National Advisory Committee for Aeronautics (NACA) - 182 Matching Results

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Preliminary investigation of a conical spike inlet in combination with a vertical-wedge auxiliary inlet at Mach number 1.9

Description: Pressure-recovery characteristics of a nacelle-type-spike inlet in combination with a vertical-wedge auxiliary scoop are presented for a free-stream Mach number of 1.9 at zero angle of attack. The auxiliary scoop provided 17 percent additional air flow with a drop in critical pressure recovery from 0.86 to 0.81. However, in terms of inlet-engine matching, the pressure recovery of the undersized spike inlet operating at a specified corrected air flow increased with the scoop open, for example, f… more
Date: September 27, 1955
Creator: Beke, Andrew; Allen, John L. & Williams, Thomas
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of a New Type of Supersonic Inlet

Description: "A supersonic inlet with supersonic deceleration of the flow entirely outside of the inlet is considered. A particular arrangement with fixed geometry having a central body with a circular annular intake is analyzed, and it is shown theoretically that this arrangement gives high pressure recovery for a large range of Mach number and mass flow and therefore is practical for use on supersonic airplanes and missiles. For some Mach numbers the drag coefficient for this type of inlet is larger than … more
Date: November 27, 1946
Creator: Ferri, Antonio & Nucci, Louis M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of an annular turbojet combustor having a catalytic-coated liner

Description: From Summary: "The performance of an experimental annular turbojet combustor was investigated at a low-pressure operating condition with an uncoated liner, with an identical liner having a ceramic coating on the inner walls, and with this same liner having a catalytic coating added onto the ceramic coating. The combustion efficiency was approximately the same for all three liners, thus indicating no gain in performance through the use of the catalytic coating."
Date: January 27, 1954
Creator: Norgren, Carl T. & Childs, J. Howard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of heat transfer to water flowing in an electrically heated Inconel tube

Description: A heat-transfer investigation was conducted with water flowing in an electrically heated Inconel tube with an inside diameter of 0.204 inch and a length-diameter ratio of 50 for ranges of Reynolds number up to 100,000 and of entrance pressure up to 200 inches of mercury gage. Correlation of average heat-transfer coefficients was obtained by use of the familiar Nusselt relation, wherein the physical properties of water were evaluated at an average bulk temperature. For conditions in which no boi… more
Date: September 27, 1950
Creator: Kaufman, Samuel J. & Isely, Francis D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of plate-type molybdenum disilicide fuel elements for an air-cycle nuclear reactor

Description: From Summary: "Flat, plate-type elements, 3.5 by 0.5 by 0.070 inches in size and containing 10 percent elemental natural uranium, were produced by hot pressing. The elements were acid-treated to remove surface uranium and then coated with an alumina glaze. Such an element remained stable and did not lose detectable quantities of fission fragments in a 400-hour treatment at 1800 degrees F in a flux of 5 X 10 to the 11th power neutrons per square centimeter per second. Such elements are convenien… more
Date: March 27, 1953
Creator: Maxwell, W. A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of the Combustion of Pentaborane and Diborane in a Turbojet Combustor at Simulated Altitude Conditions

Description: Report presenting an investigation to determine the combustion characteristics of pentaborane and diborane in a turbojet combustor. Four different test conditions were explored, which varied in inlet total pressure, temperature, and simulated flight conditions. Results regarding the combustor itself and performance of diborane fuel at high altitude are provided.
Date: February 27, 1957
Creator: Gibbs, J. B.; Kaufman, W. B. & Branstetter, J. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Low-Speed Wind-Tunnel Investigation of Some Aspects of the Aerodynamic Problems Associated with Missiles Carried Externally in Positions Near Airplane Wings

Description: A low-speed wind-tunnel investigation has been made of some aspects of the aerodynamic problems associated with the use of air-to-air missiles when carried externally on aircraft. Measurements of the forces and moments on a missile model for a range of positions under the mid-semispan location of a 45deg sweptback wing indicated longitudinal and lateral forces with regard to both carriage and release of the missiles. Surveys of the characteristics of the flow field in the region likely to be tr… more
Date: December 27, 1954
Creator: Alford, William J., Jr.; Silvers, H. Norman & King, Thomas J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Measurements of Atmospheric Turbulence at High Altitude as Determined From Acceleration Measurements on Lockheed U-2 Airplane

Description: "An analysis of a sample of turbulence data obtained from VGH records taken on Lockheed U-2 airplanes during research flight up to 55,000 feet over England and Western Europe has indicated substantial reductions in the number and intensity of gusts with increasing altitude. These results on the variation of atmospheric turbulence over England and Western Europe were found to be in overall agreement with previous turbulence data obtained from airplane- and balloon-borne instruments over the Unit… more
Date: March 27, 1957
Creator: Coleman, Thomas L. & Funk, Jack
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Measurements of Static Longitudinal Stability and Trim for the XF-92A Delta-Wing Research Airplane in Subsonic and Transonic Flight

Description: Report presenting static-longitudinal stability and trim results using the XF-92A delta-wing research airplane during power-plant demonstration and US Air Force performance tests for Mach numbers up to 0.97 and altitudes from 11,000 to 40,000 feet.
Date: March 27, 1953
Creator: Sisk, Thomas R. & Mooney, John M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Performance Data on Westinghouse Electronic Power Regulator Operating on J34-WE-32 Turbojet Engine in Altitude Wind Tunnel

Description: "The behavior of the Westinghouse electronic power regulator operating on a J34-WE-32 turbojet engine was investigated in the NACA Lewis altitude wind tunnel at the request of the Bureau of Aeronautics, Department of the Navy. The object of the program was to determine the, steady-state stability and transient characteristics of the engine under control at various altitudes and ram pressure ratios, without afterburning. Recordings of the response of the following parameters to step changes in p… more
Date: October 27, 1950
Creator: Ketchum, James R.; Blivas, Darnold & Pack, George J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Results From Flight Measurements in Gradual-Turn Maneuvers of the Wing Loads and the Distribution of Load Among the Components of a Boeing B-47A Airplane

Description: Report presenting an analysis of some strain-gage measurements of the loads carried by the wing and horizontal tail of a Boeing B-47A airplane during gradual-turn maneuvers for a variety of altitudes and Mach numbers. Results regarding the wing-load center of pressure, component loads, component-force coefficients, and fraction of the wing-fuselage load carried by the wing are provided.
Date: June 27, 1955
Creator: Cooney, T. V.; Andrews, William H. & McGowan, William A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Presentation on Facility Problems in High-Temperature Structures Research

Description: "This presentation is intended to reflect the current general approach of the NACA to the problems of high-temperature structures research facilities. The facilities and problems discussed apply to flight in the Mach number range from 2 to about 20. It is emphasized that this field is one in which the thinking is rapidly changing and the facilities investigations discussed, particularly for the higher temperature range, are in the exploratory stage" (p. 1).
Date: March 27, 1956
Creator: Purser, Paul E. & Heldenfels, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Presentation on facility problems in high-temperature structures research

Description: Presentation regarding the current general approach of NACA to the problems of high-temperature structures research facilities. The field is rapidly changing and many investigations discussed are still in the exploratory stage. The main areas of importance are heating, loading, and structural model accommodation as well as having the proper research equipment and heat exchangers.
Date: March 27, 1956
Creator: Purser, Paul E. & Heldenfels, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Distribution Over a Rectangular Monoplane Wing Model Up to 90 Degree Angle of Attack

Description: "The pressure distribution tests described in this report, covering angles of attack up to 90 degrees, were made on a rectangular monoplane wing model in the atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory. These tests indicate that a rectangular wing, by reason of its large tip loads, is uneconomical aerodynamically and structurally, has pronounced lateral instability above maximum lift, and is not adaptable to accurate calculation based on the classical wing theory" (p… more
Date: October 27, 1927
Creator: Knight, Montgomery & Loeser, Oscar, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Measurements on an Afterbody Behind Various Blunt Nose Shapes at a Mach Number of 2

Description: Memorandum presenting an investigation of flow surrounding afterbodies behind blunt nose shapes at a Mach number of 2 in the 27- by 27-inch preflight jet. Pressure measurements were made on and around the afterbodies for each configuration.
Date: December 27, 1957
Creator: Speegle, Katherine C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The pressure-recovery and propeller-force characteristics of a propeller-spinner-cowling combination employing NACA 4-(5) (05)-037 six- and eight-blade dual-rotation propellers with an NACA 1 series D-type cowl

