Author: V. M. FalknerPublisher:
ISBN:
Category :
Languages : en
Pages : 36
Book Description
Low-speed Measurements of the Pressure Distribution at the Surface of a Swept-back Wing
Author: V. M. FalknerLow-speed Measurements of the Pressure Distribution at the Surface of a Swept-back Wing
Author: Victor Montague FalknerPublisher:
ISBN:
Category :
Languages : en
Pages : 30
Book Description
Low Speed Measurements of Pressure Distribution Near Tips of Swept Back Wings at Zero Lift
Author: J. WeberEffects of Twist and Camber on the Low-speed Longitudinal Stability Characteristics of a 45© Swept-back Wing of Aspect Ratio 8 at Reynolds Numbers from 1.5 X 106 to 4.8 X 10 as Determined by Pressure Distributions, Force Tests, and Calculations
Author: George L. PrattPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 110
Book Description
Pressure Distribution and Force and Moment Measurements of an 80 Deg Swept Wing with Twist and Camber at a Mach Number of 2.98
Author: Low-speed Wind-tunnel Investigation of a Triangular Sweptback Air Inlet in the Root of a 45 Degree Sweptback Wing
Author: Arvid L. KeithPublisher:
ISBN:
Category : Air ducts
Languages : en
Pages : 76
Book Description
A low-speed investigation has been conducted in the Langley two-dimensional low-turbulence tunnel to study a sweptback wing-root air-inlet configuration believed suitable for transonic-speed jet-powered airplanes. The test configurations consisted of a basic model with an NACA 64-008 wing with quarter-chord sweepback of 45 degrees mounted in the midwing position on a fuselage of fineness ratio 6.7, and an inlet model which had a triangular-shaped sweptback inlet installed in the wing root.
High Speed Wing Theory
Author: Doris CohenPublisher: Princeton University Press
ISBN: 1400874947
Category : Technology & Engineering
Languages : en
Pages : 251
Book Description
Part of the Princeton Aeronautical Paperback series designed to bring to students and research engineers outstanding portions of the twelve-volume High Speed Aerodynamics and Jet Propulsion series. These books have been prepared by direct reproduction of the text from the original series and no attempt has been made to provide introductory material or to eliminate cross reference to other portions of the original volumes. Originally published in 1960. 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.
Pressure Distribution Measurements of Swept-back Wings (Second Report on Swept-back Wings)
Author: H. LuetgebrunePublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 35
Book Description
Pressure distribution measurements were carried out on a straight wing, a strongly swept-back wing, and on a strongly swept forward wing. The experimental results were compared with Multhopp's theoretical lift distribution.
Low Speed Boundary Layer and Pressure Distribution Tests on a Family of Swept Back Wings
Author: Harvey O. NayPressure-distribution Measurements Over a 45 Degree Sweptback Wing at Transonic Speeds by the NACA Wing-flow Method
Author: Edward C. B. DanforthPublisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 42
Book Description
Measurements of pressure were made over the chord of a swept-wing model at four stations along (2, 6, 50, and 82 percent semispan) by the NACA wing-flow method. The model tested was an untapered 45 degree sweptback wing of aspect ratio 3.5 with 2-inch-chord NACA 65-210 airfoil sections normal to the leading edge. The tests were conducted at Mach numbers from about 0.7 to 1.1 at angles of attack from -1 to 4 degrees. The Reynolds number of the tests was nominally 600,000 based on the wing chord in the stream direction. The results are presented to show the chordwise pressure distributions and the spanwise distributions of section lift, drag, and pitching moment.