Minimal Drag for Wings with Prescribed Lift, Roll Moment and Yaw Moment
Minimal Drag for Wings with Prescribed Lift, Roll Moment and Yaw Moment

Author: Karl L. E. Nickel

Publisher:

Published: 1983

Total Pages: 43

ISBN-13:

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Let L, R, Y be arbitrary real constants. A wing with fixed span which produces lift L, roll moment R, yaw moment Y and which has minimal induced drag D is wanted. This problem arises in airplane engineering. It is solved by means of Prandtl's lifting line theory combined with computation. (Author).

The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment
The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment

Author: Robert T. Jones

Publisher:

Published: 1950

Total Pages: 708

ISBN-13:

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The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. Expressions for the spanwise load distribution and the minimum drag in terms of the lateral position of the load centroid are given. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span over that for an elliptic loading having the same total lift and bending moment.

The Aerodynamic Design of Wings with Cambered Span Having Minimum Induced Drag
The Aerodynamic Design of Wings with Cambered Span Having Minimum Induced Drag

Author: Clarence D. Cone (Jr.)

Publisher:

Published: 1963

Total Pages: 36

ISBN-13:

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"The basic aerodynamic relations needed for the design of wings with cambered span having a minimum induced drag at specified flight conditions are developed for wings of arbitrary spanwise camber. Procedures are also developed for determining the physical wing form required to obtain the maximum value of lift-drag ratio at cruise, when the wing spanwise camber-line and section profiles are specified, by optimizing the wing chord and twist distributions with respect to both profile and induced drags. The application of the design procedure is illustrated by determining the physical wing form for a circular-arc spanwise camber line. The efficiency of this cambered wing is compared with that of an equal-span, flat wing of elliptical planform which satisfies the same set of fright operating conditions as does the cambered wing. The wing pitching- moment equations for optimally loaded cambered-span wings at design flight conditions are also developed for use in trim analyses on complete aircraft designs."--Page 1.

Method for Calculating the Rolling and Yawing Moments Due to Rolling for Unswept Wings with Or Without Flaps Or Ailerons by Use of Nonlinear Section Lift Data
Method for Calculating the Rolling and Yawing Moments Due to Rolling for Unswept Wings with Or Without Flaps Or Ailerons by Use of Nonlinear Section Lift Data

Author: Albert P. Martina

Publisher:

Published: 1953

Total Pages: 52

ISBN-13:

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The methods of NACA Reports 865 and 1090 have been applied to the calculation of the rolling- and yawing-moment coefficients due to rolling for unswept wings with or without flaps or ailerons. The methods allow the use of nonlinear section lift data together with lifting-line theory. Two calculated examples are presented in simplified computing forms in order to illustrate the procedures involved.

Nonlinear Functional Analysis and its Applications
Nonlinear Functional Analysis and its Applications

Author: E. Zeidler

Publisher: Springer Science & Business Media

Published: 2013-12-01

Total Pages: 1007

ISBN-13: 1461245664

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The fourth of a five-volume exposition of the main principles of nonlinear functional analysis and its applications to the natural sciences, economics, and numerical analysis. The presentation is self-contained and accessible to the non-specialist, and topics covered include applications to mechanics, elasticity, plasticity, hydrodynamics, thermodynamics, statistical physics, and special and general relativity including cosmology. The book contains a detailed physical motivation of the relevant basic equations and a discussion of particular problems which have played a significant role in the development of physics and through which important mathematical and physical insight may be gained. It combines classical and modern ideas to build a bridge between the language and thoughts of physicists and mathematicians. Many exercises and a comprehensive bibliography complement the text.

Tailless Aircraft in Theory and Practice
Tailless Aircraft in Theory and Practice

Author: Karl Nickel

Publisher: Hodder Education

Published: 1994

Total Pages: 520

ISBN-13:

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Discusses the range of tailless designs, from hanggliders to the US 'Stealth Bomber', and includes a detailed look at particularly significant designs. The authors' own experience in this field allows them to explain and illustrate the topic in a way that appeal to the enthusiast and satisfies the professional aerodynamicist.