Author : Edmund R. Jonash
Publisher :
Page : 58 pages
File Size : 22,62 MB
Release : 1946
Category : Airplanes
ISBN :
Knock-limited tests were conducted with F-4, F-3, and 17.6 small-scale engines and with a full-scale cylinder on blends containing the following purified hydrocarbons: 2,2,3,4-tetramethylpentane, 2,3,3,4-tetramethylpentane, 3,4,4-trimethyl-2-pentene, and 2,3,4-trimethyl-2-pentene.
Author : R. S. Genco
Publisher :
Page : 46 pages
File Size : 18,80 MB
Release : 1948
Category : Alkanes
ISBN :
At mild or moderate engine severity, 2,2,3,3-tetramethylpentane blend was highest in knock limit of the paraffins tested, but at severe conditions it was lowest; at severe (F-3) conditions, triptane blend was best.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 1370 pages
File Size : 23,33 MB
Release : 1949
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 836 pages
File Size : 19,41 MB
Release : 194?
Category : Aeronautics
ISBN :
Reproductions of reports, some declassified, of research done at Aircraft Engine Research Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 374 pages
File Size : 40,90 MB
Release : 1948
Category : Aeronautics
ISBN :
Author :
Publisher :
Page : 612 pages
File Size : 43,83 MB
Release : 1948
Category : Science
ISBN :
Author : United States. National Advisory Committee for Aeronautics
Publisher :
Page : 276 pages
File Size : 38,65 MB
Release :
Category : Airplanes
ISBN :
Author : Warren A. Tucker
Publisher :
Page : 738 pages
File Size : 27,52 MB
Release : 1948
Category : Aerodynamics, Supersonic
ISBN :
A theoretical analysis, based on the linearized equation for supersonic flow, of characteristics of triangular-tip control surfaces on thin triangular wings. By restriction to case for which Mach lines from wing apex lie behind the leading edge, a simplified treatment was possible; results of previous work on lift of triangular wings could be used to derive expressions for lift effectiveness, pitching moment, rolling-moment effectiveness, hinge moment due to control deflection, and hinge moment due to angle of attack. Comparisons were made with two-dimensional case.
Author :
Publisher :
Page : 388 pages
File Size : 38,25 MB
Release : 1948
Category : Aeronautics
ISBN :
Author : Lipman Bers
Publisher :
Page : 700 pages
File Size : 25,18 MB
Release : 1950
Category : Aerofoils
ISBN :
The method of computing velocity and pressure distributions along wing profiles under the assumption of the simplified density-speed relation, outlined in NACA Technical Note 1006, is extended to the case of a nonsymmetrical profile and a flow with circulation. The shape of the profile, the speed of the undisturbed flow, and a parameter determing the angle of attack may be prescribed. The problem is reduced to a nonlinear integral equation which can be solved numerical by an iteration method. A numerical example is given.
