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Large-scale low-speed wind-tunnel tests of a model having a 60 degree delta horizontal canard control surface and wing to obtain static-longitudinal-stability and canard surface hinge-moment data

Description: Report presenting a wind-tunnel investigation of a model equipped with a 60 degree delta wing and a 60 degree delta horizontal all-movable canard control surface to determine the stability, control, and canard-surface hinge-moment characteristics at low speeds and at a Reynolds number of 9 x 10(exp 6). Two longitudinal positions of the canard surface were tested. Results regarding lift and pitching moment, drag, and hinge moment are provided.
Date: June 17, 1954
Creator: Burrows, Dale L.
Partner: UNT Libraries Government Documents Department

High-Speed Drag and Opening Characteristics of a Kaman Rotochute Model

Description: Report presenting an experimental investigation in the 7- by 10-foot tunnel in a range of Mach numbers to determine the drag and opening characteristics of a model of a Kaman Aircraft Corporation Rotochute. The Rotochute is a two-bladed flapping rotor with governor-controlled blades designed for lowering cargo containers from high-speed aircraft tested at various Mach numbers simulating constant rates of descent.
Date: June 10, 1954
Creator: Lockwood, Vernard E.
Partner: UNT Libraries Government Documents Department

Vapor pressures and calculated heats of vaporization of concentrated nitric acid solutions in the composition range 71 to 89 percent nitrogen dioxide, 1 to 10 percent water, and in the temperature range 10 to 60 degrees C

Description: From Summary: "Total vapor pressures were measured for 16 acid mixtures of the ternary system nitric acid, nitrogen dioxide, and water within the temperature range 10 degrees to 60 degrees Celsius, and with the composition range 71 to 89 weight percent nitric acid, 7 to 20 weight percent nitrogen dioxide, and 1 to 10 weight percent water. Heats of vaporization were calculated from the vapor pressure measurements for each sample for the temperatures 25, 40, and 60 degrees Celsius. The ullage of the apparatus used for the measurements was 0.46. Ternary diagrams showing isobars as a function of composition of the system were constructed from experimental and interpolated data for the temperatures 25, 40, 45, and 60 degrees C and are presented herein."
Date: February 5, 1954
Creator: McKeown, A. B. & Belles, Frank E.
Partner: UNT Libraries Government Documents Department

Exploratory investigation of external stores in the aerodynamic characteristics of a 1/16-scale model of the Douglas D-558-II research airplane at a Mach number of 2.01

Description: Report presenting an investigation of stores on the Douglas D-558-II research airplane in the wind tunnel and in flight using various store configurations. The drag measured for all store configurations was high, from two to three times the free-air drag estimated for the store and pylon. Results regarding longitudinal characteristics and lateral characteristics are provided.
Date: August 25, 1954
Creator: Smith, Norman F.
Partner: UNT Libraries Government Documents Department

Flight-determined pressure measurements over the wing of the Douglas D-558-II research airplane at Mach numbers up to 1.14

Description: Report presenting an investigation of the section and panel characteristics and loads obtained from pressure measurements over a 35 degree sweptback wing at level-flight lifts for a range of Mach numbers. Section pressure distributions were taken at the root, midspan, and tip stations of a Douglas D-558-II airplane.
Date: March 12, 1954
Creator: Peele, James R.
Partner: UNT Libraries Government Documents Department

Flight determination of the buffeting characteristics of the Bell X-5 research airplane at 58.7 degrees sweepback

Description: Report presenting flight measurements of the buffeting characteristics of the Bell X-5 airplane at 58.7 degrees of sweepback at a range of Mach numbers and altitudes. Information about tail buffeting and wing buffeting at several angles of attack is provided. The pilot considered the buffeting to be unobjectionable throughout the entire test region.
Date: May 24, 1954
Creator: Briggs, Donald W.
Partner: UNT Libraries Government Documents Department

Flight determination of the drag of conical-shock nose inlets with various cowling shapes and axial positions of the center body at Mach numbers from 0.8 to 2.0

Description: Report presenting free-flight testing of conical-shock nose inlet models with cowls of fineness ratio 3 with five different profiles. Three of the profiles were mostly conic with different lip shapes, one was parabolic, and one was NACA 1-series. Results regarding the basic data, effect of cone position, comparison of profile shapes, and effect of mass-flow ratio are provided.
Date: September 10, 1954
Creator: Merlet, Charles F. & Putland, Leonard W.
Partner: UNT Libraries Government Documents Department

