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Supersonic Aerodynamic Characteristics Of A Series Of Wrap Around Fin Missile Configurations
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Book Synopsis Supersonic Aerodynamic Characteristics of a Series of Wrap-around-fin Missile Configurations by : Roger H. Fournier
Download or read book Supersonic Aerodynamic Characteristics of a Series of Wrap-around-fin Missile Configurations written by Roger H. Fournier and published by . This book was released on 1977 with total page 180 pages. Available in PDF, EPUB and Kindle. Book excerpt: A parametric study of wrap-around-fin missile configurations has been conducted at Mach numbers from 1.60 to 2.86 in the Langley Unitary Plan wind tunnel. The fin configurations investigated included variations in chord length, leading-edge sweep, thickness ratio, and leading-edge shape. The investigation also included a smooth and a stepped-down afterbody required for flush retraction of the wrap-around-fin configuration.
Book Synopsis Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations. 1: Axisymmetric Inlets at Supersonic Speeds by : Clyde Hayes
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:
Book Synopsis Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations. 2: Two-dimensional Inlets at Supersonic Speeds by : Clyde Hayes
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations. 2: Two-dimensional Inlets at Supersonic Speeds written by Clyde Hayes and published by . This book was released on 1983 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails by : Jerry M. Allen
Download or read book Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails written by Jerry M. Allen and published by . This book was released on 1994 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations: Axisymmetric inlets at supersonic speeds by : Clyde Hayes
Download or read book Aerodynamic Characteristics of a Series of Twin-inlet Air-breathing Missile Configurations: Axisymmetric inlets at supersonic speeds written by Clyde Hayes and published by . This book was released on 1983 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel by : Donald E. Coletti
Download or read book Investigation of the Aerodynamic Characteristics of the NACA RM-10 Missile (with Fins) at a Mach Number of 1.62 in the Langley 9-inch Supersonic Tunnel written by Donald E. Coletti and published by . This book was released on 1952 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Aerodynamic Characteristics of Conformal Carriage Monoplaner Circular Missile Configurations with Low-profile Quadriform Tail Fins by : A. B. Blair
Download or read book Supersonic Aerodynamic Characteristics of Conformal Carriage Monoplaner Circular Missile Configurations with Low-profile Quadriform Tail Fins written by A. B. Blair and published by . This book was released on 1990 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1992 with total page 458 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Static Aerodynamic Stability Characteristics of a Body of Revolution with Wraparound Fins at Mach Numbers from 1.6 to 2.86 by : John E. Vaughn
Download or read book Static Aerodynamic Stability Characteristics of a Body of Revolution with Wraparound Fins at Mach Numbers from 1.6 to 2.86 written by John E. Vaughn and published by . This book was released on 1972 with total page 322 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted in the NASA Langley Unitary Plan wind tunnel for several wraparound fins with straight and with swept leading edge mounted on bodies of revolution. Mach number ranged from 1.6 to 2.86 while angle of attack was varied from -6 degrees to 6 degrees at 0 degrees sideslip angle. Six component aerodynamic force and moment data were recorded on the complete missile configuration while simultaneously recording the aerodynamic normal force and bending moments acting on each fin. The results of these tests are presented herein in plotted form. The number designation given the test is UPWT 980.
Book Synopsis Investigation of the Aerodynamic Characteristics of a Model of a Rocket Missile with Several Arrangements of Folding Fins at Mach Numbers of 1.75, 2.15, 2.48, and 2.87 by :
Download or read book Investigation of the Aerodynamic Characteristics of a Model of a Rocket Missile with Several Arrangements of Folding Fins at Mach Numbers of 1.75, 2.15, 2.48, and 2.87 written by and published by . This book was released on 1960 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722388348 Total Pages :58 pages Book Rating :4.3/5 (883 download)
Book Synopsis Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails by : National Aeronautics and Space Administration (NASA)
Download or read book Experimental Study at Low Supersonic Speeds of a Missile Concept Having Opposing Wraparound Tails written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: A wind-tunnel investigation has been performed at low supersonic speeds (at Mach numbers of 1.60, 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 an 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. Allen, Jerry M. and Watson, Carolyn B. Langley Research Center...
Book Synopsis Supersonic Aerodynamic Characteristics of a Cruciform Missile Configuration with Low-a-spect-ratio Wings and In-line Tail Controls by :
Download or read book Supersonic Aerodynamic Characteristics of a Cruciform Missile Configuration with Low-a-spect-ratio Wings and In-line Tail Controls written by and published by . This book was released on 1964 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Characterization of the Flowfield Near a Wrap-Around Fin at Supersonic Speeds by : Carl P. Tilmann
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.
Book Synopsis Effect on Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers by : A. B. Blair
Download or read book Effect on Tail-fin Span on Stability and Control Characteristics of a Canard-controlled Missile at Supersonic Mach Numbers written by A. B. Blair and published by . This book was released on 1983 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Supersonic Aerodynamic Characteristics of the Active Laser Seeker (ALS) Configuration of a Proposed Maneuvering Air-to-air Missile Design by : D. H. Fikes
Download or read book Supersonic Aerodynamic Characteristics of the Active Laser Seeker (ALS) Configuration of a Proposed Maneuvering Air-to-air Missile Design written by D. H. Fikes and published by . This book was released on 1977 with total page 92 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Characteristics and Fin Loads of a Bank-to-Turn, Air-to-Air Missile Concept at Supersonic Mach Numbers by : D. H. Fikes
Download or read book Aerodynamic Characteristics and Fin Loads of a Bank-to-Turn, Air-to-Air Missile Concept at Supersonic Mach Numbers written by D. H. Fikes and published by . This book was released on 1977 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Static stability, axial-force, and fin-loading data were obtained on a proposed maneuvering air-to-air missile at Mach numbers 1.5, 2.5, and 3.5 with various combinations of fin control surface deflections. The angle-of-attack range was from -2 to 28 deg at constant angles of sideslip of -8, -4, 0, 4, and 8 deg. The test Reynolds number was 4.25 million, based on free-stream conditions and model length, at each Mach number. Results are presented illustrating the effects of control surface deflections, Mach number, and model attitude on missile and fin aerodynamic characteristics. (Author).
Book Synopsis Supersonic Aerodynamic Characteristics of a Sparrow 3 Type Missile Model with Wing Controls and Comparison with Existing Tail-control Results by :
Download or read book Supersonic Aerodynamic Characteristics of a Sparrow 3 Type Missile Model with Wing Controls and Comparison with Existing Tail-control Results written by and published by . This book was released on 1977 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
