Sash Greenhouses. (open access)

Sash Greenhouses.

Describes sash greenhouses. Provides plans for constructing and heating greenhouses.
Date: July 1958
Creator: Beattie, James H. (James Herbert), b. 1882
Object Type: Book
System: The UNT Digital Library
Swine production. (open access)

Swine production.

A guide to hog-raising, including breeding, feeding, care of pigs, disease control, and selling.
Date: July 1958
Creator: Zeller, J. H. (John Henry), 1894-
Object Type: Book
System: The UNT Digital Library
Dodder and its control. (open access)

Dodder and its control.

Describes the parasite commonly known as dodder, which attacks alfalfa and other hay-like crops; provides methods of controlling and preventing dodder infestations.
Date: July 1958
Creator: Lee, William O., 1911- & Timmons, F. L. (Francis Leonard), 1905-
Object Type: Book
System: The UNT Digital Library
Interseeding Legumes in Corn. (open access)

Interseeding Legumes in Corn.

Explains the practice and procedures for interseeding legumes and grasses in wide-row corn.
Date: July 1958
Creator: Van Doren, C. A. (Cornelius Austin), 1905- & Hays, O. E.
Object Type: Book
System: The UNT Digital Library
A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds (open access)

A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds

Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date: July 21, 1958
Creator: Heath, Atwood R., Jr. & Igoe, Ann W.
Object Type: Report
System: The UNT Digital Library
Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile With Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51 (open access)

Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile With Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51

"A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected" (p. 1).
Date: July 14, 1958
Creator: Presnell, John G., Jr.
Object Type: Report
System: The UNT Digital Library
Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model (open access)

Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model

Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.
Date: July 14, 1958
Creator: Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr.
Object Type: Report
System: The UNT Digital Library
Boundary-Layer-Transition Measurements in Full-Scale Flight (open access)

Boundary-Layer-Transition Measurements in Full-Scale Flight

Report presenting tests of the extent of laminar flow that can be obtained with practical wing-surface conditions. Chemical sublimation was used for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight. A method of continuous monitoring using heat temperature resistance gauges was also used on one wing.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Object Type: Report
System: The UNT Digital Library
Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations (open access)

Preliminary Aerodynamic Data Pertinent to Manned Satellite Reentry Configurations

Report presenting some experimental data and calculations for a variety of aerodynamic shapes considered for use as manned reentry vehicles. Three types of vehicles were tested: non-lifting bodies, lifting bodies, and airplane-like vehicles. All of the configuration types were found to be suitable for use as manned reentry vehicles with certain fin and flap modifications for certain shapes.
Date: July 21, 1958
Creator: Penland, Jim A. & Armstrong, William O.
Object Type: Report
System: The UNT Digital Library
Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile (open access)

Experimental Investigation of Flutter and Divergence Characteristics of the Rocket-Motor Fin of the ASROC Missile

Report presenting testing of models of rocket-motor fins of the ASROC missile for flutter and divergence in the supersonic flutter tunnel for a range of Mach numbers. Results indicate that both divergence of the overhung leading edge and flutter occur within the sea-level operating conditions of the missile at Mach numbers above 1.0. Results regarding the flutter boundary, type of flutter encountered, possible solutions to flutter problems, and possible effects of nondestructive type of flutter are provided.
Date: July 31, 1958
Creator: Levey, Gilbert M. & Hanson, Perry W.
Object Type: Report
System: The UNT Digital Library
Icing Frequencies Experienced During Climb and Descent by Fighter-Interceptor Aircraft (open access)

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

"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 1-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" (p. 1).
Date: July 1958
Creator: Perkins, Porter J.
Object Type: Report
System: The UNT Digital Library
Evaluation of Some Aerodynamic Controls for a Low Aspect Ratio Missile (open access)

Evaluation of Some Aerodynamic Controls for a Low Aspect Ratio Missile

"Results of a static stability controls investigation carried out with a very low-aspect-ratio delta-winged missile are presented. Control effectiveness comparisons are made for tail, canard, and nose control configurations with respect to angle of attack, angle of bank, and Mach number. Trim capabilities of the various configurations are also presented" (p. 1).
Date: July 17, 1958
Creator: Winovich, Warren & Higdon, Nancy S.
Object Type: Report
System: The UNT Digital Library
Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines (open access)

