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The torsional deflections of several propellers under operating conditions
Report presenting propeller-blade torsional-deflection data obtained during an investigation of the pressure distribution on constant-chord solid aluminum-alloy blades differing only in camber and thickness. Testing indicated that thinner blades were able to produce greater amounts of deflection. Results regarding torsional deflections are also provided.
Date:
June 22, 1951
Creator:
Gray, W. H. & Allis, A. E.
Object Type:
Report
System:
The UNT Digital Library
Performance characteristics of aircraft cooling ejectors having short cylindrical shrouds
The factors affecting the performance of ejector suitable for aircraft cooling are investigated theoretically and experimentally. The investigation covers a range of shroud-to-nozzle diameter ratios from 1.1 to 1.6, of shroud lengths from 0.2 to 2.28 nozzle diameters, of secondary-to-primary weight-flow ratios from 0 to 0.12, and of ambient-to-nozzle pressure ratios from 0.7 to 0.06. The results of a simplified theoretical analysis based on each type of flow are in good agreement with those experimentally obtained.
Date:
May 22, 1951
Creator:
Kochendorfer, Fred D. & Rousso, Morris D.
Object Type:
Report
System:
The UNT Digital Library
Hinge-moment characteristics for several tip controls on a 60 degree sweptback delta wing at Mach number 1.61
Report presenting an investigation at Mach number 1.61 to determine the hinge-moment characteristics of seven tip controls on a 60 degree sweptback delta wing. Testing occurred over a range of angles of attack and control deflection. The results indicated that the most important parameter in designing delta-wing tip control is the ratio of control-surface area ahead of the hinge line to total control-surface area.
Date:
January 22, 1953
Creator:
Czarnecki, K. R. & Lord, Douglas R.
Object Type:
Report
System:
The UNT Digital Library
A study of the use of controls and the resulting airplane response during service training operations of four jet fighter airplanes
Report presenting results from a limited flight program to obtain information on airplane response and actual rates and amounts of control motion used by service pilot in performance of squadron operational training. Results regarding control deflection, control rates, airplane angular velocities, airplane angular accelerations, angle of attack and angle of sideslip, airplane load factors, and airspeed and altitude are provided.
Date:
June 22, 1954
Creator:
Mayer, John P.; Hamer, Harold A. & Huss, Carl R.
Object Type:
Report
System:
The UNT Digital Library
Aileron and Elevator Hinge Moments of the Bell X-1 Airplane Measured in Transonic Flight
"During the flight investigation of the X-1 airplane the hinge moments of the elevator and aileron control surfaces have been measured over a Mach number range extending to above 1.0. The results of these measurements are presented in this paper" (p. 2).
Date:
June 22, 1953
Creator:
Drake, Hubert M. & McKay, John B.
Object Type:
Report
System:
The UNT Digital Library
Effect of fuels on combustion efficiency of 5-inch ram-jet-type combustor
Report presenting combustion-efficiency data for a 5-inch ramjet-type combustor using a simple V-gutter flame holder. Data for homogeneous fuel-air mixtures of 14 pure fuels and 3 fuel blends cover a range of inlet static pressures and velocities.
Date:
May 22, 1953
Creator:
Reynolds, Thaine W.
Object Type:
Report
System:
The UNT Digital Library
An analysis of the tracking performances of two straight-wing and two swept-wing fighter airplanes with fixed sights in a standardized test maneuver
From Introduction: "This report presents the initial study, the tracking performance of typical fighter airplanes with fixed gunsights. The types of airplanes tested afford two comparisons of particular interest: that between typical World War II and currently operational fighters of greatly increased speed and altitude, and that between conventional and irreversabile power-boosted controls with artificial feel, both installed on the same airframe."
Date:
October 22, 1953
Creator:
Rathert, George A., Jr.; Gadeberg, Burnett L. & Ziff, Howard L.
Object Type:
Report
System:
The UNT Digital Library
Preliminary investigation of the effects of body contouring as specified by the transonic area rule on the aerodynamic characteristics of a delta wing-body combination at Mach numbers of 1.41 and 2.01
Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel to determine the effects of body contouring as specified by the transonic drag-rise area rule on the aerodynamic characteristics of a delta wing-body combination at Mach numbers of 1.41 and 2.01. Body contouring reduced zero-lift drag of a delta wing-body combination from that of a basic wing-body combination without contouring by 18 percent at Mach number 1.41 and 6 percent at Mach number 2.01. Results regarding the characteristics at zero lift and characteristics for the lifting condition are provided.
