Reduction of Drag Due to Lift at Supersonic Speeds
Reduction of Drag Due to Lift at Supersonic Speeds

Author: Douglas Aircraft Company

Publisher:

Published: 1955

Total Pages: 124

ISBN-13:

DOWNLOAD EBOOK

$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.

A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios
A Supersonic Area Rule and an Application to the Design of a Wing-body Combination with High Lift-drag Ratios

Author: Richard T. Whitcomb

Publisher:

Published: 1960

Total Pages: 20

ISBN-13:

DOWNLOAD EBOOK

Summary: As an extension of the transonic area rule, a concept for interrelating the wave drags of wing-body combinations at moderate supersonic speeds with axial developments of cross-sectional area has been derived. The wave drag of a combination at a given supersonic speed is related to a number of developments of cross-sectional areas as intersected by Mach planes. On the basis of this concept and other design procedures, a structurally feasible, swept-wing--indented-body combination has been designed to have relatively high maximum lift-drag ratios over a range of transonic and moderate supersonic Mach numbers. The wing of the combination has been designed to have reduced drag associated with lift and, when used with an indented body, to have low zero-lift wave drag. Experimental results have been obtained for this configuration at Mach numbers from 0.80 to 2.01. Maximum lift-drag ratios of approximately 14 and 9 were measured at Mach numbers of 1.15 and 1.41, respectively.

Fluid Dynamics Research on Supersonic Aircraft
Fluid Dynamics Research on Supersonic Aircraft

Author: North Atlantic Treaty Organization. Research and Technology Organization

Publisher:

Published: 1998

Total Pages: 342

ISBN-13:

DOWNLOAD EBOOK

Contains the lecture notes prepared for a Special Course on Fluid Dynamics Research on Supersonic Aircraft organized by the RTO Applied Vehicle Technology Panel (AVT). The Course was held at the von Kármán Institute for Fluid Dynamics (VKI) Institute, Rhode-Saint-Genèse, Belgium 25-29 May 1998. The following topics were covered: History & Economics of Supersonic Transports, Supersonic Aerodynamics, Sonic Boom Theory and Minimization, Multi-Point Design Challenges, Vortex Plume Interactions, Propulsion System Design. Presentations on the major world wide supersonic transport programs were also included. The material assembled in this publication was prepared under the combined sponsorship of the RTO Applied Vehicle Technology Panel, the Consultant and Exchange Program of RTO, and the von Kármán Institute (VKI) for Fluid Dynamics.

Leading-edge Wedges to Reduce the Drag of Thick Wings at Supersonic Speeds and to Increase Lift at Low Speeds
Leading-edge Wedges to Reduce the Drag of Thick Wings at Supersonic Speeds and to Increase Lift at Low Speeds

Author: Richard M. Hartley

Publisher:

Published: 1965

Total Pages: 36

ISBN-13:

DOWNLOAD EBOOK

An unswept 12-percent-thick wing panel (NACA 0012 section) was tested with a wedge protruding from the blunt leading edge to determine if wing drag could be reduced and lift-to-drag ratio improved at a supersonic airspeed (Mach number 1.87). The wing and wedge were also tested at low subsonic airspeeds to determine if a slat effect existed which would increase maximum lift. At the supersonic airspeed, the wedge reduced the drag of the plain wing by as much as 29 percent at low angles of attack. At higher angles, this drag reduction vanished but the wedge still increased the maximum ratio of lift to drag by as much as 20 percent. At low speeds, a wedge slat increased maximum lift by as much as 54 percent. A small cambered airfoil slat (with a somewhat larger chord than the wedge) was able to increase maximum lift by 72 percent. (Author).

Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds
Aircraft Configurations Developing High Lift-drag Ratios at High Supersonic Speeds

Author: A. J. Eggers (Jr.)

Publisher:

Published: 1956

Total Pages: 42

ISBN-13:

DOWNLOAD EBOOK

Summary: The problem of designing an aircraft which will develop high lift-drag ratios in flight at high supersonic speeds is attacked using the elementary principle that the components of the aircraft should be individually and collectively arranged to impart the maximum downward and the minimum forward momentum to the surrounding air. This principle in conjunction with other practical considerations of hypersonic flight leads to the study of configurations for which the body is situated entirely below the wing; that is, flat-top wing-body combinations. Theory indicates that sensibly complete aircraft of this type can be designed to develop lift-drag ratios well in excess of 6.

Aerodynamics, Aeronautics, and Flight Mechanics
Aerodynamics, Aeronautics, and Flight Mechanics

Author: Barnes W. McCormick

Publisher: John Wiley & Sons

Published: 1994-09-28

Total Pages: 677

ISBN-13: 0471575062

DOWNLOAD EBOOK

A New Edition of the Most Effective Text/Reference in the Field! Aerodynamics, Aeronautics, and Flight Mechanics, Second Edition Barnes W. McCormick, Pennsylvania State University 57506-2 When the first edition of Aerodynamics, Aeronautics, and Flight Mechanics was published, it quickly became one of the most important teaching and reference tools in the field. Not only did generations of students learn from it, they continue to use it on the job-the first edition remains one of the most well-thumbed guides you'll find in an airplane company. Now this classic text/reference is available in a bold new edition. All new material and the interweaving of the computer throughout make the Second Edition even more practical and current than before! A New Edition as Complete and Applied as the First Both analytical and applied in nature, Aerodynamics, Aeronautics, and Flight Mechanics presents all necessary derivations to understand basic principles and then applies this material to specific examples. You'll find complete coverage of the full range of topics, from aerodynamics to propulsion to performance to stability and control. Plus, the new Second Edition boasts the same careful integration of concepts that was an acclaimed feature of the previous edition. For example, Chapters 9, 10, and 11 give a fully integrated presentation of static, dynamic, and automatic stability and control. These three chapters form the basis of a complete course on stability and control. New Features You'll Find in the Second Edition * A new chapter on helicopter and V/STOL aircraft- introduces a phase of aerodynamics not covered in most current texts * Even more material than the previous edition, including coverage of stealth airplanes and delta wings * Extensive use of the computer throughout- each chapter now contains several computer exercises * A computer disk with programs written by the author is available