Flight and preflight evaluation of an automatic thrust-coefficient control system in a twin-engine ram-jet missile

Description: Report presenting a flight and preflight evaluation of an automatic thrust-coefficient control system in a twin-engine ram-jet missile. A flicker-type single-loop servocontrol system is shown to be a usable way of controlling ram-jet thrust coefficients.
Date: January 22, 1954
Creator: Dettwyler, H. Rudolph & Trout, Otto F., Jr.
Partner: UNT Libraries Government Documents Department

Flight tests of a man standing on a platform supported by a teetering rotor

Description: Report presenting a series of flight tests to determine the flying qualities of a man standing on a platform supported by a teetering rotor. The machine was tested with a free-teetering rotor, a spring-restrained rotor, and a rotor and foot platform isolated from the framework by rubber connections. Results of the different configurations during indoor and outdoor flights are presented.
Date: March 24, 1954
Creator: Hill, Paul R. & Kennedy, T. L.
Partner: UNT Libraries Government Documents Department

An investigation of a supersonic aircraft configuration having a tapered wing with circular-arc sections and 40 degree sweepback: stability and control characteristics at a Mach number of 1.61 of the complete configuration equipped with spoilers

Description: Report discussing an investigation to determine the stability and control characteristics of a supersonic aircraft configuration with a 40 degree sweptback wing and equipped with spoiler lateral control devices at Mach number 1.61. The effects of various types of spoilers, spoiler span, spoiler projection, and chordwise location were investigated, as well as the hinge-moment characteristics of the plain spoiler.
Date: September 10, 1954
Creator: Hamilton, Clyde V. & Driver, Cornelius
Partner: UNT Libraries Government Documents Department

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 operational requirements are provided.
Date: May 25, 1954
Creator: Heaton, Thomas R.; Forrette, Robert E. & Holeski, Donald E.
Partner: UNT Libraries Government Documents Department

An investigation of a method for obtaining hydrodynamic data at very high speeds with a free water jet

Description: Report presenting information regarding the feasibility of using a rectangular free water jet to obtain hydrodynamic data at very high speeds. Total-head pressure distributions in the jet and experimental hydrodynamic lift data is provided and compared to data obtained in water tank testing. The data obtained indicates that it is feasible to use a free water jet for this purpose.
Date: June 14, 1954
Creator: Weinflash, Bernard & McGehee, John R.
Partner: UNT Libraries Government Documents Department

Investigation of a transonic turbine designed for a maximum rotor-blade suction-surface relative Mach number of 1.57

Description: From Summary: "A transonic turbine designed for a maximum blade-surface relative Mach number of 1.57 was investigated experimentally. The performance of the turbine is compared with that of three other transonic turbines that were previously investigated."
Date: October 11, 1954
Creator: Whitney, Warren J.; Wong, Robert Y. & Monroe, Daniel E.
Partner: UNT Libraries Government Documents Department

Investigation of adjustable supersonic inlet in combination with J34 engine up to Mach 2.0

Description: Report presenting an investigation of an annular nose inlet equipped with a remotely controlled translating spike and variable bypass in the supersonic wind tunnel. The inlet performance was explored with the airflow controlled by an operating J34 engine and with the engine simulated by a choked plug. Results regarding the performance of the inlet, corrective action that should be applied to avoid pulsing, performance of the subsonic portion of the diffuser, supersonic performance, radial-flow profiles, and other flow profiles are provided.
Date: October 15, 1954
Creator: Nettles, J. C. & Leissler, L. A.
Partner: UNT Libraries Government Documents Department

Investigation of a pulse-jet-powered helicopter rotor on the Langley helicopter test tower

Description: Report discussing testing of a helicopter rotor powered by pulse-jet engines located at the rotor-blade tips. The basic hovering characteristics of the rotor and propulsive characteristics of the pulse-jet engine were obtained at a range of engine speeds with the engines rigidly fixed to the blade tips and with the engines free to pivot. Measurements were also taken to determine the effect of inlet blockage on the power-off drag of the jet engines and the noise intensity in the vicinity of operating engines.
Date: February 8, 1954
Creator: Radin, Edward J. & Carpenter, Paul J.
Partner: UNT Libraries Government Documents Department

Investigation of a high-temperature single-stage turbine suitable for air cooling and turbine stator adjustment 2: performance of vortex turbine at various stator settings

