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Author : Gregg L. Abate
Publisher :
ISBN 13 :
Total Pages : 12 pages
Book Rating : 4.3/5 (91 download)
Download or read book Aerodynamics of Missiles Wih Offset Fin Configurations written by Gregg L. Abate and published by . This book was released on 1989 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Gregg L. Abate
Publisher :
ISBN 13 :
Total Pages : 10 pages
Book Rating : 4.:/5 (227 download)
Download or read book Aerodynamics of Missiles with Offset Fin Configurations written by Gregg L. Abate and published by . This book was released on 1989 with total page 10 pages. Available in PDF, EPUB and Kindle. Book excerpt: Subsonic and transonic aerodynamic data for offset fin configurations are presented. Free-flight aeroballistic tests to obtain this data were conducted at atmospheric pressure over a Mach number range of 0.6 to 1.6. The aerodynamic coefficients and derivatives presented were extracted from the position-attitude-time histories of the experimentally measured trajectories using nonlinear numerical integration data reduction routines. Results of this testing and analysis show the static and dynamic stability variations for four different fin offset configurations. The presence of a side moment dependent on pitch angle results in dynamic instability under certain conditions. The stability boundaries associated with this side moment are mapped. Designers should be consider this moment whenever offset fins are utilized. Keywords: Offset fins; Missile stability; Flexible fins; Aerodynamics; Dynamic stability; Side moments. (JHD).
Author : Carl P. Tilmann
Publisher :
ISBN 13 :
Total Pages : 166 pages
Book Rating : 4.3/5 (91 download)
Download or read book Characterization of the Flowfield Near a Wrap-Around Fin at Supersonic Speeds written by Carl P. Tilmann and published by . This book was released on 1998 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 : Gregg L. Abate
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (11 download)
Download or read book Aerodynamics of Missiles with Slotted Fin Configurations written by Gregg L. Abate and published by . This book was released on 1991 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Roger S. Gates
Publisher :
ISBN 13 :
Total Pages : 14 pages
Book Rating : 4.3/5 (91 download)
Download or read book Aerodynamic Test and Analysis of a Slender Generic Missile Configuration written by Roger S. Gates and published by . This book was released on 1989 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 506 pages
Book Rating : 4.E/5 ( download)
Download or read book Technical Reports Awareness Circular : TRAC. written by and published by . This book was released on 1989-11 with total page 506 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William J. Monta
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (317 download)
Download or read book Aerodynamic Characteristics at Mach Numbers from 1.60 to 2.16 of a Blunt-nose Missile Model Having a Triangular Cross Section and Fixed Triform Fins written by William J. Monta and published by . This book was released on 1971 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Frankie Gale Moore
Publisher :
ISBN 13 :
Total Pages : 148 pages
Book Rating : 4.3/5 (91 download)
Download or read book An Improved Semiempirical Method for Calculating Aerodynamics of Missiles with Noncircular Bodies written by Frankie Gale Moore and published by . This book was released on 1997 with total page 148 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James DeSpirito
Publisher :
ISBN 13 :
Total Pages : 212 pages
Book Rating : 4.3/5 (91 download)
Download or read book Numerical Investigation of Aerodynamics of Canard-controlled Missile Using Planar and Grid Tail Fins written by James DeSpirito and published by . This book was released on 2004 with total page 212 pages. Available in PDF, EPUB and Kindle. Book excerpt: Viscous computational fluid dynamic simulations were used to predict the aerodynamic coefficients and flow field around a canard-controlled missile in subsonic and transonic flow. Computations were performed at Mach 0.6 and 0.9, six angles of attack between 0 deg and 10 deg, and with planar and grid tail fins. The computations were validated with wind tunnel data. Flow visualizations showed that the canard downwash produced a low-pressure region on the starboard side of the missile that produced a large induced side force. The canard trailing vortices interacted with the tail fins until alpha> 8 deg, producing a pressure differential on the leeward tail fin, leading to the adverse induced roll effects. Visualizations of the flow through the grid fin structure showed choking of the flow at Mach 0.9 and Mach 1.5. The validated simulations results showed that grid fins did not improve the canard roll-control effectiveness at subsonic and transonic speeds as well as they did at the low supersonic speed.
Author : Calvin Wayne Dahlke
Publisher :
ISBN 13 :
Total Pages : 376 pages
Book Rating : 4.3/5 (91 download)
Download or read book Aerodynamic Characteristics of Wraparound Fins Mounted on Bodies of Revolution and Rheir Influence on the Missile Static Stability at Mach Numbers from 0.3 to 1.3 written by Calvin Wayne Dahlke and published by . This book was released on 1972 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted for several wraparound fins and one planar fin configuration on bodies of revolution at Mach number ranging from 0.3 to 1.3 and angles of attack from -6 degrees to 6 degrees at 0 degrees at sideslip angle. Six component aerodynamic forces and moments were recorded on the complete missile configuration while simultaneously measuring the aerodynamic normal force and bending moments acting on each fin. The fin configuration parameters varied include chord length, fin thickness, leading edge configuration, tip chord geometry and body, root chord gap. The report presents the plotted coefficient data in two volumes. Volume I contains the complete missile aerodynamic data. Volume 2 contains the individual fin aerodynamic data.
