Author : Raymond E. Mineck
Publisher :
Page : 88 pages
File Size : 21,46 MB
Release : 1993
Category :
ISBN :
Author : William I. Scallion
Publisher :
Page : 16 pages
File Size : 42,15 MB
Release : 1959
Category : Aerodynamics
ISBN :
Author : Sanger M. Burk
Publisher :
Page : 44 pages
File Size : 13,91 MB
Release : 1970
Category : Pilot ejection seats
ISBN :
A wind-tunnel investigation has been conducted in the Langley full-scale tunnel to determine the static longitudinal and l a t e r a l characteristics of a model of an ejection seat equipped with a rigid-wing recovery system. Several wing and vertical-tail arrangements were tested as well as various configurations of the ejection seat alone, ranging from unfaired to completely faired s e a t s .
Author : Kenneth W. Mort
Publisher :
Page : 18 pages
File Size : 44,2 MB
Release : 1966
Category : Space vehicles
ISBN :
Author : Kenneth W. Mort
Publisher :
Page : 70 pages
File Size : 35,60 MB
Release : 1970
Category : Aerodynamics
ISBN :
Author : Thomas C. Kelly
Publisher :
Page : 86 pages
File Size : 10,26 MB
Release : 1957
Category : Aerodynamic load
ISBN :
Pressure data have been obtained in the Langley 8-foot transonic tunnel at Mach numbers from 0.80 to 1.115 and angles of attack from 0 to 20 degrees for wing-body configurations employing a thin trapezoidal wing in combination with basic and indented bodies. The wing had 26.6 degrees sweepback of the quarter-chord line, an aspect ratio of 2.61, a taper ratio of 0.211, and 2-percent-thick symmetrical circular-arc airfoil sections parallel to the plane of symmetry. Results are also presented for the basic body alone. Reynolds numbers for the tests were on the order of 2,600,000, based on the wing mean aerodynamic chord.
Author : Kenneth W. Mort
Publisher :
Page : 36 pages
File Size : 42,30 MB
Release : 1969
Category : Aerodynamics
ISBN :
Author : J. C. Donaldson
Publisher :
Page : 212 pages
File Size : 44,4 MB
Release : 1973
Category : Aerodynamic load
ISBN :
Exploratory static-stability tests were made on models of the MK-84 weapon and a modular weapon configuration during simulated weapon separation from the wing of the F-4C Tactical Fighter Aircraft at freestream Mach numbers 1.76, 2.0, and 2.5. Data were obtained with the parent aircraft at zero angle of attack and the weapon at the carriage incidence angle of -1 deg. Supplementary data were obtained for weapon angles of attack of + or - deg. Unit Reynolds number ranged from 4.6 million per ft at M free stream mach number = 1.76 to 6.2 million per ft at M free stream mach number = 2.5. Selected results are presented which show the effects on the weapon aerodynamic loads of free-stream Mach number, weapon angle of attack, weapon axial position, and the presence of other stores. Representative shadowgraph and schlieren photographs of the interference flow field are also presented. (Author).
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 86 pages
File Size : 18,66 MB
Release : 2018-07-17
Category :
ISBN : 9781722870737
Three planar, untwisted wings with the same elliptical chord distribution but with different curvatures of the quarter-chord line were tested in the Langley 8-Foot Transonic Pressure Tunnel (8-ft TPT) and the Langley 7- by 10-Foot High-Speed Tunnel (7 x 10 HST). A fourth wing with a rectangular planform and the same projected area and span was also tested. Force and moment measurements from the 8-ft TPT tests are presented for Mach numbers from 0.3 to 0.5 and angles of attack from -4 degrees to 7 degrees. Sketches of the oil-flow patterns on the upper surfaces of the wings and some force and moment measurements from the 7 x 10 HST tests are presented at a Mach number of 0.5. Increasing the curvature of the quarter-chord line makes the angle of zero lift more negative but has little effect on the drag coefficient at zero lift. The changes in lift-curve slope and in the Oswald efficiency factor with the change in curvature of the quarter-chord line (wingtip location) indicate that the elliptical wing with the unswept quarter-chord line has the lowest lifting efficiency and the elliptical wing with the unswept trailing edge has the highest lifting efficiency; the crescent-shaped planform wing has an efficiency in between. Mineck, Raymond E. and Vijgen, Paul M. H. W. Langley Research Center...
Author : James W. Wiggins
Publisher :
Page : 32 pages
File Size : 36,1 MB
Release : 1954
Category : Aerodynamic load
ISBN :
