Author: Zegmund O. BlevissPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 446
Book Description
Interference Effects in Supersonic Flow
Author: Zegmund O. BlevissPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 446
Book Description
Interference effects from total-pressure rakes in supersonic flow
Author: Vernon Albert LeePublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 32
Book Description
Foreplane-wing Interference Effects in Supersonic Flow
Author: Roland Duane JenisonPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 130
Book Description
An experimental investigation of interference effects due to relative proximity of static-pressure probes in supersonic flow
Author: John Lewis LindseyPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 44
Book Description
Interference Effects Due to Relative Proximity of Static-pressure Probes in Supersonic Flow
Author: J. L. LindseyPublisher:
ISBN:
Category :
Languages : en
Pages : 53
Book Description
An experimental investigation was conducted in a supersonic wind tunnel to determine the minimum critical spacing for no mutual interference of two cone-cylinder-type static-pressure probes designed for simultaneous pressure measurement in supersonic flow. Tests made over a Mach Number range of approximately 1.9 through 3.4 indicate that the minimum critical spacing is predominately a function of Mach Number and static-orifice location. Probe cone-angle and probe diameter variations produce minor effects. A theoretical study of static-orifice location was also made. Results indicate that the generally recommended position of six to ten probe diameters aft of the cone shoulder is suitable for pressure measurement at Mach Numbers as high as approximately 3.5; however, higher velocities require static-orifice locations at greater distances from the cone shoulder. (Author).
Aerodynamic Interference of Two Axisymmetric Stores at Low Supersonic Speeds
Author: John E. BurkhalterPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 70
Book Description
A method for determining the basic pressure distribution on an axisymmetric body in supersonic flow has been evaluated. Supersonic line sources with linearly varying strengths placed along the centerline of the body were used to generate the body shape. The results of these theoretical computations for an isolated body agreed very well with experimental data. Two approaches were investigated to determine the pressure distribution on two bodies interfering with each other. In the first approach supersonic point sources were placed along an image line, as determined by subsonic theory, and along the body centerline. The strengths of these point sources were determined so that body boundary conditions were met on top and bottom of each interfering body. Computational problems were encountered with this techniuqe resulting from the nature of induced velocities from a supersonic point source and the approach was finally abandoned. The second interference approach utilized linearly varying line sources placed along an image line and along the body centerline. The location of the image line is solely a function of the delta-x interval chosen for the problem. As before, body boundary conditions were met on top and on bottom of each interfering body. The results of these computations appear realistic for thin bodies.
Reverse Flow and Supersonic Interference
Author: Brown University. Division of EngineeringPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 106
Book Description
Interference Effects Produced by Gaseous Side-jets Issuing Into a Supersonic Stream
Author: F. MAURERPublisher:
ISBN:
Category :
Languages : en
Pages : 89
Book Description
Experimental and theoretical investigations are made of flow fields resulting from lateral injection of a gaseous control jet from slot nozzles of finite length into a gaseous main stream at supersonic speeds. The experimental work is restricted to injection of cold air into a windtunnel flow over a flat plate at zero angle of attack. The experimental results consist of pressure distributions and normal force coefficients, as well as schlieren and oil-film photographs. On the basis of the observed results, a model is developed for analytical approximation. The calculated results, compared with the measured results, show the influence of the various parameters and give a better understanding of the flow processes. (Author).
External Interference Effects of Flow Through Static-pressure Orifices of Airspeed Head at Several Supersonic Mach Numbers and Angles of Attack [with List of References]
![External Interference Effects of Flow Through Static-pressure Orifices of Airspeed Head at Several Supersonic Mach Numbers and Angles of Attack [with List of References] PDF](https://books.google.com/books/content/images/frontcover/GS5oQwAACAAJ?fife=w80-h100)
Author: Aerodynamic Interference Between High-speed Slender Bodies
Author: Ross ChaplinPublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
Significant aerodynamic interference can occur between high-speed bodies in close proximity. A complex flowfield develops where shock and expansion waves from a generator body impinge upon the adjacent receiver body. The pressure and flow angularity changes which occur across these disturbances modify the body aerodynamics. The aim of this research is to quantify the aerodynamic interference effects for multi-body configurations and understand the relevant flow physics. The interference aerodynamics for slender bodies in a supersonic flow were investigated through a parametric wind tunnel study. The receiver bodies were finned and un-finned configurations. The effect of lateral and axial body separations, receiver incidence and the strength of the disturbance field were investigated. Measurements included forces and moments, surface pressures and flow visualisations. Supporting computations using steady-state, viscous predictions provided a deeper understanding of the underlying aerodynamics and flow mechanisms. Good agreement was found between the measured and predicted interference loads and surface pressures for all configurations. The interference loads are strongly dependent upon the axial impingement location of the primary shockwave. These induced loads change polarity as the impingement location moves aft over the receiver. The magnitude of the interference loads increase when the receiver is at incidence and are amplified by up to a factor of three when rear fins are attached. In general, the interference loads are larger for a stronger disturbance flowfield. The centre of pressure location is substantially affected and the static stability of the finned receiver changes in some configurations. The effect of the aerodynamic interference on the body trajectories was assessed using an unsteady, Euler prediction in combination with a 6DOF dynamic model. This shows aerodynamiciiinterference can cause a collision between the bodies. Moreover, the initial interference loads dominate the subsequent body trajectories and static modelling can be used to evaluate the dynamic trajectories.