Analytical prediction of the base pressure resulting from hot, axisymmetric jet interaction in supersonic flow

1981 ◽  
Author(s):  
J. FOX ◽  
R. BAUER
Keyword(s):  
Supersonic Flow ◽  
Base Pressure ◽  
Analytical Prediction ◽  
Jet Interaction ◽  
Axisymmetric Jet

The Effect of Sting Diameter and Length on Base Pressure at M = 3·88

1968 ◽  
Vol 19 (4) ◽  
pp. 368-374 ◽  
Author(s):  
Walter R. Sieling
Keyword(s):  
Supersonic Flow ◽  
Axisymmetric Body ◽  
Base Pressure ◽  
Base Diameter ◽  
Apparent Change

SummaryThe effects of sting diameter and cylindrical protuberance length on the base pressure of an axisymmetric body in a turbulent supersonic flow are experimentally determined. It is found that the change in base pressure due to the presence of the sting is greater than 4 per cent when the ratio of sting diameter to base diameter is 0·150 or greater. When the ratio of cylindrical protuberance length to base diameter is greater than 1·3 there is no apparent change in base pressure with a change in length. However, when this ratio is less than 1·3, the base pressure varies greatly with length.

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

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.

The effect of base bleed on vortex shedding and base pressure in compressible flow

1981 ◽  
Vol 110 ◽  
pp. 273-292 ◽  
Author(s):  
F. Motallebi ◽  
J. F. Norbury
Keyword(s):  
Supersonic Flow ◽  
Compressible Flow ◽  
Vortex Shedding ◽  
Transonic Flow ◽  
Vortex Formation ◽  
Base Pressure ◽  
Trailing Edge ◽  
Blunt Trailing Edge ◽  
Base Bleed ◽  
The Relationship

Experiments have been carried out to investigate the phenomenon of vortex shedding from the blunt trailing edge of an aerodynamic body in transonic and supersonic flow. The effect of a discharge of bleed air from a slot in the trailing edge has been included and the relationship between the vortex formation and base pressure has been considered.In transonic flow a small amount of bleed air was found to produce a rearward shift in the point of origin of the vortices with a consequent substantial increase in base pressure. The effect was less marked in supersonic flow. At higher rates of bleed two different regimes of vortex shedding were identified and increase in bleed rate caused a reduction in base pressure. For bleed rates giving near-maximum base pressure no vortex shedding occurred.

Review and development of base pressure and base heating correlations in supersonic flow

1995 ◽  
Vol 32 (1) ◽  
pp. 8-23 ◽  
Author(s):  
J. Parker Lamb ◽  
William L. Oberkampf
Keyword(s):  
Supersonic Flow ◽  
Base Pressure

Two Different Theoretical Approaches to the Base Pressure Problem in Two-Dimensional Supersonic Flow

1978 ◽  
Vol 29 (2) ◽  
pp. 114-130 ◽  
Author(s):  
M. Tanner
Keyword(s):  
Supersonic Flow ◽  
Flow Model ◽  
The Body ◽  
Experimental Results ◽  
Base Pressure ◽  
Two Dimensional ◽  
Reattachment Point ◽  
Fundamental Idea ◽  
Entropy Increase ◽  
Theoretical Approaches

SummaryThe basic physical idea underlying the theories based on the flow model of CHAPMAN and KORST is that the base pressure can be predicted if the pressure at the reattachment point is known. In the new theory of TANNER the fundamental idea is the connection between the drag of the body and the entropy increase in the flow. This paper presents the essence of both theories together with theoretical and experimental results.

Jet Interaction in Supersonic Flow with a Downstream Surface Ramp

2005 ◽  
Vol 42 (1) ◽  
pp. 38-44 ◽  
Author(s):  
Y. H. Byun ◽  
K. J. Bae ◽  
S. Wallis ◽  
V. Viti ◽  
J. A. Schetz ◽  
...  
Keyword(s):  
Supersonic Flow ◽  
Jet Interaction

Two-Dimensional Boat-Tailed Bases in Supersonic Flow

1974 ◽  
Vol 25 (3) ◽  
pp. 210-224 ◽  
Author(s):  
P R Viswanath ◽  
R Narasimha
Keyword(s):  
Boundary Layer ◽  
Supersonic Flow ◽  
Free Stream ◽  
The Body ◽  
Base Pressure ◽  
Two Dimensional ◽  
Sharp Corner ◽  
Boundary Layer Effect ◽  
Pressure Distributions ◽  
Layer Effect

SummaryBoat-tailing of aft bodies may affect the base pressure through two mechanisms: firstly by changing the angle between the approaching flow at separation and the reattachment surface, and secondly by distorting the boundary layer through the favourable pressure gradient (which can be particularly severe in the presence of a sharp corner on the body). The first effect is isolated here by tests on inclined backward-facing steps with a fully developed turbulent boundary layer at separation, at free-stream Mach numbers of 1.75 and 2.4. It is found that the base pressure increases significantly with boat-tail angle; the data have been correlated taking explicit account of the boundary layer effect, modifying and extending the approach adopted by Nash. Charts are provided for quick estimation of base pressure in engineering calculations. Some of the earlier data on boat-tailed bases, on re-examination in the light of the present correlation, suggest that strongly distorted boundary layers at separation affect the base pressure appreciably. Several features of the measured reattachment pressure distributions, including their internal similarity, are also discussed.

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