽

Slender Body Theory ◽

Lift And Drag ◽

Body Theory ◽

Slender Wing

Summary The slender-body theory of Ward is applied to a configuration consisting of a slender, pointed wing, carrying directly beneath it a pointed half-body of revolution divided along a meridian plane. Expressions for lift and drag due to incidence are found which are valid in both subsonic and supersonic flow if the flow is attached. The lift result can be used to find pitching moment. For the supersonic case the drag at zero incidence is also found and the expressions for a conical configuration are developed so that a limiting form of these can be compared with the results of ref. 3.

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Centre of Pressure of Cowl Shapes Having Minimum Drag in Supersonic Flow

Journal of the Royal Aeronautical Society ◽

10.1017/s0001924000058784 ◽

1965 ◽

Vol 69 (657) ◽

pp. 636-637

Author(s):

D. J . Carey

Keyword(s):

Supersonic Flow ◽

Close Correlation ◽

Centre Of Pressure ◽

Newtonian Flow ◽

Pressure Distributions ◽

Minimum Drag

Formulae are presented giving the centre of pressure of axi-symmetric bodies at zero incidence having profiles for which the drag is a minimum in Newtonian flow.Boyd has suggested that a close correlation may exist between such profiles, and profiles derived from exact pressure distributions, in supersonic flow.

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