Author : W. F. Lindsey
Publisher :
Page : 524 pages
File Size : 25,74 MB
Release : 1947
Category : Aerodynamics, Supersonic
ISBN :
An investigation has been conducted at subsonic Mach numbers in the Langley rectangular high-speed tunnel on five supersonic airfoils and, for comparison, on two subsonic airfoils. Two-dimensional data were obtained by pressure measurements and schlieren photographs at angles of attack from 0 degrees to 4 degrees for Mach numbers between 0.30 and 0.90 for these 6-percent-thick symmetrical airfoils.
Author :
Publisher :
Page : 376 pages
File Size : 12,70 MB
Release : 1948
Category : Aeronautics
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 986 pages
File Size : 10,96 MB
Release : 1958
Category : Aeronautics
ISBN :
Author : Harry E. Murray
Publisher :
Page : 744 pages
File Size : 34,68 MB
Release : 1950
Category : Laplace transformation
ISBN :
The lateral motions of aircraft are obtained by means of the Laplace transform which gives solutions in terms of elementary functions for the free motions and the motions due to forcing step functions. The lateral stability of a specific airplane and certain of its free and forced motions are calculated.
Author : John R. Westfall
Publisher :
Page : 674 pages
File Size : 32,95 MB
Release : 1957
Category : Airplanes
ISBN :
This paper briefly summarizes the more important statistical data obtained by the NACA on the subject of ground loads. The information presented relates primarily to landing-impact and taxiing loads; however, some limited data are also presented on one phase of ground-handling loads, namely, braking friction. A number of experimental and theoretical papers dealing with various aspects of the subject are listed in the bibliography.
Author :
Publisher :
Page : 28 pages
File Size : 26,20 MB
Release : 1947
Category : Aerodynamics
ISBN :
Author : Eugene S. Love
Publisher :
Page : 702 pages
File Size : 13,7 MB
Release : 1955
Category : Aerodynamic load
ISBN :
Some recent contributions to the problem of shock-induced separation of the boundary layer are examined, and additional analytical and experimental results are presented. The probable ranges of pressure rises and flow deflections associated with separation are indicated. Consideration is given to the effects of Mach number, adverse pressure gradient, and Reynolds number for laminar boundary layers and to the effects of Mach number, Reynolds number, and ratio of sepcific heats for turbulent boundary layers.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 162 pages
File Size : 43,97 MB
Release : 1954
Category : Aeronautics
ISBN :
Author : Max C. Kurbjun
Publisher :
Page : 686 pages
File Size : 26,98 MB
Release : 1955
Category : Noise
ISBN :
Theoretical calculations of the sound-pressure levels by the method of NACA TN 2968 predict accurately, for the 10-foot propeller investigated, the location of and the maximum levels to be expected for the overall noise and the first two propeller harmonics. The calculations do not predict accurately the location of the maximum sound-pressure levels ad the maximum calculated levels are 10 and 13 decibels lower than the msximm messured levels for the third and fourth harmonics, respectively.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 388 pages
File Size : 37,85 MB
Release : 1959
Category : Aeronautics
ISBN :
