Linearized Lifting-surface Theory for Swept-back Wings with Slender Plan Forms PDF Download
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Author: Harvard Lomax Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 48
Book Description
The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back wing of slender plan form are developed by means of linearized lifting-surface theory. The results are applicable for all free-stream Mach numbers. The term slender implies that the ratio of the reduced span to over-all length of the wing is small.
Author: Harvard Lomax Publisher: ISBN: Category : Aerodynamic load Languages : en Pages : 48
Book Description
The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back wing of slender plan form are developed by means of linearized lifting-surface theory. The results are applicable for all free-stream Mach numbers. The term slender implies that the ratio of the reduced span to over-all length of the wing is small.
Author: Paul J. Carpenter Publisher: ISBN: Category : Helicopters Languages : en Pages : 642
Book Description
The rotor system investigated is a servocontrol type with blades fastened rigidly at the hub and twisted outboard by auxiliary airfoils called flaps to obtain pitch control.
Author: Fred M. Reinhart Publisher: ISBN: Category : Aluminum alloys Languages : en Pages : 766
Book Description
Corrosion behaviro of spot-welded aluminum-alloy (alclad 24S-T3, 24S-T3, alclade XB75S-T6, XB75S-T6, and R-301-T6) panels of varying weld quality was determined. Tidewater and weather exposure tests were made and the results were evaluated largely in terms of distribution of corrosion products and effects on weld strength. Metallographic examinations of several of the alloys were also made to determine the extent and type of corrosion attack associated with various welding and exposure conditions.
Author: James C. Sivells Publisher: ISBN: Category : Ailerons Languages : en Pages : 722
Book Description
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.
Author: Allen F. Donovan Publisher: Princeton University Press ISBN: 1400879906 Category : Science Languages : en Pages : 863
Book Description
Volume VII of the High Speed Aerodynamics and Jet Propulsion series. It deals with applications to specific components of the complete aircraft. Sections of the volume include: aerodynamics of wings at high speed, aerodynamics of bodies at high speed, interaction problems, propellers at high speed, diffusers and nozzles, and nonsteady wing characteristics. Originally published in 1957. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Author: Harvard Lomax
Author: Harvard Lomax
Author: United States. National Advisory Committee for Aeronautics
Author: Paul J. Carpenter
Author: Fred M. Reinhart
Author: 
Author: James C. Sivells
Author: 
Author: Allen F. Donovan
Author: United States. National Advisory Committee for Aeronautics
Author: