Technical Report Archive & Image Library (TRAIL) - 32,553 Matching Results

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Investigation of a 42.7 Degree Sweptback Wing Model to Determine the Effects of Trailing-Edge Thickness on the Aileron Hinge-Moment and Flutter Characteristics at Transonic Speeds

Description: Report presenting an investigation in the high-speed tunnel of a 42.7 degree sweptback wing model to determine the effects of aileron trailing-edge thickness on aileron hinge moments and one-degree-of-freedom aileron flutter. Results regarding the hinge-moment characteristics and free-floating characteristics are also provided.
Date: December 26, 1950
Creator: Thompson, Robert F.
Partner: UNT Libraries Government Documents Department
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Investigation of a Canard Missile Configuration (NACA RM-4) in the Langley 9-Inch Supersonic Tunnel at Mach Numbers of 1.62 and 1.93

Description: Report presenting an investigation in the supersonic tunnel using a canard missile configuration designated as NACA RM-4. Measurements of lift, drag, and pitching moment were made over a range of Mach numbers and angles of attack. The data is presented without analysis.
Date: June 24, 1954
Creator: Grigsby, Carl E.
Partner: UNT Libraries Government Documents Department
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Investigation of a Cermet Gas-Turbine-Blade Material of Titanium Carbide Infiltrated With Hastalloy C

Description: A cermet composition was investigated as a potential material for gas-turbine blades. Blades of HS-21 alloy were also operated in the engine simultaneously to provide a basis of comparison. The cermet blades survived as long as approximately 312-1/2 hours at about 1500 degrees F with an average midspan centrifugal stress of approximately 11,500 psi.
Date: January 24, 1955
Creator: Hoffman, Charles A.
Partner: UNT Libraries Government Documents Department
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Investigation of a Chromium Plus Aluminum Oxide Metal-Ceramic Body for Possible Gas Turbine Blade Application

Description: "A metal-ceramic composition containing approximately 80 percent chromium plus 20 percent aluminum oxide (Al(sub 2)O(sub 3)) by weight has been investigated for possible gas-turbine blade use. The results of modulus-of-rupture, thermal-shock, and blade-performance studies indicate that this material may have adequate thermal-shock resistance; however, the strength for the application appears marginal" (p. 1).
Date: November 16, 1953
Creator: Hoffman, Charles A.
Partner: UNT Libraries Government Documents Department
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Investigation of a continuous normal-shock positioning control for a translating-spike supersonic inlet in combination with J34 turbojet engine

Description: From Summary: "Use of a normal-shock positioning control was demonstrated at Mach numbers of 1.8 and 2.0 for a translating-spike supersonic inlet in combination with a J34 turbojet engine. Stable operation of the control was obtained which can be partly attributed to a nonlinearity in the servo valve in the null region."
Date: October 2, 1957
Creator: Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
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Investigation of a continuous normal-shock positioning control on the bypass of a supersonic inlet in combination with the J34 turbojet engine

Description: Report presenting an investigation of a normal-shock positioning control which utilized the bypass of a supersonic inlet to set the required air flow for a J34 turbojet engines to Mach number 2.0 in the supersonic tunnel. Continuous control without oscillations was obtained by use of the pressure signal from the small static probe. Calculated response time generally agreed with measured values.
Date: January 4, 1956
Creator: Wilcox, Fred A.
Partner: UNT Libraries Government Documents Department
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Investigation of a diffraction-grating interferometer for use in aerodynamic research

Description: Report presenting a description of a low-cost interferometer that is easy to adjust and has a large field of view. The instrument uses small diffraction gratings to produce and recombine separate beams of light. The usual two-parabolic-mirror schileren system can be converted inexpensivley to a diffraction-grating interferometer.
Date: November 1952
Creator: Sterrett, James R., Jr. & Erwin, John R.
Partner: UNT Libraries Government Documents Department
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Investigation of a Flow Deflector and an Auxiliary Scoop for Improving Off-Design Performance of Nose Inlets

Description: Memorandum presenting an investigation of flow deflectors which extend forward of an open-nose inlet for improving positive angle-of-attack performance and auxiliary scoops for use at off-design engine air-flow conditions at low angles of attack to determine their effect on net inlet performance. The results show that a deflector inlet and a basic open-nose inlet have about the same net performance at low angles of attack although the flow steadiness characteristics of the deflector inlet are t… more
Date: July 20, 1954
Creator: Anderson, Warren E. & Scherrer, Richard
Partner: UNT Libraries Government Documents Department
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An investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type cowing at Mach numbers up to 0.83

Description: Report presenting an investigation of a four-blade single-rotation propeller in combination with an NACA 1-series D-type spinner-cowling combination at Mach numbers up to 0.83. Characteristics of the propeller operating in the presence of the cowling are compared with the characteristics of the propeller with the spinner.
Date: April 13, 1953
Creator: Reynolds, Robert M.; Sammonds, Robert I. & Kenyon, George C.
Partner: UNT Libraries Government Documents Department
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Investigation of a full-scale, cascade-type thrust reverser

Description: A double set of turning vanes was carried inside the jet tailpipe. To produce reverse thrust, the tailpipe opens into two side sections and the turning vanes move outward to form a V-shaped cascade, which deflects the exhaust-gas flow. Forward and reverse net thrust were measured over a range of engine speeds with the airplane stationary. Taxi tests were made to determine the comparative stopping distances using wheel braking and reverse thrust separately, and a combination of both. The effect … more
Date: April 1957
Creator: Kohl, Robert C. & Algranti, Joseph S.
Partner: UNT Libraries Government Documents Department
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An Investigation of a Full-Scale Model of the Republic XF-91 Airplane in the Ames 40- By 80-Foot Wind Tunnel: Pressure Data

Description: Wind-tunnel tests of a full-scale model of the Republic XF-91 airplane were conducted to determine the distribution of pressure over the external wing fuel tank installation and over the vee tail and ventral fin. The data were obtained for a range of angles of attack and sideslip and elerudder deflection angles; the presentation is in tabular form.
Date: March 25, 1949
Creator: Hunton, Lynn W. & Dew, Joseph K.
Partner: UNT Libraries Government Documents Department
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Investigation of a Half-Conical Scoop Inlet Mounted at Five Alternate Circumferential Locations Around a Circular Fuselage: Pressure-Recovery Results at a Mach Number 2.01

Description: The effects of inlet circumferential position around the fuselage on the characteristics of a half-conical scoop inlet having a 24.6deg half-angle cone have been investigated in the langley 4- by 4-foot supersonic pressure tunnel. Pressure-recovery results have been obtained at a Mach number of 2.01 for a fixed boundary-layer-bleed height which was 60 percent of the boundary-layer thickness at an angle of attack of 0deg, and for cowling position parameters of 42.4deg and 38.0deg. inlet had a ca… more
Date: June 30, 1953
Creator: Hasel, Lowell E.; Lankford, John L. & Robins, A. W.
Partner: UNT Libraries Government Documents Department
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Investigation of a High-Flow Transonic-Compressor Inlet Stage Having a Hub-Tip Radius of 0.35

Description: Report discussing testing on a high-thrust turbojet engine capable of operation at high flight speeds. The report presents the overall performance and blade-element performance of the engine at a specified hub-tip radius ratio and specific weight flow of air.
Date: March 6, 1958
Creator: Felix, A. Richard
Partner: UNT Libraries Government Documents Department
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Investigation of a High-Performance Axial-Flow Compressor Transonic Inlet Rotor Designed for 37.5 Pounds Per Second Per Square Foot of Frontal Area: Aerodynamic Design and Overall Performance

Description: Report presenting an investigation of the design and tests of a transonic inlet rotor with emphasis placed on increasing the design specific weight flow while maintaining reasonably high pressure ratio and efficiency. Information regarding peak efficiency and how to best achieve it through design is provided.
Date: March 24, 1955
Creator: Savage, Melvyn & Felix, A. Richard
Partner: UNT Libraries Government Documents Department
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Investigation of a High-Performance Axial-Flow Compressor Transonic Inlet Rotor Designed for 37.5 Pounds Per Second Per Square Foot of Frontal Area: Detailed Blade-Element Performance

Description: Report presenting detailed blade-element-performance plots for a high-flow transonic inlet rotor. Information provided includes the effects of Mach number, blade loading, and angle of attack on element performance is provided.
Date: April 12, 1957
Creator: Felix, A. Richard & Savage, Melvyn
Partner: UNT Libraries Government Documents Department
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Investigation of a High-Performance Top Inlet to Mach Number of 2.0 and at Angles of Attack to 20 Degrees

