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A Preliminary Investigation of the Performance of a Short Length Turbojet Combustor Using Vaporized Hydrocarbon Fuels
"Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors" (p. 1).
Date:
January 7, 1958
Creator:
Jones, R. E. & Pawlik, E. V.
System:
The UNT Digital Library
Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine
Report presenting an investigation of the performance of a diffuser static-pressure-ratio control with a normal shock-positioning limit on a ramjet engine installed in an altitude free-jet facility. Testing occurred at Mach numbers of 2.35 and 2.50, altitudes of 50,000, 60,000 and 65,000 feet, and angles of attack of 0 and 7 degrees. Results regarding the effects of control constants, effects of disturbance size and operating point, effects of flight conditions, and control limitations and possible improvements are provided.
Date:
January 15, 1957
Creator:
Dunbar, William R.; Wentworth, Carl B. & Crowl, Robert J.
System:
The UNT Digital Library
Tracking Performance of a Swept-Wing Fighter With a Director-Type Radar Fire-Control System and Scope Presentation
Memorandum presenting flight tests conducted with an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracking performance in the manual mode of operation were investigated. Results regarding fixed-sight tracking and tracking with scope presentation are provided.
Date:
January 20, 1958
Creator:
Turner, Horward L.; Rathert, George A., Jr. & Heinle, Donovan R.
System:
The UNT Digital Library
Analysis of Limitations Imposed on One-Spool Turbojet-Engine Designs by Turbines Having Downstream Stators at 0, 2.0, and 2.8 Flight Mach Numbers
Memorandum presenting an aerodynamic design-point analysis of one-spool turbojet engines with one-stage turbines with one and with two rows of downstream stator blades. The object of the analysis was to evaluate the design characteristics of the turbines in comparison with conventional one- and two-stage turbines, to determine the extent to which exit whirl can be increased before causing weight-flow capacity to decrease, and to determine the effect of downstream stators on engine design limitations.
Date:
January 19, 1955
Creator:
Cavicchi, Richard H. & Constantine, Anita B.
System:
The UNT Digital Library
A Study of Injection Processes for 15-percent Fluorine-85- Percent Oxygen and Heptane in a 200-pound-thrust Rocket Engine
Injection techniques for fluorine, oxygen, and heptane in 200-pound thrust rocket engine.
Date:
January 15, 1957
Creator:
Heidmann, M. F.
System:
The UNT Digital Library
Speed-Brake Investigation at Low Speed of a 1/10-Scale Model of the MX-1554A Airplane With a Circular Jet Nozzle
Report discussing an investigation of the effect of curved speed brakes on the drag characteristics and longitudinal stability and control characteristics of a model of the MX-1554A with a circular jet nozzle. The speed brakes were tested at several deflections, gaps, and locations in the landing configuration and clean configuration. Results of a lateral- and directional-stability study due to reduction in the vertical tail area are also provided.
Date:
January 7, 1954
Creator:
Solomon, Martin
System:
The UNT Digital Library
Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane
Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.
Date:
January 13, 1958
Creator:
Healy, Frederick M.
System:
The UNT Digital Library
Preliminary Wind-Tunnel Investigation of the Performance of Republic F-105 Wing-Root Inlet Configurations at Various Angles of Attack and a Mach Number of 2.01
"A 1/13-scale model of the forebody of the Republic F-105 with twin-duct wing-root inlets was tested in the Langley 4- by 4-foot supersonic pressure tunnel through a range of angle of attack from -4 deg to 15 deg at a Mach number of 2.01 and a Reynolds number of approximately 3.4 x 10(exp 6) per foot. The tests were made with four configurations which incorporated varying amounts of sweep and stagger of the inlet leading edges, modifications to the areas of the boundary-layer diverter floor plate, and modifications to the area of the boundary-layer diverter bleed slots. The highest overall pressure recovery at an angle of attack of 0 deg (average total-pressure recovery, 0.84 mass-flow ratio, 0.98) was achieved with configuration having an inlet leading-edge sweep angle of 58 deg with no leading-edge stagger" (p. 1).
Date:
January 15, 1957
Creator:
Kouyoumjian, Walter L.
