UNT Libraries Government Documents Department - 36 Matching Results

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Aerodynamic heating of aircraft components

Description: From Introduction: "The purpose of this paper is to review new and significant data which will be of interest to designers in determining the heating of these components. A comparison with existing theory to indicate its adequacy in each case is also presented."
Date: February 14, 1956
Creator: Chauvin, Leo T.
Item Type: Refine your search to only Report
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Concluding Report on Free-Spinning and Recovery Characteristics of a 1/24-Scale Model of the Grumman F11F-1 Airplane, TED No. NACA AD 395

Description: "An investigation has been completed in the Langley 20-foot free-spinning tunnel on a 1/24-scale model of the Grumman F11F-1 airplane to determine its spin and recovery characteristics. An interim report, Research Memorandum SL55G20, was published earlier and the present report concludes the presentation of results of the investigation. Primarily, the present report presents results obtained with engine gyroscopic moments simulated on the model. Also, the current results were obtained with a re… more
Date: August 14, 1956
Creator: Bowman, James S., Jr.
Item Type: Refine your search to only Report
open access

Effect of boundary-layer control and inlet lip shape on the performance of a twin-scoop air-induction system at Mach numbers from 0 to 1.9

Description: Report presenting an experimental investigation to determine the effect of boundary-layer control and inlet lip shape on the performance of a side-inlet air-induction system for a fighter-type airplane. Two methods of boundary layer control and three inlet lip shapes were investigated at a range of Mach numbers and mass-flow ratios. Results regarding net propulsive thrust are also provided.
Date: February 14, 1956
Creator: Lazzeroni, Frank A. & Pfyl, Frank A.
Item Type: Refine your search to only Report
open access

Effect of Wing Height and Dihedral on the Lateral Stability Characteristics at Low Lift of a 45 Deg Swept-Wing Airplane Configuration as Obtained from Time-Vector Analyses of Rocket-Propelled-Model Flights at Mach Numbers from 0.7 to 1.3

Description: From Summary: "Lateral-stability flight tests were made over the Mach number range from 0.7 to 1.3 of models of three airplane configurations having 45 degree sweptback wings. One model had a high wing; one, a low wing; and one, a high wing with cathedral. The models were otherwise identical. The lateral oscillations of the models resulting from intermittent yawing disturbances were interpreted in terms of full-scale airplane flying qualities and were further analyzed by the time-vector method … more
Date: September 14, 1956
Creator: Gillis, Clarence L. & Chapman, Rowe, Jr.
Item Type: Refine your search to only Report
open access

Electronics Counting Rooms for Nuclear Research

Description: Abstract: "This report describes six electronics areas at the Radiation Laboratory (Berkeley and Livermore) that are being successfully used with various particle acceleration for nuclear research. The electronics equipment, consisting of pulse amplifiers, scalers, coincidence circuits, pulse-height analyzers, automatic recording equipment, high-voltage supplies, etc., is arranged in such a manner that most experiments can be quickly set up, and a number of people can run experiments simultaneo… more
Date: June 14, 1956
Creator: Stripeika, Alexander J.
Item Type: Refine your search to only Report
open access

Experimental investigation of interference effects of lateral-support struts on afterbody pressures at Mach 1.9

Description: Report presenting testing of a series of single and double unswept, lateral-support struts at a Mach number of 1.9 on a cone-cylinder body at zero angle of attack. The struts consisted of a rectangular box section with identical wedge fairings fore and aft. Results regarding the shock-wave intersections and pressure distributions are provided.
Date: May 14, 1956
Creator: Klann, John L. & Huff, Ronald G.
Item Type: Refine your search to only Report
open access

Feasibility of In Vivo Plutonium Measurements

Description: It was shown that without further major development the detectors proposed for the Body Monitor can be expected to detect 0.02 microcurie of plutonium at the center of the chest cavity. This is the permissible body burden of insoluble forms of plutonium. The detection level can be decreased by decreasing the background counting rate. Decreases in the background can reasonably be expected; it should be possible to detect a small fraction of the permissible body burden. If it can be shown, as sug… more
Date: May 14, 1956
Creator: Roesch, W. C. & Baum, J. W.
Item Type: Refine your search to only Report
open access

