Download or read book A Summary of Aerodynamic Characteristics for Wrap around Fins from Mach 0 3 to 3 0 written by James A. Humphrey and published by . This book was released on 1977 with total page 234 pages. Available in PDF, EPUB and Kindle. Book excerpt: Wrap-around fin effectiveness for tube-launched missiles was investigated in a series of 6 wind tunnel tests. Wind tunnels were AEDC Propulsion Wind Tunnel, NASA/Langley Research Center Unitary Plan Wind Tunnel and McDonnell Douglas 4-foot Trisonic Wind Tunnel. Mach number range was 0.3 to 3.0. Basic model was a 2-caliber secant ogive nose with an 8-caliber cylindrical afterbody and 21 fin configurations. Variations in the coefficients are presented for changes in fin geometry including taper ratio and leading edge sweep angle, aspect ratio, exposed semi-span, and root chord length; opening angle, fully closed to 10 deg past fully open; and body step down.
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 606 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.
Download or read book NASA Technical Memorandum written by and published by . This book was released on 1976 with total page 1068 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1978 with total page 1008 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Static Aerodynamic Stability Characteristics of a Body of Revolution with Wraparound Fins at Mach Numbers from 0 5 to 1 3 written by John E. Vaughn and published by . This book was released on 1972 with total page 306 pages. Available in PDF, EPUB and Kindle. Book excerpt: Experimental aerodynamic investigations were conducted in the AEDC-4T wind tunnel for several wraparound fins with straight and with swept leading edge mounted on bodies of revolution. Mach number ranged from 0.50 to 1.30 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 in plotted form. (Author).
Download or read book A Collection of Technical Papers written by and published by . This book was released on 1985 with total page 564 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
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.
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.
Download or read book Government Reports Annual Index written by and published by . This book was released on 1975 with total page 882 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book 31st Aerospace Sciences Meeting and Exhibit 93 0450 93 0499 written by and published by . This book was released on 1993 with total page 628 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Magnus Measurements of the 10 Caliber Army Navy Spinner Projectile with Wrap around Fins written by Frank J. Regan and published by . This book was released on 1970 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: A research configuration was formed by attaching wraparound fins in a cruciform arrangement to a 10-caliber Army-Navy spinner projectile. This configuration was tested in a supersonic tunnel to get the Magnus force and moment, as well as the normal force and pitching moment. Model spin rate was generated by means of fin cant.
Download or read book Collection of Technical Papers on Atmospheric Flight Mechanics written by and published by . This book was released on 1974 with total page 330 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Hole Size on Single row and Multirow Ejection written by Herman W. Prust and published by . This book was released on 1976 with total page 216 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aeronautical Engineering written by and published by . This book was released on 1986 with total page 540 pages. Available in PDF, EPUB and Kindle. Book excerpt: A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
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:
