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Results 15251 - 15274 of 18,906
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Aerodynamic Research on Fuselages with Rectangular Cross Section

Aerodynamic Research on Fuselages with Rectangular Cross Section

Date: July 1, 1958
Creator: Maruhn, K.
Description: The influence of the deflected flow caused by the fuselage (especially by unsymmetrical attitudes) on the lift and the rolling moment due to sideslip has been discussed for infinitely long fuselages with circular and elliptical cross section. The aim of this work is to add rectangular cross sections and, primarily, to give a principle by which one can get practically usable contours through simple conformal mapping. In a few examples, the velocity field in the wing region and the induced flow produced are calculated and are compared with corresponding results from elliptical and strictly rectangular cross sections.
Contributing Partner: UNT Libraries Government Documents Department
Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Altitude Performance of the Afterburner on the Iroquois Turbojet Engine. Coord. No. AF-P-6

Date: July 1, 1958
Creator: Groesbeck, Donald E. & Peters, Daniel J.
Description: The performance and operational characteristics of two afterburner configurations for the Iroquois turbojet engine were evaluated in an altitude test chamber over a range of afterburner equivalence ratios at afterburner-inlet pressures from 733 to 3186 pounds per square foot absolute. These conditions correspond to an altitude range from 38,700 to 66,800 feet at a flight Mach number of 1.5. The only difference between the two afterburner configurations was in the pattern of afterburner fuel injection. At an afterburner-inlet pressure of approximately 3100 pounds per square foot absolute, corresponding to an altitude of 38,700 feet and a_ flight Mach number of 1.5, the combustion efficiency of both configurations reached peak values of 0.80 to 0.85 at equivalence ratios of 0.35 to 0.40. However, further reduction in the afterburner-inlet pressure severely affected combustion efficiency. For example, at an afterburner inlet pressure level of 700 to 1000 pounds per square foot absolute, the efficiency for both configurations was 0.20 to 0.40.
Contributing Partner: UNT Libraries Government Documents Department
A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge

A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge

Date: July 1, 1958
Creator: Pitts, William C. & Nielsen, Jack Norman
Description: Ward's slender-body-theory formula for zero-lift drag contains three integrals plus a base-drag term. Two of these integral terms depend only upon the cross-sectional area distribution of the body. The third integral term depends only upon the body shape and axial slopes at the base of the body. This term is neglected in the transonic area rule because in many cases it is zero; however, there are also many cases in which it is not zero. This paper examines the term for the possibility of drag reduction for a particular case. The model considered consists of a body of revolution in combination with any wing that has an unswept trailing edge and a constant trailing-edge angle along its span. It is found that (neglecting any change in base drag) a drag reduction is obtainable which, for the case considered, is an additional 12 percent of that obtained with the area-rule modification. The probable effect of viscosity on this theoretical result is discussed.
Contributing Partner: UNT Libraries Government Documents Department
Compressive strength and creep of 17-7 PH stainless-steel plates at elevated temperatures

Compressive strength and creep of 17-7 PH stainless-steel plates at elevated temperatures

Date: July 1, 1958
Creator: Stein, Bland A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Dynamic stability of vehicles traversing ascending or descending paths through the atmosphere

Dynamic stability of vehicles traversing ascending or descending paths through the atmosphere

Date: July 1, 1958
Creator: Tobak, Murray & Allen, H Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effect of favorable pressure gradients on transition for several bodies of revolution at Mach 3.12

Effect of favorable pressure gradients on transition for several bodies of revolution at Mach 3.12

Date: July 1, 1958
Creator: Jack, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of boundary-layer displacement and leading-edge bluntness on pressure distribution, skin friction, and heat transfer of bodies at hypersonic speeds

Effects of boundary-layer displacement and leading-edge bluntness on pressure distribution, skin friction, and heat transfer of bodies at hypersonic speeds

Date: July 1, 1958
Creator: Bertram, Mitchel H & Henderson, Arthur, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of fabrication-type roughness on turbulent skin friction at supersonic speeds

Effects of fabrication-type roughness on turbulent skin friction at supersonic speeds

Date: July 1, 1958
Creator: Czarnecki, K R; Sevier, John R , Jr & Carmel, Melvin M
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Effects of fixing transition on the transonic aerodynamic characteristics of a wing-body configuration at Reynolds numbers from 2.4 to 12 million

Date: July 1, 1958
Creator: Hunton, Lynn W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Effects of nose shape and spray control strips on emergence and planing spray of hydro-ski models

Effects of nose shape and spray control strips on emergence and planing spray of hydro-ski models

Date: July 1, 1958
Creator: Mcgehee, John R
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An estimate of the fluctuating surface pressures encountered in the reentry of a ballistic missile

An estimate of the fluctuating surface pressures encountered in the reentry of a ballistic missile

Date: July 1, 1958
Creator: Callaghan, Edmund E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An evaluation of the effects of flexibility on wing strains in rough air for a large swept-wing airplane by means of experimentally determined frequency-response functions with an assessment of random-process techniques employed

An evaluation of the effects of flexibility on wing strains in rough air for a large swept-wing airplane by means of experimentally determined frequency-response functions with an assessment of random-process techniques employed

Date: July 1, 1958
Creator: Coleman, Thomas L; Press, Harry & Meadows, May T
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flight investigation of the acceptability of a small side-located controller used with an irreversible hydraulic control system