A flight evaluation of a wing-shroud-blowing boundary-layer control system applied to the flaps of an F9F-4 airplane

Description: Report presenting an investigation of the F9F-4 airplane to evaluate a high-energy blowing boundary-layer-system in flight in order to improve the maximum lift characteristics of airplane wings. A high-energy blowing-boundary-layer control system was installed by the Grumman Aircraft Engineering Corporation. A series of test flights were made to measure the lift and drag variations with changes in angle of attack for the flap and gear both up and down and for blowing on and off.
Date: February 14, 1956
Creator: Rolls, L. Stewart & Innis, Robert C.
Item Type: Refine your search to only Report
open access

A Flight Investigation of the Handling Characteristics of a Fighter Airplane Controlled Through a Rate Type of Automatic Control System

Description: Report presenting an investigation of the handling qualities of a fighter airplane that is controlled by a pilot supplying signals to a rate type of automatic control system. The handling qualities were investigated in pull-ups, aileron rolls, aerobatics, rough-air flying, and precision tasks.
Date: September 14, 1956
Creator: Russell, Walter R.; Sjoberg, S. A. & Alford, William L.
Item Type: Refine your search to only Report
open access

Gas-to-blade heat-transfer coefficients and turbine heat-rejection rates for a range of one-spool cooled-turbine engine designs

Description: Report presenting gas-to-blade heat-transfer coefficients and turbine heat-rejection rates obtained for a wide range of one-spool turbojet engine designs believed to be representative of engines that will employ turbine cooling. The values of heat-transfer coefficient and heat-rejection rates are applicable to both liquid- and air-cooled turbines. Results regarding the heat-transfer coefficients and heat-rejection rates for turbojet engine designs, total heat-rejection rates for various turboje… more
Date: May 14, 1956
Creator: Slone, Henry O. & Esgar, Jack B.
Item Type: Refine your search to only Report
open access

Heat-Requirements for Ice Protection of a Cyclically Gas-Heated, 36 Degree Swept Airfoil with Partial-Span Leading-Edge Slat

Description: From Summary: "Heating requirements for satisfactory cyclic de-icing over a wide range of icing and operating conditions have been determined for a gas-heated, 36 degree swept airfoil of 6.9-foot chord with a partial-span leading-edge slat. Comparisons of heating requirements and effectiveness were made between the slatted and unslatted portions of the airfoil. Studies were also made comparing cyclic de-icing with continuous anti-icing, and cyclic de-icing systems with and without leading-edge … more
Date: May 14, 1956
Creator: Gray, Vernon H. & von Glahn, Uwe H.
Item Type: Refine your search to only Report
open access

Investigation of Afterburner Combustion Screech and Methods of Its Control at High Combustor Pressure Levels

Description: Memorandum presenting an experimental investigation of various methods for the control of afterburner combustion screech at afterburner-inlet total pressures from 4000 to 6400 pounds per square foot absolute. Generally, the range of afterburner fuel-air ratios in which screech occurred and the intensity of screech did not vary appreciably in the range of pressures covered.
Date: May 14, 1956
Creator: Trout, Arthur M.; Koffel, William K. & Smolak, George R.
Item Type: Refine your search to only Report
open access

Method for calculating the aerodynamic loading on an oscillating finite wing in subsonic and sonic flow

Description: A method is presented for calculating the loading on a finite wing oscillating in subsonic or sonic flow. The method is applicable to any plan form and may be used for determining the loading on deformed wings. The procedure is approximate and requires numerical integration over the wing surface.
Date: March 14, 1956
Creator: Runyan, Harry L. & Woolston, Donald S.
Item Type: Refine your search to only Report
open access

Neutron Irradiation of Sapphire (Al 2 O 3 )

Description: A centerless-ground, 0.25-in.-diam. by 0.75-in.-long sapphire single crystal exposed to an integrated thermal neutron flux of 2 x 10 19 nvt at a temperature of 350 deg C (660 deg F) did not change its dimensions appreciably simple beam, with slightly less force than was required to break a similar unirradiated rod. In a darkened room the irradiated sapphire begins to thermoluminesce noticeably at 280 deg C (535 deg F) and most of the amber or brown coloration produced by the pile exposure is re… more
Date: March 14, 1956
Creator: Wheeler, R.G.
Item Type: Refine your search to only Report
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