Effect of Horizontal-tail Location on Low-speed Static Longitudinal Stability and Damping in Pitch of a Model Having 45° Sweptback Wing and Tail Surfaces PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Effect of Horizontal-tail Location on Low-speed Static Longitudinal Stability and Damping in Pitch of a Model Having 45° Sweptback Wing and Tail Surfaces PDF full book. Access full book title Effect of Horizontal-tail Location on Low-speed Static Longitudinal Stability and Damping in Pitch of a Model Having 45° Sweptback Wing and Tail Surfaces by Jacob H. Lichtenstein. Download full books in PDF and EPUB format.
Author: Jacob H. Lichtenstein Publisher: ISBN: Category : Airplanes Languages : en Pages : 34
Book Description
Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.
Author: Jacob H. Lichtenstein Publisher: ISBN: Category : Airplanes Languages : en Pages : 34
Book Description
Wind-tunnel results are presented to show the effect of changes in horizontal-tail location on the low-speed static longitudinal stability and steady-state rotary damping in pitch for a complete model with wing and tail surfaces having the quarter-chord lines swept back 45 degrees.
Author: Rudolph W. Hensel Publisher: ISBN: Category : Mathematical analysis Languages : en Pages : 708
Book Description
Calculations of the ratios of the velocity increments at test bodies to those at the tunnel walls caused by the solid blocking of these bodies within the walls of a closed rectangular wind tunnel are presented. The boides treated include two-dimensional airfoils; small bodies of revolution; straight, untapered, finite-span wings of varying span; and swept, untapered, finite-span wings of varying span. It is shown that, after wake blocking effects have been removed , the present method furnishes semiempirical blocking corrections for most wind-tunnel models and their components. The test section proportions of the Southern California Cooperative Wind Tunnel at CIT (ratio of height to width equal to 1/square root of 2) are used in the calculations.
Author: Jacob H. Lichtenstein
Author: Jacob H. Lichtenstein
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: Clarence W. Matthews
Author: United States. National Advisory Committee for Aeronautics
Author: 
Author: 
Author: Rudolph W. Hensel