Description: Memorandum presenting several top-inlet configurations tested on a body of revolution in the 8- by 6-foot supersonic wind tunnel at a range of angles of attack and free-stream Mach numbers. The effect on performance of the following variables were studied: throat bleed, ramp perforations, inlet approach surface, side fairings, fuselage fences, canopies, and a simulated 60 degree delta wing.
Date: March 20, 1957
Creator: Vargo, Donald J.; Parks, Philip N. & Davis, Owen H.
Partner: UNT Libraries Government Documents Department
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Investigation of a High-Pressure-Ratio Eight-Stage Axial-Flow Research Compressor With Two Transonic Inlet Stages 1: Aerodynamic Design

Description: Memorandum presenting an eight-stage high-pressure-ratio axial-flow compressor designed for use as a research unit in which the problems associated with design and off-design performance of transonic stages combined with highly loaded subsonic stages could be studied. The report discusses the design procedure and presents the experimentally determined overall performance of the compressor.
Date: December 4, 1953
Creator: Voit, Charles H.
Partner: UNT Libraries Government Documents Department
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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 2: preliminary analysis of over-all performance

Description: Report presenting an investigation of the overall performance of a 20-inch-tip-diameter, eight-stage axial-flow compressor conducted as the initial step in an investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The investigation was made over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed. Results regarding the overall performance, stage performance, comparison with design, and engine applicat… more
Date: December 1, 1953
Creator: Geye, Richard P.; Budinger, Ray E. & Voit, Charles H.
Partner: UNT Libraries Government Documents Department
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Investigation of a high-pressure ratio eight-stage axial-flow research compressor with two transonic inlet stages 3: individual stage performance characteristics

Description: Report presenting a determination of the individual stage performance for an eight-stage axial-flow compressor from circumferentially fixed radial rake measurements of total temperature and total pressure at the discharge of each stage. The performance of stages 1, 3, 4, 5, and 6 was anticipated in design and produced a peak pressure ratio considerably above the design pressure ratio while stages 2, 7, and 8 produced a peak pressure ratio approximately equal to design.
Date: November 1954
Creator: Voit, Charles H. & Geye, Richard P.
Partner: UNT Libraries Government Documents Department
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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 4: modification of aerodynamic design and prediction of performance

Description: Report presenting a modification of an eight-stage high-pressure-ratio axial-flow compressor in order to improve design-speed performance and to provide an instrument for continued study of the problems associated with design and off-design performance of transonic stages combined with highly loaded subsonic stages. Results regarding the design point characteristics and predicted changes in compressor performance are provided.
Date: June 1955
Creator: Geye, Richard P. & Voit, Charles H.
Partner: UNT Libraries Government Documents Department
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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 5: preliminary analysis of over-all performance of modified compressor

Description: Report presenting an investigation of the overall performance of a modified eight-stage axial-flow compressor as part of the investigation of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The maximum total pressure ratio obtained at design speed was 11.0 at an equivalent weight flow of 70.9 pounds per second with an adiabatic efficiency of 0.81. Results regarding modified compressor performance and comparison with predicted performance are … more
Date: May 23, 1955
Creator: Standahar, Raymond M. & Geye, Richard P.
Partner: UNT Libraries Government Documents Department
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Investigation of a high-pressure-ratio eight-stage axial-flow research compressor with two transonic inlet stages 6: over-all performance, rotating stall, and blade vibration at low and intermediate compressor speeds

Description: Report presenting an investigation to determine the overall performance of the modified eight-stage axial-flow compressor with new fourth-stage stator blades as part of a study of the problems encountered in a high-pressure-ratio axial-flow compressor with transonic inlet stages. The performance of the compressor was determined over a range of weight flows at equivalent speeds from 30 to 100 percent of design speed.
Date: November 1, 1955
Creator: Standahar, Raymond M.; Hanson, Morgan P. & Geye, Richard P.
Partner: UNT Libraries Government Documents Department
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Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 1: design of vortex turbine and performance with stator at design setting

Description: Report presenting an investigation to study the aerodynamic problems associated with a turbine design for a mode of engine operation which utilizes turbine stator adjustment to maintain a fixed compressor operating point. An indication of the turbine requirements for a particular compressor operating point indicated that a feasible sing-stage air-cooled turbine design could be obtained within reasonable aerodynamic limits. Results regarding the performance of the turbine, pressure ratios, and o… more
Date: May 25, 1954
Creator: Heaton, Thomas R.; Forrette, Robert E. & Holeski, Donald E.
Partner: UNT Libraries Government Documents Department
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