Date:
September 22, 1953
Creator:
Carlson, Harry W.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of a Shielded Total-Pressure Tube at Transonic Speeds
Report presenting testing of a shielded total-pressure tube with a curved venturi entry in order to obtain the variation of total-pressure error with angle of attack from a range of 0 to 60 degrees and for a range of Mach numbers. The critical angle was found to vary from about 57 degrees at Mach number 0.90 to 56 degrees at Mach number 1.10.
Date:
January 22, 1952
Creator:
Gracey, William; Pearson, Albin O. & Russell, Walter R.
Object Type:
Report
System:
The UNT Digital Library
Summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations at Mach numbers from 0.6 to 1.7 as determined from rocket-powered models
A summary of some effective aerodynamic twisting-moment coefficients of various wing-control configurations for use at a range of Mach numbers. The values obtained were determined by the combined use of experimentally determined free-flight data and subsonic aerodynamic theory.
Date:
January 22, 1952
Creator:
Strass, H. Kurt
Object Type:
Report
System:
The UNT Digital Library
A Transonic Wind-Tunnel Investigation of the Effect of Modifications to an Indented Body in Combination With a 45 Degree Sweptback Wing
Memorandum presenting an investigation of modifications to an indented body which was originally designed on the basis of the transonic drag-rise rule to determine the effects on the aerodynamic characteristics of a 45 degree sweptback-wing-body combination. The investigation covered a range of Mach numbers and angles of attack. Results regarding lift, drag for the nonlifting case, drag for the lifting case, maximum lift-to-drag ratios, and pitching moment are provided.
Date:
September 22, 1953
Creator:
Loving, Donald L.
Object Type:
Report
System:
The UNT Digital Library
The Synthesis of Butylsilanes by a Large-Scale Reduction with Lithium Aluminum Hydride
"Eighty pounds of butylsilanes required for test purposes was synthesized by reducing butyltrichlorosilane with lithium aluminum hydride in dioxane solution. This was safely and successfully accomplished by operating in steel equipment under an atmosphere of oil-pumped nitrogen to minimize the hazards involved in conducting this operation on a large scale. The apparatus and procedure used to carry out the necessary manipulations are described in this report" (p. 1).
Date:
July 22, 1953
Creator:
Kaye, Samuel; Tannenbaum, Stanley & Hipsher, Harold F.
Object Type:
Report
System:
The UNT Digital Library
Effects of Auxiliary and Ejector Pumping on the Mach Number Attainable in a 4 1/2- by 4 1/2-Inch Slotted Tunnel at Low Pressure Ratios
Report presenting the results of an investigation to determine the pressure ratios required to operate a slotted tunnel through a range of Mach numbers where the speed variation is affected by removal of air from the main stream by auxiliary pumping, use of a main-stream-operated ejector located downstream of the test section, and a combination of these methods. Testing was conducted in order to improve the accuracy of transonic wind-tunnel testing.
Date:
January 22, 1954
Creator:
Dennard, John S. & Little, Barney H., Jr.
Object Type:
Report
System:
The UNT Digital Library
Flight Determination of Drag of Normal-Shock Nose Inlets With Various Cowling Profiles at Mach Numbers From 0.9 to 1.5
Report discussing free-flight tests of normal-shock nose-inlet models with 1-series, parabolic, and conic cowling profiles in order to investigate the external drag characteristics at an angle of attack of 0 degrees. The testing occurred at a variety of Mach numbers, mass-flow ratios, and Reynolds numbers. Information about the effect of afterbody length, basic data, and effect of cowl shape is provided.
Date:
October 22, 1953
Creator:
Sears, R. I.; Merlet, C. F. & Putland, L. W.
Object Type:
Report
System:
The UNT Digital Library
Test of single-stage axial-flow fan
"A single-stage axial fan was built and tested in the shop of the propeller-research tunnel of the NACA. The fan comprised a simple 24-blade rotor having a diameter of 21 inches and a solidity of 0.86 and a set of 37 contravanes having a solidity of 1.33. The rotor was driven by a 25-horsepower motor capable of rotating at a speed of 3600 r.p.m. The fan was tested for volume, pressure, and efficiency over a range of delivery pressures and volumes for a wide range of contravane and blade-angle settings" (p. 49).
Date:
September 22, 1941
Creator:
Bell, E. Barton
Object Type:
Report
System:
The UNT Digital Library
An investigation of the drag of windshields in the 8-foot high-speed wind tunnel
Report presents the results of tests made to determine the drag of closed-cockpit and transport-type windshields. The tests were made at speeds corresponding to a Mach number range of approximately 0.25 to 0.58 in the NACA 8-foot high-speed wind tunnel. This speed range corresponds to a test Reynolds number range of 2,510,000 to 4,830,000 based on the mean aerodynamic chord of the full-span model (17.29 in.). The shapes of the windshield proper, the hood, and the tail fairing were systematically varied to include common types and refined design.
