Technical Report Archive and Image Library (TRAIL) - 817 Matching Results

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Accelerations in transport-airplane crashes

Description: From Introduction: "A study of crash-impact survival in light airplanes is reported in references 1 and 2. A similar study for fighter airplanes is reported in reference 3. This report discusses crash-impact survival in transport airplanes."
Date: February 1958
Creator: Preston, G Merritt & Pesman, Gerard J
Partner: UNT Libraries Government Documents Department

Accidental Radiation Excursion at the Y-12 Plant, June 16, 1958: Final Report

Description: This report describes the circumstances leading to the accident, attempts to reconstruct the nuclear reactivity conditions, and reviews the dosimetric means and results which were used to help determine the exposure of affected employees.
Date: September 12, 1958
Creator: Patton, F. S.; Bailey, J. C.; Callihan, A. D.; Googin, J. M.; Jasny, G. R.; McAlduff, H. J. et al.
Partner: UNT Libraries Government Documents Department

Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Description: From Introduction: " Considerable analytical and experimental research has been done to find means of reducing the noise levels of the turbojet transports. Noise levels can be decreased by engine redesign to reduce the jet-exit velocity (ref. 1), proper flight-climb techniques (ref. 2), and the use of noise-suppression exhaust nozzles (refs. 3 to 5). The present report is concerned with the last method."
Date: April 1958
Creator: Ciepluch, Carl C; North, Warren J; Coles, Willard D & Antl, Robert J
Partner: UNT Libraries Government Documents Department

AEC Hot Cells and Related Facilities

Description: Foreward: The primary purpose of this report is to present as an accumulation of basic information on the hot cells constructed to date by the United States Atomic Energy Commission.
Date: May 1958
Creator: Fosdick, Ellery R.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at a Mach number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls

Description: Report discussing an investigation to determine the aerodynamic characteristics of hypersonic missile configurations with cruciform trailing-edge flaps with all-movable control surfaces. The all-movable controls were found to produce much larger values of trim lift and normal acceleration than the trailing-edge-flap configuration.
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at a Mach Number of 6.8 of two hypersonic missile configurations, one with low-aspect-ratio cruciform fins and trailing-edge flaps and one with a flared afterbody and all-movable controls

Description: Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree fins and trailing-edge flaps, and body with 10 degree flare and all-movable controls.
Date: August 4, 1958
Creator: Robinson, Ross B. & Bernot, Peter T.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at Mach numbers 2.36 and 2.87 of an airplane configuration having a cambered arrow wing with a 75 degree swept leading edge

Description: From Introduction: "The results obtained in the wind-tunnel tests at Mach numbers 2.36 and 2.87 for several configurations utilizing this wing, including results on the wing alone are presented."
Date: August 4, 1958
Creator: Hallissy, Joseph M., Jr. & Hasson, Dennis F.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics at Mach numbers from 2.5 to 3.5 of a canard bomber configuration designed for supersonic cruise flight

Description: Report presenting an investigation of a canard-type configuration designed for supersonic cruise flight in the Unitary Plan wind tunnel. Tests were conducted over a range of angles of attack and angles of sideslip. Results regarding the effect of forebody configuration, effects of Reynolds number and transition, effect of canard and elevon deflection, and effect of vertical surfaces are provided.
Date: September 10, 1958
Creator: Carmel, Melvin M.; Kelly, Thomas C. & Gregory, Donald T.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a 45 deg swept wing fighter airplane model and aerodynamic loads on adjacent stores and missiles at Mach numbers of 1.57, 1.87, 2.16, and 2.53

Description: Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale aircraft.
Date: June 24, 1958
Creator: Oehman, Waldo I. & Turner, Kenneth L.
Partner: UNT Libraries Government Documents Department

Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Description: From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."
Date: March 24, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department

Aerodynamic Effects Caused by Icing of an Unswept NACA 65A004 Airfoil

Description: From Summary: "The effects of ice formations on the section lift, drag, and pitching-moment coefficients of an unswept NACA 65A004 airfoil section of 6-foot chord were studied.. The magnitude of the aerodynamic penalties was primarily a function of the shape and size of the ice formation near the leading edge of the airfoil. The exact size and shape of the ice formations were determined photographically and found to be complex functions of the operating and icing conditions."
Date: February 1958
Creator: Gray, Vernon H. & von Glahn, Uwe H.
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on the problem."
Date: August 11, 1958
Creator: Stoney, William E , Jr
Partner: UNT Libraries Government Documents Department

Aerodynamic heating of blunt nose shapes at Mach numbers up to 14

Description: From Introduction: "The importance of blunt noses as a means of reducing the heat transfer to high velocity missiles has recently received much publicity. The question of just what blunt shape is best is still moot, and it is the purpose of this paper to present and examine some recent experimental results which may throw some light on this problem."
Date: August 11, 1958
Creator: Stoney, W. E., Jr.
Partner: UNT Libraries Government Documents Department

Aerodynamic load distribution on a 45 degree sweptback wing with leading-edge chord-extensions at transonic speeds, including effects of a spoiler-slot-deflector aileron

Description: Report discussing the aerodynamic loading characteristics of a 45 degree sweptback wing with leading-edge chord extensions, including the effects of a spoiler-slot-deflector aileron. The wing section loading, wing-panel loading, and chord-extension loading are described.
Date: February 20, 1958
Creator: Schmeer, James W.; Whitcomb, Charles F. & West, F. E., Jr
Partner: UNT Libraries Government Documents Department

Aerodynamic Research on Fuselages with Rectangular Cross Section

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.
Date: July 1958
Creator: Maruhn, K.
Partner: UNT Libraries Government Documents Department