System:
The UNT Digital Library
An Analysis of a Nuclear Powered Supercritical-Water Cycle for Aircraft Propulsion
Memorandum presenting an analysis to indicate the feasibility of the supercritical water compressor jet cycle for nuclear powered aircraft. Performance values of the cycle are given for a range of design-point engine operating conditions and subsonic flight conditions.
Date:
January 19, 1953
Creator:
Karp, Irving M.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Subsonic and Supersonic Speeds of a Model of a Tailless Fighter Airplane Employing a Low-Aspect-Ratio Swept-Back Wing-Stability and Control
Memorandum presenting the results of a wind-tunnel investigation of the static stability and control characteristics of a model of a fighter airplane employing a low-aspect-ratio swept-back wing with trailing-edge elevons, a swept-back vertical tail, but no horizontal tail. The results indicated that, for the test conditions at which the investigation was conducted, the model, with elevons undeflected, was longitudinally and directionally stable.
Date:
January 12, 1953
Creator:
Smith, Willard G.
System:
The UNT Digital Library
Experimental Investigation of a Body Flare for Obtaining Pitch Stability and a Body Flap for Obtaining Pitch Control in Hypersonic Flight
Memorandum presenting the effectiveness of a body flare as a pitch-stabilizing device and a body flap as a pitch-control device investigated experimentally at Mach numbers from 3.00 to 6.25. The basic test body was rotationally symmetric and consisted of a fineness ratio 3 nose followed by a fineness ratio 9 afterbody. Results regarding the stability of the flared body, effect of body flap on lift and drag, trim conditions, flow visualization studies, and comparison of theory and experiment are provided.
Date:
January 18, 1955
Creator:
Eggers, A. J., Jr. & Syvertson, Clarence A.
System:
The UNT Digital Library
Material Compatibility With Gaseous Fluorine
Report presenting static tests on the compatibility of gaseous fluorine with various liquids, solid plastics, waxes, and greases at pressures of 0 and 1500 pounds per square inch gage and atmospheric temperature. Several materials were found to be compatible at atmospheric pressure, but only Teflon and ruby were compatible under static conditions at 1500 pounds per square inch gage.
Date:
January 23, 1957
Creator:
Price, Harold G., Jr. & Douglass, Howard W.
System:
The UNT Digital Library
Static Lateral-Directional Stability Characteristics of Five Contemporary Airplane Models From Wind-Tunnel Tests at High Subsonic and Supersonic Speeds
Memorandum presenting the static lateral-directional stability characteristics of several airplane models recently investigated which cover many of the geometric arrangements of high-speed airplane components of current interest. The results are limited to the most pertinent aerodynamic phenomena contributing to the lateral-directional characteristics of each airplane type. Results for five different models are provided.
Date:
January 4, 1956
Creator:
Smith, Willard G. & Ball, Louis H.
System:
The UNT Digital Library
Investigation of Drag and Static Longitudinal and Lateral Stability Characteristics of a Model of a 40.4 Degree Swept-Wing Airplane at Mach Numbers of 1.56 and 2.06
Memorandum presenting an investigation to determine the drag, longitudinal stability, and lateral stability characteristics of a model of a fighter-type airplane. Several modifications were made to the model in an attempt to eliminate pitch-up.
Date:
January 18, 1957
Creator:
Carmel, Melvin M. & Turner, Kenneth L.
System:
The UNT Digital Library
Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane
Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.
Date:
January 24, 1958
Creator:
Sellers, Thomas B.
System:
The UNT Digital Library
Measurement of Static Forces on Externally Carried Bombs of Fineness Ratios 7.1 and 10.5 in the Flow Field of a Swept-Wing Fighter- Bomber Configuration at a Mach Number of 1.6
Memorandum presenting forces and moments measured at Mach number 1.6 in the 4- by 4-foot supersonic pressure tunnel on bombs of fineness ratios 7.0 and 10.5 in the presence of a swept-wing fighter-bomber airplane configuration for a large number of positions under the fuselage. The results can be used to calculate bomb-drop paths.
Date:
January 31, 1957
Creator:
Geier, Douglas J. & Carlson, Harry W.
