Author : Artur Mager
Publisher :
Page : 47 pages
File Size : 33,51 MB
Release : 1951
Category : Aeronautics
ISBN :
A numerical evaluation of this solution carried out the data obtained in a curving nonrotating duct shows a fair quantitative agreement with the measured values.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 1200 pages
File Size : 46,23 MB
Release : 1954
Category : Aeronautics
ISBN :
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Author : Roberto Vaglio-Laurin
Publisher :
Page : 54 pages
File Size : 50,44 MB
Release : 1958
Category : Aerodynamics, Hypersonic
ISBN :
Author : Arthur W. Goldstein
Publisher :
Page : 236 pages
File Size : 35,61 MB
Release : 1952
Category : Aerodynamics, Supersonic
ISBN :
Author :
Publisher :
Page : 620 pages
File Size : 37,26 MB
Release : 1945
Category : Aeronautics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 534 pages
File Size : 48,47 MB
Release : 1953
Category : Aeronautics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 1462 pages
File Size : 40,90 MB
Release : 1951
Category : Aeronautics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 1274 pages
File Size : 40,46 MB
Release : 1958
Category : Aeronautics
ISBN :
Author : Stanley Faber
Publisher :
Page : 680 pages
File Size : 21,46 MB
Release : 1958
Category : Airplanes
ISBN :
In this study in which an airplane simulator with one degree of freedom (pitch) was used, results were determined for three conditions of airplane dynamics. For an undamped natural frequency of 1/2 cps with a damping ratio of 0.18 and for an undamped natural frequency of 1 cps with a damping ratio of 0.11, moderate longitudinal stick forces and displacements were desired.
Author : Maurice Tucker
Publisher :
Page : 686 pages
File Size : 32,36 MB
Release : 1951
Category : Aerodynamics, Supersonic
ISBN :
An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