Description: Report presenting a consideration of a mode of engine operation that requires operational flexibility of the turbine, which requires that the turbine stator and exhaust nozzle area are adjusted to maintain a fixed compressor operating point. Results regarding turbine performance and comparison of predicted and experimental turbine performance are provided.
Date: August 3, 1954
Creator: Heaton, Thomas R.; Holeski, Donald E. & Forrette, Robert E.
Partner: UNT Libraries Government Documents Department

Investigation of a missile airframe with control surfaces consisting of projecting quadrants of the nose cone

Description: Report presenting the results of an investigation of a missile model with extensible control surfaces and small-span fins. Normal-force, axial-force, and pitching-moment coefficients based on body cross-sectional area and diameter are given for various control deflections up to a maximum of 30 degrees.
Date: March 15, 1954
Creator: Lazzeroni, Frank A.
Partner: UNT Libraries Government Documents Department

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

Investigation of Supersonic-Compressor Rotors Designed with External Compression

Description: Report presenting an investigation of the possibility of utilizing the relatively good characteristics of the spike-type diffuser in the supersonic compressor. Results regarding the overall performance, inlet conditions, outlet conditions, entrance flow conditions, and estimated performance of subsonic portion of rotor passage are provided.
Date: September 24, 1954
Creator: Jahnsen, Lawrence J. & Hartmann, Melvin J.
Partner: UNT Libraries Government Documents Department

Investigation of transient combustion characteristics in a single tubular combustor

Description: An investigation was conducted to determine the combustion response to rapid fuel-flow changes in a single tubular combustor at two simulated altitude-rotor speed conditions of 25,000 feet-70 percent rated engine speed and 50,000 feet-70 percent rated engine speed. Limiting rates of change of fuel flow (acceleration limits) were determined and the effects of certain combustion air flow variables on the transient combustion characteristics were studied with the aid of rapid-response instrumentation.
Date: February 11, 1954
Creator: Donlon, Richard H.; McCafferty, Richard J. & Straight, David M.
Partner: UNT Libraries Government Documents Department

Investigation of the aerodynamic characteristics at high supersonic Mach numbers of a family of delta wings having double-wedge sections with the maximum thickness at 0.18 chord

Description: Report presenting a program to investigate the aerodynamic characteristics of a family of delta wings with a blunt double-wedge section in the hypersonic tunnel at Mach number 6.9. The wings varied at semiapex angle and were tested over a range of angles of attack and Reynolds numbers. Results regarding lift and drag characteristics, center of pressure and moment coefficient, Schlieren photographs, and surface film flow studies are presented.
Date: October 20, 1954
Creator: Bertram, Mitchel H. & McCauley, William D.
Partner: UNT Libraries Government Documents Department

Investigation of mechanical fastenings for solid turbine blades made from ductile materials

Description: Report presenting rupture testing conducted on tensile specimens of fir-tree turbine blade root fastenings for three specific turbojet engines. Testing was conducted at temperatures from 0 degrees to 1500 degrees. Results regarding the short-time tests at various temperatures, long-time stress-rupture tests at 1200 degrees Fahrenheit, long-time tests at increased temperature, and remarks on the criteria for using the fir-tree root design are provided.
Date: August 2, 1954
Creator: Meyer, André J., Jr.; Kaufman, Albert & Caywood, W. C.
Partner: UNT Libraries Government Documents Department

Thrust and pumping characteristics of a series of ejector-type exhaust nozzles at subsonic and supersonic flight speeds

Description: Report presenting an investigation conducted in the 8- by 6-foot supersonic wind tunnel to determine the thrust and pumping characteristics of a series of ejector exhaust nozzles. Data were obtained for various ejector diameter and spacing ratios at a range of Mach numbers, pressure-ratio ranges, and secondary-primary weight-flow ratios. Results regarding the primary-nozzle mass-flow coefficients, performance comparison of configurations, effect of free-stream Mach number on the ejectors, net thrust characteristics, and comparison to conventional nozzles are provided.
Date: November 17, 1954
Creator: Hearth, Donald P. & Valerino, Alfred S.
Partner: UNT Libraries Government Documents Department

Pressure distributions on triangular and rectangular wings to high angles of attack Mach numbers 1.45 and 1.97

Description: Pressure distributions were measured over rectangular wings of aspect ratio 2 and triangular wings of aspect ratios 2 and 4 at Mach numbers of 1.45 and 1.97. The investigation includes some comparison of the effects of Reynolds number and of thickening the wing root sections on the loading.
Date: June 25, 1954
Creator: Kaattari, George E.
Partner: UNT Libraries Government Documents Department