Author: F. Carroll DoughertyPublisher:
ISBN:
Category : Boundary value problems
Languages : en
Pages : 40
Book Description
Aerodynamic Interference Between Stores
Author: F. Carroll DoughertyPublisher:
ISBN:
Category : Boundary value problems
Languages : en
Pages : 40
Book Description
Aerodynamic Interference of Wing-pylon-body Combinations at Low Subsonic Speeds
Author: Kenneth Boland WalkleyPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 120
Book Description
A method for determining the subsonic aerodynamic interference between a planar wing with pylons and a single axisymmetric body has been developed and evaluated. The wing and body solutions were obtained independently using a simple horseshoe vortex system and a three-dimensional point source distribution, respectively. A vortex image system based on the two-dimensional theory of images was then added to the body to maintain the tangent-flow boundary condition in the non-uniform wing flow field. Both the influence of the vortex image system within the body and the body flow field effects at the wing were evaluated. No significant change in the wing vortex strength distribution resulted so that it was unnecessary to iterate the isolated wing solution. The theoretical results for incompressible flow were compared with pressure distributions obtained from low-speed wind tunnel tests of the wing-body configuration. The correlation was generally good. (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.
Mutual Aerodynamic Interference Effects for Multiple Bodies by the Cross-flow Corrections Method
Author: Fred W. MartinPublisher:
ISBN:
Category : Cross-flow (Aerodynamics)
Languages : en
Pages : 66
Book Description
The complexity of the flow field beneath an aircraft with external stores is examined analytically. Equations are produced for computing store separation trajectories, based on mutual interference flow fields between the aircraft and the store. The circle theorem and the small disturbances theory are used in establishing the perturbations responsible for the flow field interference. (Author).
Aerodynamic Interference Effects on Various Weapon Shapes in the Flow Field of a Transonic Wing Configuration at Mach Numbers from 0.5 to 1.3
Author: G. R. MattasitsPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 270
Book Description
Tests were conducted in the Aerodynamic Wind Tunnel (4T) to evaluate the validity of weapon aerodynamics acquired from theoretical calculations which employed mathematical models to simulate actual test hardware and to assess the problems encountered during the separation of various weapon shapes, at transonic flight conditions, from the number one TER position. The data will also be used to aid in the development of a mathematical method for predicting store separation characteristics. Data were obtained at Mach numbers from 0.5 to 1.3. Force and pressure distribution measurements were obtained to assess the influence of angle of attack and both linear and angular store displacements from the carriage position. Store models were separated from a TER mounted on the inboard pylon of a half-span wing similar in planform to the wing of the F-4 aircraft. Data were obtained on 0.10-scale models of the M-117 and maximum volume bombs. Test results showed that large nose-down pitching-moment coefficients were encountered by all store models at the number one TER carriage position. Complete separation trajectories were obtained only at a Mach number of 0.5 for all 16-in.-diam store models. Decreasing store model diameter increased the maximum Mach number at which complete trajectories were obtained. (Author).
Aerodynamics of Store Integration and Separation
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Fluid Dynamics Panel. SymposiumPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 306
Book Description
Mutual Aerodynamic Interference Effects for Two Axisymmetric Bodies
Author: Fred W. MartinPublisher:
ISBN:
Category : Cross-flow (Aerodynamics)
Languages : en
Pages : 62
Book Description
The mutual aerodynamic interference problem for two axisymmetric bodies has been analyzed using the image system technique. In order to facilitate this analysis, it has been assumed that small perturbation solutions are valid. It is further assumed that the external stores are slender bodies and that the mutual interference can be analyzed by first assuming a cross-flow solution. The image system in the cross-flow plane consists of source-sink pairs appropriately located by using the Milne-Thomson circle theorem. The actual three-dimensional source-sink paris are displaced from the body axis according to the cross flow image system. Their strengths are then determined by the Rankine method. Good agreement has been found between the theoretical and experimental results. (Author).
Transonic Unsteady Aerodynamics and Aeroelasticity, 1987
Author: Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 684
Book Description
Annual Report of the National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 672
Book Description
Includes the Committee's Reports no. 1-1058, reprinted in v. 1-37.
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 456
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.