Effect of Design Variables on Performance of Mach 4.0 Hydrogen Expansion Engines

Memorandum presenting performance calculations for hypothetical hydrogen expansion engines in which only a small part of the engine airflow passes through the heat exchanger. The flight path was representative of those for long-range, high-speed aircraft. Results regarding the off-design operation and engine performance are provided.
Date: July 22, 1958
Creator: Dugan, James F., Jr.
Object Type: Report
System: The UNT Digital Library
Performance of Five Short Multielement Turbojet Combustors for Hydrogen Fuel in Quarter-Annulus Duct (open access)

Performance of Five Short Multielement Turbojet Combustors for Hydrogen Fuel in Quarter-Annulus Duct

Report described five short multielement turbojet combustors for use with hydrogen fuel and their performance. Information about the combustion efficiency, temperature profiles, pressure loss, durability, and comparison with previous short combustors is included.
Date: July 22, 1958
Creator: Jones, Robert E. & Rayle, Warren D.
Object Type: Report
System: The UNT Digital Library
A Body Modification to Reduce Drag Due to Wedge Angle of Wing with Unswept Trailing Edge (open access)

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

From Summary: "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."
Date: July 1958
Creator: Pitts, William C. & Nielsen, Jack Norman
Object Type: Report
System: The UNT Digital Library
Performance of Multiple Jet-Exit Installations (open access)

Performance of Multiple Jet-Exit Installations

Memorandum presenting the results of recent exploratory investigations of the performance of clustered jet-exit installations at Mach numbers from 0.60 to 3.05. Data presented in this report were obtained with tunnel-wall-mounted models with cold-air-jet exhaust. Results regarding base pressures, effect of boattailing, effect of afterbody-nozzle geometry, and terminal fairings are provided.
Date: July 7, 1958
Creator: Swihart, John M. & Nelson, William J.
Object Type: Report
System: The UNT Digital Library
Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight (open access)

Hydrodynamic Characteristics of a Model of a Proposed Six-Engine Hull-Type Seaplane Designed for Supersonic Flight

Memorandum presenting an investigation of the hydrodynamic characteristics of a six-engine hull-type seaplane designed for supersonic flight. The configuration had four engines mounted on top of the wing in individual nacelles and two engines mounted on top of the aft section of the hull with their inlets located on top of the wing.
Date: July 14, 1958
Creator: Coffee, Claude W., Jr.
Object Type: Report
System: The UNT Digital Library
The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance (open access)

The Effect of Compressor-Inlet Water Injection on Engine and Afterburner Performance

"A turbojet engine incorporating a conventional-type afterburner was operated over a range of afterburner pressure levels from 1000 to 2000 pounds per square foot absolute and a range of engine-inlet water-air ratios from 0 to 0.08. At each pressure level and water-air ratio, the afterburner fuel flow was varied from lean blowout to maximum burner-outlet temperature" (p. 1).
Date: July 22, 1958
Creator: Sivo, Joseph N.; Wanhainen, John P. & Jones, William L.
Object Type: Report
System: The UNT Digital Library
An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering (open access)

An Investigation of the Effect of Target Temperature on Projectile Penetration and Cratering

Results regarding testing of steel projectiles fired into copper targets at velocities from 5,000 to 11,500 feet per second, which indicated that as target temperature is increased, the crater size also increases. Twenty-two caliber steel cylinders and steel spheres were used as projectiles.
Date: July 28, 1958
Creator: Kinard, William H. & Lambert, C. H., Jr.
Object Type: Report
System: The UNT Digital Library
Static Stability and Control of Hypersonic Gliders (open access)

Static Stability and Control of Hypersonic Gliders

Memorandum presenting a study of the static stability and control problems associated with several hypersonic boost gliders. Generally, it is possible to obtain the desired trim features. Results regarding the high-lift-drag-ratio type of gliders and low-lift-drag-ratio type of gliders are provided.
Date: July 7, 1958
Creator: Rainey, Robert W.
Object Type: Report
System: The UNT Digital Library
Boundary-Layer-Transition Measurements in Full-Scale Flight (open access)

