A Theoretical Model of the Near Wake of a Slender Body in Supersonic Flow

AIAA Journal ◽  
1972 ◽  
Vol 10 (9) ◽  
pp. 1165-1172 ◽  
Author(s):  
JOHN T. OHRENBERGER ◽  
ERIC BAUM
Keyword(s):  
Theoretical Model ◽  
Supersonic Flow ◽  
Slender Body ◽  
Near Wake

The Supersonic Flow Field Associated with a Conical Flame Sheet

1970 ◽  
Vol 21 (4) ◽  
pp. 368-378 ◽  
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.

The Slender Wing with a Half Body of Revolution Mounted Beneath

1968 ◽  
Vol 72 (693) ◽  
pp. 803-807 ◽  
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.

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.

Experimental Investigation of the Effects of Base Mass Addition on the Near Wake of a Slender Body

AIAA Journal ◽  
1971 ◽  
Vol 9 (8) ◽  
pp. 1506-1513 ◽  
Author(s):  
JOHN E. LEWIS ◽  
WILHELM BEHRENS ◽  
DONALD J. COLLINS
Keyword(s):  
Experimental Investigation ◽  
Slender Body ◽  
Near Wake

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.

Sign in / Sign up

Export Citation Format

Share Document