NASA Langley Scientific and Technical Information Output-2001
Author :
Publisher :
Page : 166 pages
File Size : 29,8 MB
Release : 2002
Category :
ISBN :
Census of England and Wales, 1871
Author : Great Britain. Census Office
Publisher :
Page : 248 pages
File Size : 35,95 MB
Release : 1872
Category : Great Britain
ISBN :
Book Description
Administration Of The Poor Laws
Author : John Rickmann
Publisher :
Page : 48 pages
File Size : 39,31 MB
Release : 1832
Category :
ISBN :
Book Description
Simulator Study of Stall/post-stall Characteristics of a Fighter Airplane with Relaxed Longitudinal Static Stability
Author :
Publisher :
Page : 236 pages
File Size : 49,3 MB
Release : 1979
Category :
ISBN :
Book Description
A Parametric Study of the Aerodynamic Characteristics of Nose-cylinder-flare Bodies at a Mach Number of 6.0
Author : George C. Ashby
Publisher :
Page : 82 pages
File Size : 14,23 MB
Release : 1965
Category : Aerodynamics, Hypersonic
ISBN :
Book Description
Summary of Flight-test Results of the VZ-2 Tilt-wing Aircraft
Author : Robert J. Pegg
Publisher :
Page : 48 pages
File Size : 16,37 MB
Release : 1962
Category : Aerodynamics
ISBN :
Book Description
Buckling of a Pressurized Toroidal Ring Under Uniform External Loading
Author : George E. Weeks
Publisher :
Page : 28 pages
File Size : 12,49 MB
Release : 1967
Category : Buckling (Mechanics)
ISBN :
Book Description
Investigation of Engine-exhaust-airframe Interference on a Cruise Vehicle at Mach 6
Author : James M. Cubbage
Publisher :
Page : 76 pages
File Size : 43,82 MB
Release : 1971
Category : Aircraft exhaust emissions
ISBN :
Book Description
Results from an investigation of the effects of underexpanded engine exhaust flow on the aerodynamic performance and stability of a cruise airplane at Mach 6 are presented. The influence of wing reflex angle and nozzle geometry on exhaust flow interference effects was investigated on a flat-plate model. The experiments were conducted at a free-stream Reynolds number of 17.05 X 10 (to the 6 power) based on the length of the airplane model over a model angle-of-attack range of 0(degrees) to 10(degrees) and at nozzle static-pressure ratios from 1 to approximately 4.
Analysis of Partly Wrinkled Membranes
Author : Manuel Stein
Publisher :
Page : 36 pages
File Size : 31,35 MB
Release : 1961
Category : Mathematical analysis
ISBN :
Book Description
A Theory for Inflated Thin-wall Cylindrical Beams
Author : W. B. Fichter
Publisher :
Page : 28 pages
File Size : 47,22 MB
Release : 1966
Category : Bending
ISBN :