Boundary-Layer-Transition Measurements in Full-Scale Flight

Chemical sublimation has been employed for boundary-layer-flow visualization on the wings of a supersonic fighter airplane in level flight at speeds near a Mach number of 2.0. The tests have shown that laminar flow can be obtained over extensive areas of the wing with practical wing-surface conditions. In addition to the flow visualization tests, a method of continuously monitoring the conditions of the boundary layer has been applied to flight testing, using heated temperature resistance gages installed in a Fiberglas "glove" installation on one wing. Tests were conducted at speeds from a Mach number of 1.2 to a Mach number of 2.0, at altitudes from 35,000 feet to 56,000 feet. Data obtained at all angles of attack, from near 0 deg to near 10 deg, have shown that the maximum transition Reynolds number on the upper surface of the wing varies from about 2.5 x 10(exp 6) at a Mach number of 1.2 to about 4 x 10(exp 6) at a Mach number of 2.0. On the lower surface, the maximum transition Reynolds number varies from about 2 x 10(exp 6) at a Mach number of 1.2 to about 8 x 10(exp 6) at a Mach number of 2.0.
Date: July 28, 1958
Creator: Banner, Richard D.; McTigue, John G. & Petty, Gilbert, Jr.
Object Type: Report
System: The UNT Digital Library
Heat-Transfer Measurements on a Concave Hemispherical Nose Shape With Unsteady-Flow Effects at Mach Numbers of 1.98 and 4.95 (open access)

Heat-Transfer Measurements on a Concave Hemispherical Nose Shape With Unsteady-Flow Effects at Mach Numbers of 1.98 and 4.95

Memorandum presenting heat-transfer rates and pressure fluctuations at Mach numbers of 1.98 and 4.95 measured at the stagnation point of a concave hemisphere for a range of Reynolds numbers based on free-stream conditions and model diameter. Results regarding heat-transfer characteristics, heat-transfer data, and schileren photographs and stagnation point pressure measurements are provided.
Date: July 17, 1958
Creator: Cooper, Morton; Beckwith, Ivan E.; Jones, Jim J. & Gallagher, James J.
Object Type: Report
System: The UNT Digital Library
Characteristics of the Langley 8-Foot Transonic Tunnel With Slotted Test Section (open access)

Characteristics of the Langley 8-Foot Transonic Tunnel With Slotted Test Section

"A large wind tunnel, approximately 8 feet in diameter, has been converted to transonic operation by means of slots in the boundary extending in the direction of flow. The usefulness of such a slotted wind tunnel, already known with respect to the reduction of the subsonic blockage interference and the production of continuously variable supersonic flows, has been augmented by devising a slot shape with which a supersonic test region with excellent flow quality could be produced. Experimental locations of detached shock waves ahead of axially symmetric bodies at low supersonic speeds in the slotted test section agreed satisfactorily with predictions obtained by use of existing approximate methods" (p. 1297).
Date: July 3, 1958
Creator: Wright, Ray H.; Ritchie, Virgil S. & Pearson, Albin O.
Object Type: Report
System: The UNT Digital Library
Measurements of free-space oscillating pressures near propellers at flight Mach numbers to 0.72 (open access)

Measurements of free-space oscillating pressures near propellers at flight Mach numbers to 0.72

"In the course of a short flight program initiated to check the theory of Garrick and Watkins (NACA rep. 1198), a series of measurements at three stations were made of the oscillating pressures near a tapered-blade plan-form propeller and rectangular-blade plan form propeller at flight Mach numbers up to 0.72. In contradiction to the results for the propeller studied in NACA rep. 1198, the oscillating pressures in the plane ahead of the propeller were found to be higher than those immediately behind the propeller. Factors such as variation in torque and thrust distribution, since the blades of the present investigation were operating above their design forward speed, may account for this contradiction" (p. 999).
Date: July 1, 1958
Creator: Kurbjun, Max C. & Vogeley, Arthur W.
Object Type: Report
System: The UNT Digital Library