Download or read book Aerodynamic Test and Analysis of Wrap around Fins at Supersonic Mach Numbers Utilizing Design of Experiments written by Mark W. Swenson and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 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 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.
Download or read book Experimental Investigation of Supersonic Wrap around Fin Aerodynamic Mach Number Effects written by Thomas C. McIntyre and published by . This book was released on 1999 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aerodynamic Characteristics of Wrap Around Fins Including Fold Angle at Mach Numbers from 0 5 to 3 0 written by C. W. Dahlke and published by . This book was released on 1974 with total page 367 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the McDonnell Douglas Aerophysics Laboratory 4-foot trisonic wind tunnel to study the aerodynamic characteristics of wrap around fins. Wrap around fins with leading edge sweep angle and exposed semi-span variations were tested. One unswept fin was tested simulating various opening angles from 10 degrees beyond fully open to a folding angle of 112.5 degrees. Force and moment data were obtained at Mach Numbers from 0.5 to 3.0 at angles of attack up to 14 degrees and roll angles from 0 to 45 degrees. The complete results of this test are presented in plotted form for the main balance and all four fin balances.
Download or read book 37th AIAA Aerospace Sciences Meeting and Exhibit written by and published by . This book was released on 1999 with total page 668 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aerodynamic Characteristics of Wrap Around Fins Including Fold Angle at Mach Numbers from 0 5 to 1 3 written by C. W. Dahlke and published by . This book was released on 1974 with total page 517 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the transonic wind tunnel to study the aerodynamic characteristics of wrap-around fins. Wrap-around fins with leading edge sweep angle on straight and step down bodies were tested. One unswept fin was tested simulating various opening angles from 10 degrees beyond fully open to a folding angle of 112.5 degrees. Force and moment data were obtained at Mach numbers from 0.5 to 1.3 at angles of attack up to 14 degrees and roll angles from 0 to 67.5 degrees. The results of the test are presented in plotted form for the main balance and all four fin balances.
Download or read book 32nd Aerospace Sciences Meeting Exhibit 94 0180 94 0219 written by and published by . This book was released on 1994 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1991 with total page 1102 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Aerodynamics of Wrap around Fins in Supersonic Flow written by and published by . This book was released on 2005 with total page 73 pages. Available in PDF, EPUB and Kindle. Book excerpt: Existing supersonic fin theory has been modified to compute the pressure distribution over Wraparound Fin (WAF). Evvard's theory has been used to calculate the pressure loading due to Angle-of-Attack (AoA) on a WAF by including fin curvature as a variable in the definition of zones of influence. Evvard's theory uses the intersections of the fin surface and the Mach cones originating from the leading edge discontinuities to split the fin surface into regions of influence. For a planar fin, the intersections are linear; however, the intersections on a curved fin form curved lines. By redefining the Mach lines to account for fin curvature and using an empirically derived induced AoA, the application of Evvard's theory can be extended to accurately compute the unique aerodynamic characteristic of WAFs.
Download or read book The Finding Guide to AIAA Meeting Papers written by American Institute of Aeronautics and Astronautics. Technical Information Service and published by . This book was released on 1994 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Aerodynamic Characteristics of Wrap around Fins at Mach Numbers of 0 3 to 3 0 written by C. Wayne Dahlke and published by . This book was released on 1976 with total page 61 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results of investigations into many of the geometric and flow parameters influencing the aerodynamics of wrap-around fins are presented in this report. Particular emphasis is placed on defining static and dynamic roll characteristics between Mach numbers of 0.3 to 3.0. Among the geometric parameters highlighted are fin span, aspect ratio, leading edge sweep, leading edge shape, fin opening angle, and afterbody geometry. Comparisons of static stability, dynamic stability, and drag are made between the flat and the wrap- around fin. Problems associated with measurement of wrap-around fin rolling mounts are also discussed. An overview of the wrap-around fin roll moment characteristics are presented as an aid for making estimates and establishing testing techniques. This report supercedes RD-73-17.
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:
Download or read book The Aerodynamic Characterictics of Wrap around Fins at Mach Numbers of 0 3 to 3 0 written by C. W. Dahlke and published by . This book was released on 1976 with total page 60 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Investigation at Mach Numbers of 0 20 to 3 50 of Blended Wing body Combinations of Sonic Design with Diamond Delta and Arrow Plan Forms written by George H. Holdaway and published by . This book was released on 1960 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
