Download or read book An Investigation of Supersonic Delta Wings for Minimum Drag written by Ralph William Detra and published by . This book was released on 1951 with total page 90 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Preliminary Investigation at Supersonic Speeds of Triangular and Sweptback Wings written by Macon C. Ellis and published by . This book was released on 1949 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results from a supersonic wind-tunnel investigation of a series of thin triangular and sweptback wings are presented. The triangular wing series consisted of eight triangular wings of vertex angles such that a range of leading-edge postions both inside and outside the Mach cone at the test Mach numbers of 1.43 and 1.71 was obtained. The three swept wings had angles of sweep at 45, 55, and 63 degrees and were tested at a Mach number of 1.43.
Download or read book A Note on the Drag Due to Lift of Delta Wings at Mach Numbers Up to 2 0 written by Robert S. Osborne and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Effect of Some Section Modifications and Protuberances on the Zero lift Drag of Delta Wings at Transonic and Supersonic Speeds written by Carl A. Sandahl and published by . This book was released on 1954 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Reduction of Drag Due to Lift at Supersonic Speeds written by Douglas Aircraft Company and published by . This book was released on 1955 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: $EVERAL TOPICS RELATING TO THE REDUCTION OF DRAG DUE TO LIFT AT SUPERSONIC SPEEDS ARE DISCUSSED. The distribution of camber for optimial loading of diamond planform wings and some low drag geometries for rectangular wings are determined. It appears that substantial drag reduction, through the use of spanwise distribution of camber, may be achieved only for low reduced aspect ratios, M2-1 AR. The distribution of lift throughout volumes of prescribed shape is considered and some optimum distributions found for certain cases. It is shown that optimum spatial distributions of lift arc generally not unique. The possibility of using biplanes is explored and it is concluded that for non-interfering biplanes (wings acting as isolated monoplanes) there is an inherent structural advantage which is the result of a scale effect for geometrically similar structures The preacnt status of means for drag reduction is surveyed and the direction for further study indicated.
Download or read book Trim Drag at Supersonic Speeds of Various Delta planform Configurations written by M. E. Graham and published by . This book was released on 1960 with total page 104 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Supersonic Wave Drag of Nonlifting Delta Wings with Linearly Varying Thickness Ratio written by Arthur Henderson and published by . This book was released on 1952 with total page 51 pages. Available in PDF, EPUB and Kindle. Book excerpt: The supersonic wave drag of a nonlifting, symmetrical, double-wedge-profile, delta wing the thickness ratio of which varies linearly in the spanwise direction is calculated by means of linear theory. In general it is found that a delta wing with linearly varying thickness-ratio delta wing of the same plan form when both wings have either the same projected frontal area or the same internal volume. The thickness distributions for minimum drag and the corresponding values of the ratio of the drag of a linearly varying thickness-ratio wing to a constant-thickness ratio wing are found.
Download or read book The Proper Combination of Lift Loadings for Least Drag on a Supersonic Wing written by Frederick C. Grant and published by . This book was released on 1955 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The best combination of four loadings on a delta wing with subsonic leading edges is calculated for several Mach numbers as a numerical example. The loadings considered have finite pressures everywhere on the plan form. At each Mach number the optimum combination of the four non-singular loadings has about the same drag coefficient as a flat plate with leading-edge thrust.
Download or read book Supersonic Aerodynamics of Delta Wings written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-08 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt: Through the empirical correlation of experimental data and theoretical analysis, a set of graphs has been developed which summarize the inviscid aerodynamics of delta wings at supersonic speeds. The various graphs which detail the aerodynamic performance of delta wings at both zero-lift and lifting conditions were then employed to define a preliminary wing design approach in which both the low-lift and high-lift design criteria were combined to define a feasible design space. Wood, Richard M. Langley Research Center AERODYNAMICS; DELTA WINGS; INVISCID FLOW; SUPERSONIC AIRFOILS; SUPERSONIC SPEED; AERODYNAMIC LOADS; DESIGN ANALYSIS; EXPERIMENT DESIGN; FRICTION DRAG; LIFT; NONLINEAR SYSTEMS; WINGS...
Download or read book Investigation of the Aerodynamic Characteristics at High Supersonic Mach Numbers of a Family of Delta Wings Having Double wedge Sections with the Maximum Thickness at 0 18 Chord written by Mitchel H. Bertram and published by . This book was released on 1954 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt: A program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section has been conducted at the Langley 11-inch hypersonic tunnel. These wings had a maximum thickness of 8 percent of the chord located at the 18-percent-chord point. For the wings tested at a Mach number of 6.9, the semiapex angle was varied from 5 to 30 degrees and the wings were tested over a range of angle of attack from 0 to 28 degrees and Reynolds numbers in the range of 800,000 to 3,600,000 based on root chord. In addition, pertinent results from tests at Mach number as low as 1.62 have been utilized. The shock-expansion theory and the Newtonian impact theory have been used to analyze the effects of changes made in the various parameters investigated.
Download or read book Maximum Lift drag ratio Characteristics of Rectangular and Delta Wings at Mach 6 9 written by Jim A. Penland and published by . This book was released on 1965 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Integrated Approach to the Analysis and Design of Wings and Wing body Combinations in Supersonic Flow written by Ralph L. Carmichael and published by . This book was released on 1966 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Drag of a Delta Wing in Supersonic Flow written by Eugene A. Carpovich and published by . This book was released on 1949 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wing Theory in Supersonic Flow written by Elie Carafoli and published by Elsevier. This book was released on 2013-10-22 with total page 611 pages. Available in PDF, EPUB and Kindle. Book excerpt: Division II: Aerodynamics, Volume 7: Wing Theory in Supersonic Flow examines the cases of isolated simple wings, wings with vertical plane tail, cruciform wings, and simple or cruciform wings fitted with a body. This book presents the method for the actual calculation of isolated wings or of more complex system. Organized into 12 chapters, this volume starts with an overview of the basic equations in the mechanics of inviscid fluids. This text then presents a unified theory that is established for angularly shaped wings in supersonic flow. Other chapters consider the method for calculating the characteristics of drag, lift, and moments for various shapes of the trailing edge line. This book discusses as well the wings of ordinary shapes, delta wings, yawed wings, polygonal wings, trapezoid wings, and arrow-head or swept-back wings. The final chapter deals with a delta wing with a central fusiform body. This book is a valuable resource for teachers, students, and specialists engaged in modern aerodynamics.
Download or read book Supersonic Aerodynamics of Delta Wings written by Richard M. Wood and published by . This book was released on 1988 with total page 112 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Minimum Drag Due to Lift for a Delta Wing with Sonic Leading Edges written by Torstein Strand and published by . This book was released on 1954 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book A Wing Concept for Supersonic Maneuvering written by William Henry Mason and published by . This book was released on 1983 with total page 88 pages. Available in PDF, EPUB and Kindle. Book excerpt:
