Author: Brown University. Division of EngineeringPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 106
Book Description
Reverse Flow and Supersonic Interference
Author: Brown University. Division of EngineeringPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 106
Book Description
Reverse-flow Integral Methods for Second-order Supersonic Flow Theory
Author: Joseph Henry ClarkePublisher:
ISBN:
Category :
Languages : en
Pages : 42
Book Description
A general reverse-flow relation is obtained within the framework of second-order (in surface deflection) supersonic flow theory. From this it is shown that the second-order increment in the drag of an arbitrary quasicylindrical body can be expressed as surface and volume integrals of the first-order solutions corresponding to forward and reverse flow past the body. Analogous results are obtained for second-order transverse forces and moments on an arbitrary quasiplanar wing, except the first-order reverse flow must correspond to certain zero-thickness wings. Other similar results are possible. Thus, second order aerodynamic forces on bodies may be obtained from first-order solutions by quadrature. It is also shown that the reverse-flow integral relation can yield the pressure distribution on the surface by inversion of an integral equation constructed therefrom. It is thought that these results should be particularly useful for the Mach number range between that of linearized theory and that of full hypersonic small-disturbance theory. (Author).
Uniform Second-order Solution for Supersonic Flow Over Delta Wing Using Reverse-flow Integral Method
Author: Joseph Henry ClarkePublisher:
ISBN:
Category :
Languages : en
Pages : 60
Book Description
The problem of supersonic flow over an inclined flatplate delta wing with supersonic edges is solved to second order in incidence. This solution for surface pressure is uniform and fully analytic. The approach utilizes a reverse-flow integral method previously developed for secondorder problems. This method is augmented by a number of techniques appropriate to its framework. The simplification over standard techniques acgieved by using these reverse-flow methods is quite substantial and makes the problem tractible. Reverse-flow procedures give a volume-surface integral relation that connects the second-order forward flow over the body of interest with the linearized reverse-flow over a related body. A singular integral equation is generated from the integral relation by introducing the edge sweep of the reverse-flow wing as a free parameter. An inversion is available which gives the second-order solution on the surface of the wing. The solution is then made uniformly valid using techniques previously developed. (Author).
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
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.
On Wing-body Interference in Supersonic Flow
Author: K. StewartsonThe Interference Between Two Intersecting Perpendicular Two-dimensional Supersonic Flow Fields
Author: Marten T. LandahlPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 38
Book Description
Some interference problems in linearised supersonic flow
Author: Henry PortnoyThe Wing-body Interference Problem for Linearized Supersonic Flow
Author: Michael Chen-Chiang FongPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
Book Description