Flight investigation of the acceptability of a small side-located controller used with an irreversible hydraulic control system

Date: July 1, 1958
Creator: Kuehnel, Helmut A & Sommer, Robert W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Flow induced by a rotor in power-on vertical descent

Flow induced by a rotor in power-on vertical descent

Date: July 1, 1958
Creator: Castles, Walter, Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Full-scale wind-tunnel tests of a 35 degree sweptback-wing airplane with blowing from the shroud ahead of the trailing-edge flaps

Full-scale wind-tunnel tests of a 35 degree sweptback-wing airplane with blowing from the shroud ahead of the trailing-edge flaps

Date: July 1, 1958
Creator: Tolhurst, William H , Jr
Description: None
Contributing Partner: UNT Libraries Government Documents Department
General instability of stiffened cylinders

General instability of stiffened cylinders

Date: July 1, 1958
Creator: Becker, Herbert
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Geology of the Mississippi River Deltaic Plain, Southeastern Louisiana: Volume 1

Geology of the Mississippi River Deltaic Plain, Southeastern Louisiana: Volume 1

Date: July 1958
Creator: Waterways Experiment Station (U.S.)
Description: "The purpose of this report is to consolidate data gathered by the Corps of Engineers in various geologic investigations, and to augment this material with pertinent information garnered from the extensive investigations and studies [of the Mississippi River deltaic plain and its associated offshore area]" (p. 1). The report focuses primarily on those materials that are most important from an engineering standpoint.
Contributing Partner: UNT Libraries Government Documents Department
Handbook of structural stability part VI : strength of stiffened curved plates and shells

Handbook of structural stability part VI : strength of stiffened curved plates and shells

Date: July 1, 1958
Creator: Becker, Herbert
Description: A comprehensive review of failure of stiffened curved plates and shells is presented. Panel instability in stiffened curved plates and general instability of stiffened cylinders are discussed. The loadings considered for the plates are axial, shear, and the combination of the two. For the cylinders, bending, external pressure, torsion, transverse shear, and combinations of these loads are considered. When possible, test data and theory were correlated. General instability in stiffened cylinders was investigated. For bending and torsion loads, test data and theory were correlated. For external pressure several existing theories were compared. As a result of this investigation a unified theoretical approach to analysis of general instability in stiffened cylinders was developed. (author).
Contributing Partner: UNT Libraries Government Documents Department
Heat-transfer and pressure measurements on flat-faced cylinders at a Mach number of 2

Heat-transfer and pressure measurements on flat-faced cylinders at a Mach number of 2

Date: July 1, 1958
Creator: Stoney, William E , Jr & Markley, J Thomas
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Icing Frequencies Experienced During Climb and Descent by Fighter-Interceptor Aircraft

Icing Frequencies Experienced During Climb and Descent by Fighter-Interceptor Aircraft

Date: July 1, 1958
Creator: Perkins, Porter J.
Description: Data and analyses are presented on the relative frequencies of occurrence and severity of icing cloud layers encountered by jet aircraft in the climb and descent phases of flights to high altitudes. Fighter-interceptor aircraft operated by the Air Defense Command (USAF) at bases in the Duluth and Seattle areas collected the data with icing meters installed for a l-year period. The project was part of an extensive program conducted by the NACA to collect Icing cloud data for evaluating the icing problem relevant to routine operations. The average frequency of occurrence of icing was found to be about 5 percent of the number of climbs and descents during 1 year of operations The icing encounters were predominantly in the low and middle cloud layers, decreasing above 15,000 feet to practically none above 25,000 feet. The greatest thickness of ice that would accumulate on any aircraft component (as indicated by the accretion on a small object) was measured with the icing meters. The ice thicknesses on a small sensing probe averaged less than 1/32 inch and did not exceed 1/2 inch. Such accumulations are relatively small when compared with those that can form during horizontal flight in icing clouds. The light ...
Contributing Partner: UNT Libraries Government Documents Department
Idealized wings and wing-bodies at a Mach number of 3

Idealized wings and wing-bodies at a Mach number of 3

Date: July 1, 1958
Creator: Katzen, Elliott D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Influence of heat treatment on microstructure and high-temperature properties of nickel-base precipitation-hardening alloy

Influence of heat treatment on microstructure and high-temperature properties of nickel-base precipitation-hardening alloy

Date: July 1, 1958
Creator: Decker, R F; Rowe, John P; Bigelow, W C & Freeman, J W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Internal characteristics and performance of an aerodynamically controlled, variable-discharge convergent nozzle

Internal characteristics and performance of an aerodynamically controlled, variable-discharge convergent nozzle

Date: July 1, 1958
Creator: Mcardle, Jack G
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Local instability of the elements of a truss-core sandwich plate

Local instability of the elements of a truss-core sandwich plate

Date: July 1, 1958
Creator: Anderson, Melvin S
Description: The charts presented give the compressive buckling coefficients for a single-truss-core and a double-truss-core sandwich plate. These charts cover a wide range of sandwich proportions and may be used for sandwiches with unequal faces. They apply to inplane compressive loads acting parallel or perpendicular to the core direction or for various combinations of these loads. (author).
Contributing Partner: UNT Libraries Government Documents Department