System:
The UNT Digital Library
Investigation of Porous Gas-Heated Leading-Edge Section for Icing Protection of a Delta Wing
"A tip section of a delta wing having an NACA 0004-65 airfoil section and a 600 leading-edge sweepback was equipped with a porous leading-edge section through which hot gas was bled for anti-icing. Heating rates for anti-icing were determined for a wide range of icing conditions. The effects of gas flow through the porous leading-edge section on airfoil pressure distribution and drag in dry air were investigated" (p. 1).
Date:
January 19, 1955
Creator:
Bowden, Dean T.
System:
The UNT Digital Library
Icing Protection for a Turbojet Transport Airplane: Heating Requirements, Methods of Protection, and Performance Penalties
"The problems associated with providing icing protection for the critical components of a typical turbojet transport airplane operating over a range of probable icing conditions are analyzed and discussed. Heating requirements for several thermal methods of protection are evaluated and the airplane performance penalties associated with providing this protection from various energy sources are assessed. The continuous heating requirements for icing protection and the associated airplane performance penalties for the turbojet transport are considerably increased over those associated with lower-speed aircraft" (p. 1).
Date:
January 1953
Creator:
Gelder, Thomas F.; Lewis, James P. & Koutz, Stanley L.
System:
The UNT Digital Library
Experimental Investigation of Radome Icing and Icing Protection
Memorandum presenting an investigation conducted in the icing research tunnel to determine the icing characteristics, the effects of icing on radar operation, and the protection requirements for two radome configurations. The radomes were for the F-89 airplane and were investigated at airspeeds up to 290 miles per hour, air total temperatures from -15 to 20 degrees Fahrenheit, water contents up to 1.0 gram per cubic meter, and angles of attack of 0 and 4 degrees.
Date:
January 20, 1953
Creator:
Lewis, James P. & Blade, Robert J.
System:
The UNT Digital Library
Design of Combustor for Long-Range Ram-Jet Engine and Performance of Rectangular Analog
Memorandum presenting the design of a piloted combustor intended for a ramjet engine of long flight range. The unit comprises a large annular basket of V-type cross section, the inner surface of which is slotted and bent into small V-gutters.
Date:
January 29, 1954
Creator:
Rayle, Warren D. & Koch, Richard G.
System:
The UNT Digital Library
Preliminary Transient Performance Data on the Fuel Control of the XRJ47-W-5 Ram-Jet Engine
Report discussing the characteristics of the fuel control of the 48-inch diameter WRJ47-W-5 ramjet engine, including the time history of the fuel system pressures, fuel flow, and engine inlet total pressure. Oscillograph traces for the different variables are provided as well as the accuracy of the calibration factors.
Date:
January 29, 1954
Creator:
Welna, Henry J. & Smith, Ivan D.
System:
The UNT Digital Library
On the Permeability of Porous Materials
Note presenting an investigation of the effects on porous-material permeability characteristics of the absolute pressure level, choking of the flow, bending the material, and other factors. Experiments showed permeability characteristics to be appreciably affected by absolute pressure level, flow choking, and thickness of the material. Results regarding testing with wire cloth and sintered metal are provided.
Date:
January 1956
Creator:
Yates, E. Carson, Jr.
System:
The UNT Digital Library
The Resistance to Air Flow of Porous Materials Suitable for Boundary-Layer-Control Applications Using Area Suction
"Measurements were made of the resistance to air flow of commercially available porous materials. Three general types of porous media were tested - granular (sintered materials), fibrous (felt cloths and filter papers), and perforated. The flow-resistance characteristics of the porous materials tested are presented in a form intended to assist in the selection of materials for applications to boundary-layer control using area suction" (p. 1).
Date:
January 1954
Creator:
Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
System:
The UNT Digital Library
A Fibrous-Glass Compact as a Permeable Material for Boundary-Layer-Control Applications Using Area Suction
"Measurements were made of the resistance of fibrous-glass compacts to normal air flow. The flow resistance was related to the thickness and density. As a porous material for boundary-layer-control applications using area suction, the fibrous-glass compact could be made to any desired thickness and permeability and sandwiched between perforated rigid surfaces" (p. 1).
Date:
January 1955
Creator:
Dannenberg, Robert E.; Weiberg, James A. & Gambucci, Bruno J.
System:
The UNT Digital Library