Date:
May 22, 1939
Creator:
Robinson, Russell G. & Delano, James B.
Object Type:
Report
System:
The UNT Digital Library
Calculated Effect of Uranium Distribution on Reflector Control Effectiveness for a Water-Moderated Power Reactor
Report presenting two-group theory calculations to determine the effect of nonuniform uranium loading as compared to uniform loading on the reflector control effectiveness attainable in a large thermal reactor usable for aircraft power application. Results regarding reactivities and investments, uranium distributions, and power distributions are provided.
Date:
January 22, 1954
Creator:
Fox, Thomas A. & Valerino, Michael F.
Object Type:
Report
System:
The UNT Digital Library
Flight and Preflight Evaluation of an Automatic Thrust-Coefficient Control System in a Twin-Engine Ram-Jet Missile
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.
Object Type:
Report
System:
The UNT Digital Library
Mechanical design analysis of several noncritical air-cooled turbine disks and a corrugated-insert air-cooled turbine rotor blade
Report presenting a series of turbine wheel designs made for a turbojet engine with an axial-flow compressor. The designs were made to determine the influence of air-cooling on overall engine design, weight, critical-material content, and complexity and to assist with construction of research model full-scale turbines.
Date:
July 22, 1953
Creator:
Moseson, Merland L.; Krasner, Morton H. & Ziemer, Robert R.
Object Type:
Report
System:
The UNT Digital Library
Some theoretical low-speed span loading characteristics of swept wings in roll and sideslip
The Weissinger method for determining additional span loading for incompressible flow is used to find the damping in roll, the lateral center of pressure of the rolling for wing plan forms of various aspect ratios, taper ratios, and sweep angles. In addition, the applicability of the method to the determination of certain other aerodynamic derivatives is investigated, and corrections for the first-order effects of compressibility are indicated. The agreement obtained between experimentally and theoretically determined values for the aerodynamic coefficients indicates that the method of Weissinger is well suited to the calculation of such resulting aerodynamic derivatives of wings as do not involve considerations of tip suction.
Date:
December 22, 1948
Creator:
Bird, John D.
Object Type:
Report
System:
The UNT Digital Library
The application of Green's theorem to the solution of boundary-value problems in linearized supersonic wing theory
From Introduction: "The present paper is restricted to a discussion of wing theory subject to the assumptions of linearized compressible flow. It therefore employs solutions of Laplace's equation and the wave equation for cases where the boundary condition are specified in the plane of the wing."
Date:
December 22, 1948
Creator:
Heaslet, Max A. & Lomax, Harvard
Object Type:
Report
System:
The UNT Digital Library
The effect of nacelle combinations and size on the zero-lift drag of a 45 degree sweptback wing and body configuration as determined by free-flight tests at Mach numbers between 0.8 and 1.3
Investigation of the effect on zero-lift drag of varying the size and number of symmetrically mounted nacelles on a 45 degree sweptback wing and body combination as determined by free-flight tests of rocket-propelled models over a range of Mach and Reynolds numbers. The nacelle configuration consisted of a twin-engine nacelle near the fuselage, a combination of single-engine nacelles at the wing tip and fuselage, a large nacelle at the wing tip, and a large nacelle near the fuselage.
Date:
June 22, 1953
Creator:
Hoffman, Sherwood & Pepper, William B., Jr.
Object Type:
Report
System:
The UNT Digital Library
The effect of initial rate of subsonic diffusion on the stable subcritical mass-flow range of a conical shock diffuser
Report presenting results of a systematic study in the 8- by 6-foot supersonic wind tunnel to determine the effect that area distribution in the subsonic diffuser might have on stability and overall performance of conical-type supersonic diffusers. Drag, pressure recovery, and mass flow are presented for five diffusers designed for maximum mass flow at Mach number 2.0.
Date:
July 22, 1953
Creator:
Nettles, J. C.
Object Type:
Report
System:
The UNT Digital Library
High-altitude performance of 9.5-inch-diameter tubular experimental combustor with fuel staging
Report presenting an investigation of 57 experimental tubular designs embodying adjacent fuel-rich and air-rich regions and axial staging of the fuel introduction at simulated high-altitude conditions. Results regarding the development of pilot, development of secondary-air admission sleeve, development of final configuration, and performance of best configuration are provided.
Date:
March 22, 1954
Creator:
Scull, Wilfred E.
Object Type:
Report
System:
The UNT Digital Library