Description: Report presenting an investigation to determine the effect of both six- and eight-blade dual-rotation propellers on the internal-flow characteristics of an NACA 1-series D-type cowl and the effect of the cowl on the characteristics of the propellers.
Date: January 27, 1955
Creator: Sammonds, Robert I. & Reynolds, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Recovery, Drag, and Subcritical Stability Characteristics of Conical Supersonic Diffusers With Boundary-Layer Removal

Description: A study of two 20 degrees half-angle, low mass-flow ratio conical supersonic inlets with cone boundary-layer bleed was made on a 16-inch ram-jet engine in the Lewis 8- by 6-foot supersonic wind tunnel. A greater stable subcritical range of operation was obtained with the bleed inlets than with the corresponding inlet without boundary-layer bleed. The drag added by the bleed system was small.
Date: February 27, 1952
Creator: Obery, Leonard J.; Englert, Gerald W. & Nussdorfer, Theodore J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Pressure Recovery, Drag, and Subcritical Stability Characteristics of Three Conical Supersonic Diffusers at Stream Mach Numbers From 1.7 to 2.0

Description: A study of a 20 degree and a 25 degree half-angle high mass-flow ratio conical supersonic inlet was made on a 16-inch ram jet in the 8- by 6-foot supersonic tunnel. A greater range of stable subcritical operation was obtained with the low mass-flow ratio inlets; a greater range was obtained with the 25 degree than with the 20 degree half-angle low mass-flow ratio inlet. The high mass-flow ratio inlet had the least drag.
Date: February 27, 1952
Creator: Nussdorfer, Theodore J.; Obery, Leonard J. & Englert, Gerald W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Prospects for Laminar Flow on Hypersonic Airplanes

Description: The factors which affect the extent of laminar flow on airplanes for hypersonic flight are discussed on the basis of the available data. Factors considered include flight Reynolds number, surface roughness, angle of attack, angle of leading-edge sweepback, and aerodynamic interference. Test data are presented for one complete configuration.
Date: June 27, 1958
Creator: Seiff, Alvin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Reduction of Fuel-Vapor Loss by Omitting Some of the Fuel Constituents Normally Lost During Flight

Description: Report discussing an investigation to determine the effect of omitting some of the fuel constituents in AN-F-28 Amendment 2 fuel that are normally lost in flight on fuel-vapor loss. Removing the components was found to decrease the fuel-vapor loss and increase the critical altitudes.
Date: August 27, 1945
Creator: Stone, Charles S. & Kramer, Walter E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Reflection of a Weak Shock Wave From a Boundary Layer Along a Flat Plate 1: Interaction of Weak Shock Waves With Laminar and Turbulent Boundary Layers Analyzed by Momentum-Integral Method

Description: Note presenting an investigation of the phenomena encountered when a plane oblique shock wave is incident upon the boundary layer of a flat plate. The flow field was divided into a viscous layer near the wall and a supersonic potential outer flow. With the outer flow determined, boundary-layer growth and pressure distribution were computed and results for the laminar cases were obtained and provided.
Date: January 27, 1953
Creator: Ritter, Alfred & Kuo, Yung-Huai
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Resolution of Annealing Experiments for the Study of Nonequilibrium States

Description: The two techniques for conducting annealing experiments for the purpose of determining the distribution of atoms of a solid among non equilibrium states are considered. Related definitions for resolving power for annealing with steadily rising temperature and for annealing at a series of fixed temperatures are given. The necessary separation of activation energies for the resolution of two different non equilibrium states is found to be greater in the case of a steadily rising temperature, but … more
Date: September 27, 1951
Creator: Schwed, Philip
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Rough-Water Tests of Models of the Vosper and Plum Planing Boats

Description: Models of two types of high-speed surface craft were tested in Langley tank no. 1 to obtain rough-water data for an evaluation by the David Taylor .Model Basin of the relative merits of the designs. Time-history records were obtained of trim, rise, and normal acceleration at two points in the hulls for various speeds and two sizes of waves.
Date: April 27, 1950
Creator: Chambliss, Derrill B. & Blanchard, Ulysse J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Simplified procedures for estimating flap-control loads at supersonic speeds

Description: Report presenting an investigation to determine the possibility of using simplified procedures for the estimation of control loads at supersonic speeds. The results indicated that relatively simple procedures are possible for the estimation of loadings on flap-type controls at supersonic speeds for cases when no flow separation occurs ahead of the hinge line.
Date: May 27, 1955
Creator: Czarnecki, K. R. & Lord, Douglas R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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