Author :
Publisher :
ISBN 13 :
Total Pages : 376 pages
Book Rating : 4.E/5 ( download)
Download or read book Subsystem Integration for Tactical Missiles ( SITM ) and Design and Operation of Unmanned Air Vehicles ( DOUAV ) written by and published by . This book was released on 1996 with total page 376 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : G. R. Gomillion
Publisher :
ISBN 13 :
Total Pages : 404 pages
Book Rating : 4.3/5 (91 download)
Download or read book A Compilation of Static Stability and Fin Loads Data for Slender Body Missile Models with and Without Tail Fins and Wings written by G. R. Gomillion and published by . This book was released on 1976 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt: This document contains a compilation of aerodynamic data for the Martin Generalized Research Model, which is a composite of several body, wing, and tail fin configurations typical of missile applications. The model variations included five body configurations, three wing configurations at various body locations, and 15 tail fin configurations. Static stability and tail fin loads data are presented in tabulated and plotted form for a Mach number range from 0.20 to 4.63 over an angle-of-attack range from -6 to 60 deg and a sideslip angle range from -20 to 20 deg for the body-alone configurations, body-wing configurations, and the body-wing-tail fin configurations. In addition, the tail fin configurations were tested using the reflection plane technique, and the resulting fin loads data are presented for a Mach number range of 0.80 to 2.16 over an angle-of-attack range from 0 to 210 deg. Volume I contains the narrative and selected plotted data. (Author).
Author : Frank G. Moore
Publisher :
ISBN 13 : 9781423545590
Total Pages : 78 pages
Book Rating : 4.5/5 (455 download)
Download or read book A Simplified Method for Predicting Aerodynamics of Multi-Fin Weapons written by Frank G. Moore and published by . This book was released on 1999-03-01 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new semiempirical method was developed to compute aerodynamics of multi-fin missile configurations using cruciform missile aerodynamics as a baseline. The method was developed using full Euler Computational Fluid Dynamics codes to compare computations with wind tunnel data bases for cruciform missiles as a function of Mach number, angle of attack, and aspect ratio. The Euler codes were then used for the same free stream conditions and missile configurations except the number of fins were increased from four to six and eight respectively. A table of coefficients was then formed for the aerodynamics of six- and eight-fin configurations compared to that of four-fin cases for use in the aeroprediction code or other semiempirical codes. It was concluded that this approach worked well except for subsonic Mach numbers at moderate to large angles of attack, where the Euler codes failed to predict the leeward plane flow field adequately. It is believed that full Navier-Stokes solutions could be used to improve upon this semiempirical model. Engineering judgement, in conjunction with low angle-of-attack Euler solutions were used in the regions where Euler solutions were suspect. In comparing the new semiempirical method to a limited amount of wind tunnel data on several configurations, it was concluded that the model worked well at all the conditions where data was available. However, additional wind tunnel data at higher angles of attack on six- and eight-fin configurations is needed before the method can be truly validated.
Author : Clyde Hayes
Publisher :
ISBN 13 :
Total Pages : 284 pages
Book Rating : 4.:/5 (317 download)
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations. 1: Axisymmetric Inlets at Supersonic Speeds written by Clyde Hayes and published by . This book was released on 1983 with total page 284 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 980 pages
Book Rating : 4.F/5 ( download)
Download or read book International Aerospace Abstracts written by and published by . This book was released on 1998 with total page 980 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781721146192
Total Pages : 116 pages
Book Rating : 4.1/5 (461 download)
Download or read book Aerodynamics of an Axisymmetric Missile Concept Having Cruciform Strakes and In-Line Tail Fins from Mach 0. 60 To 4. 63 written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study has been performed to develop a large force and moment aerodynamic data set on a slender axisymmetric missile configuration having cruciform strakes and in-line control tail fins. The data include six-component balance measurements of the configuration aerodynamics and three-component measurements on all four tail fins. The test variables include angle of attack, roll angle, Mach number, model buildup, strake length, nose size, and tail fin deflection angles to provide pitch, yaw, and roll control. Test Mach numbers ranged from 0.60 to 4.63. The entire data set is presented on a CD-ROM that is attached to this paper. The CD-ROM also includes extensive plots of both the six-component configuration data and the three-component tail fin data. Selected samples of these plots are presented in this paper to illustrate the features of the data and to investigate the effects of the test variables. Allen, Jerry M. Langley Research Center WU 23-090-20-35
Author :
Publisher :
ISBN 13 :
Total Pages : 356 pages
Book Rating : 4.0/5 ( download)
Download or read book Missile Aerodynamics written by and published by . This book was released on 1974 with total page 356 pages. Available in PDF, EPUB and Kindle. Book excerpt:
