Aerodynamics of Missiles Wih Offset Fin Configurations PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Aerodynamics of Missiles Wih Offset Fin Configurations PDF full book. Access full book title Aerodynamics of Missiles Wih Offset Fin Configurations by Gregg L. Abate. Download full books in PDF and EPUB format.
Author: Gregg L. Abate
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 12
Get Book Here
Book Description
Author: Gregg L. Abate
Publisher:
ISBN:
Category : Aerodynamic measurements
Languages : en
Pages : 12
Get Book Here
Book Description
Author: Carl P. Tilmann
Publisher:
ISBN:
Category : Technology & Engineering
Languages : en
Pages : 166
Get Book Here
Book Description
A wall-mounted semi-cylindrical model fitted with a single wrap- around in (WAF) has been investigated numerically and experimentally, with the objective of characterizing the mean and turbulent flowfield near a WAF in a supersonic flowfield. Numerical and experimental results are used to determine the nature of the flowfield and quantify the effects of fin curvature on the character of the flow near WAFs. This research has been motivated by the need to identify possible sources of a high-speed rolling moment reversal observed in sub-scale flight tests. Detailed mean flow and turbulence measurements were obtained in the AFIT Mach 3 wind tunnel using conventional probes and cross-wire hot-film anemometry at a series of stations upstream of and aft of the fin shock/boundary layer interaction. Hot-film anemometry results showed the turbulence intensity and Reynolds shear stress in the fuselage boundary layer to be far greater on the concave side of the fin than on the convex side. Mean flow was also obtained in the AFIT Mach 5 wind tunnel using conventional pressure probes. Numerical results were also obtained at the test conditions employing the algebraic eddy viscosity model of Baldwin and Lomax. Correlation with experimental data suggests that the calculations have captured the flow physics involved in this complicated flowfield. The calculations, corroborated by experimental results, indicate that a vortex exists in the fin/body juncture region on the convex side of the fin. This feature is not captured by the oft- used inviscid methods, and can greatly influence the pressure loading on the fin near the root.
Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 506
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Air warfare
Languages : en
Pages : 376
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 980
Get Book Here
Book Description
Author: Jerry M. Allen
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 64
Get Book Here
Book Description
Abstract: A wind-tunnel investigation has been performed at low supersonic speeds (at Mach numbers of 1.60, 1.90, and 2.16) to evaluate the aerodynamic characteristics of a missile concept capable of being tube launched and controlled with a simple one-axis canard controller. This concept, which features and axisymmetric body with two planar canards and four wraparound tail fins arranged in opposing pairs, must be in rolling motion to be controllable in any radial plane with the planar canards. Thus, producing a constant rolling moment that is invariant with speed and attitude to provide the motion is desirable. Two tail-fin shaping designs, one shaved and one beveled, were evaluated for their efficiency in producing the needed rolling moments, and the results showed that the shaved fins were much more desirable for this task than the beveled fins.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 460
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 568
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 598
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 730
Get Book Here
Book Description
