Numerical Simulations of Supersonic Flow over an Elliptic-Section Projectile with Jet Interaction

2002 ◽  
Author(s):  
Jubaraj Sahu
Keyword(s):  
Supersonic Flow ◽  
Numerical Simulations ◽  
Jet Interaction ◽  
Elliptic Section

Jet Interaction in Supersonic Flow with a Surface Ramp

2003 ◽  
Author(s):  
Yung-Hwan Byun ◽  
Scott Wallis ◽  
Valerio Viti ◽  
Ki Joon Bae ◽  
Joseph Schetz ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Jet Interaction

scholarly journals Numerical Simulation of Supersonic Carman Curve Bodies with Aerospike

2021 ◽  
Vol 2021 ◽  
pp. 1-14
Author(s):  
HaiLong Zhao ◽  
Ke Peng ◽  
ZePing Wu ◽  
WeiHua Zhang ◽  
JiaWei Yang ◽  
...  
Keyword(s):  
Numerical Simulation ◽  
Mach Number ◽  
Supersonic Flow ◽  
Drag Reduction ◽  
Numerical Simulations ◽  
Reduction Methods ◽  
Reduction Effect ◽  
Supersonic Vehicles

Drag reduction is one of the important problems for the supersonic vehicles. As one of the drag reduction methods, aerospike has been used in some equipment because of its good drag reduction effect. In this paper, the numerical simulations of Carman curve bodies with different lengths of the aerospike and different radius of the flat cylindrical aerodisk in supersonic flow freestream are investigated. Based on the numerical simulations, the mechanism of drag reduction of the aerospike is discussed. The drag reduction effect influence of the parameters of the aerodisk radius and the aerospike length on the Carman curve body is analyzed. The aerodisk radius within a certain range is helpful for the drag reduction. The change of length of the aerospike has little effect on the drag of Carmen curve bodies. The drag reduction effect of the same aerospike becomes worse with the increase of the incoming Mach number.

scholarly journals Unsteady Transition From a Mach to a Regular Shockwave Intersection

2021 ◽  
Vol 16 ◽  
pp. 153-158
Author(s):  
S. J. Karabelas ◽  
N.C. Markatos
Keyword(s):  
Supersonic Flow ◽  
Numerical Simulations ◽  
Deflection Angle ◽  
Mach Reflection ◽  
Single Point ◽  
Research Work ◽  
Mach Disk ◽  
Navier Stokes ◽  
The Deflection Angle ◽  
To Come

The purpose of this research work is to perform accurate numerical computations of supersonic flow in a converging nozzle and specifically to study Mach-disks. The latter process has been widely studied over the last years. In the present study numerical simulations are performed for transient supersonic flow, tracing the transition from a Mach reflection to a regular one. This has been done by enforcing the walls of a converging nozzle to come closer together, changing the deflection angle with time. Viscosity was taken into account and the full Navier- Stokes have been solved. The results obtained clearly show the gradual extinction of the Mach disk and the eventual wave intersection to a single point

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

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.

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

2013 ◽  
Vol 404 ◽  
pp. 296-301
Author(s):  
Shi Jie Luo ◽  
Yao Feng Liu ◽  
Ning Cao
Keyword(s):  
Supersonic Flow ◽  
Angle Of Attack ◽  
Symmetry Plane ◽  
Slender Body ◽  
Lateral Loads ◽  
Jet Interaction ◽  
Pressure Distributions ◽  
Highly Nonlinear ◽  
Flow Features ◽  
Force Moment

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.

scholarly journals Secondary Eyewall Formation in Tropical Cyclones by Outflow–Jet Interaction

2017 ◽  
Vol 74 (6) ◽  
pp. 1941-1958 ◽  
Author(s):  
Yi Dai ◽  
Sharanya J. Majumdar ◽  
David S. Nolan
Keyword(s):  
Wind Speed ◽  
Numerical Simulations ◽  
Tropical Cyclones ◽  
Deep Convection ◽  
Stratiform Cloud ◽  
Jet Interaction ◽  
Secondary Eyewall Formation ◽  
Stratiform Region ◽  
Upper Level ◽  
Convective Cells

Abstract This study uses idealized numerical simulations to show that the interaction between tropical cyclones and a midlatitude jet can result in secondary eyewall formation. It is argued that the eddy activity by the outflow–jet interaction can enhance the upper-level outflow, thereby creating an asymmetric stratiform region outside of the primary eyewall. Numerous long-lasting deep convective cells are able to form in the stratiform cloud, creating forcing necessary for the secondary eyewall. The low-level inflow and the TC’s primary circulation advect the deep convective cells inward and cyclonically. The secondary eyewall forms after the deep convection has surrounded the TC. In contrast, numerical simulations without the jet do not show secondary eyewall formation. For moderately strong jets of wind speed 15–30 m s−1, there is little sensitivity to the jet strength. There is sensitivity to the distance between the jet and the TC, with secondary eyewall formation evident when their separation is 15° latitude but not when the separation exceeds 20°.

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