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Investigations toward simplification of missile control systems

Description: Paper presenting three ideas regarding potential simplifications of missile-control systems in order to make them more reliable without sacrificing system performance. The three methods presented include an autorotating-vane spoiler, a bellows flap, and free controls. All are based on modified airplane control systems.
Date: November 12, 1953
Creator: Curfman, Howard J., Jr.; Strass, H. Kurt & Crane, Harold L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effects of a Small Jet of Air Exhausting From the Nose of a Body of Revolution in Supersonic Flow

Description: Report presenting the results of an investigation to determine the effects of a small jet of air exhausting from the nose of an elliptical body of revolution upon boundary-layer transition and the viscous, pressure, and total drag of the forebody at three body stations at Mach number 1.62. The jet effects on body pressure, pressure variations, boundary-layer transition, and total drag are provided.
Date: November 12, 1952
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Ice Prevention on Aircraft by Means of Engine Exhaust Heat and a Technical Study of Heat Transmission From a Clark Y Airfoil

Description: "This investigation was conducted to study the practicability of employing heat as a means of preventing the formation of ice on airplane wings. The report relates essentially to technical problems regarding the extraction of heat from the exhaust gases and its proper distribution over the exposed surfaces. In this connection a separate study has been made to determine the variation of the coefficient of heat transmission along the chord of a Clark Y airfoil. Experiments on ice prevention both … more
Date: June 12, 1931
Creator: Theodorsen, Theodore & Clay, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Lateral Stability and Control Measurements of a Fighter-Type Airplane With a Low-Aspect-Ratio Unswept Wing and a Tee-Tail

Description: Report presenting an investigation of the lateral stability and control effectiveness of a model of a fighter-type airplane model with a low-aspect-ratio and 3.4-percent-thick wing with negative dihedral at a range of Mach numbers, sideslip angles, and angles of attack. Results regarding the lateral characteristics at zero angle of attack, lifting conditions, and lateral and directional controls are provided.
Date: June 12, 1956
Creator: Arabian, Donald D. & Schmeer, James W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A flight evaluation of the longitudinal stability characteristics associated with the pitch-up of a swept-wing airplane in maneuvering flight at transonic speeds

Description: This report presents the results of flight measurements of longitudinal stability and control characteristics made on a swept-wing jet aircraft to determine the origin of the pitch-up encountered in maneuvering flight at transonic speeds. For this purpose measurements were made of elevator angle, tail angle of attack, and wing-fuselage pitching moments (obtained from measurements of the balancing tail loads).
Date: September 12, 1951
Creator: Anderson, Seth B. & Bray, Richard S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Extrapolation techniques applied to matrix methods in neutron diffusion problems

Description: "A general matrix method is developed for the solution of characteristic-value problems of the type arising in many physical applications. The scheme employed is essentially that of Gauss and Seidel with appropriate modifications needed to make it applicable to characteristic-value problems. An iterative procedure produces a sequence of estimates to the answer; and extrapolation techniques, based upon previous behavior of iterants, are utilized in speeding convergence. Theoretically sound limit… more
Date: May 12, 1955
Creator: McCready, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis and Calculation by Integral Methods of Laminar Compressible Boundary-Layer With Heat Transfer and With and Without Pressure Gradient

Description: From Introduction: "The purpose of the present report is to present a comprehensive summary of theoretical investigations of comprehensible laminar boundary layers which have been carried out since 1949 at the Polytechnic Institute of Brooklyn under the sponsorship and with the financial assistance of the National Advisory Committee for Aeronautics. The results of these investigations are contained primarily in references 1 to 7."
Date: April 12, 1955
Creator: Morduchow, Morris
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine

Description: Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date: June 12, 1957
Creator: Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Summary of Subsonic-Diffuser Data

Description: Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.
Date: October 12, 1956
Creator: Henry, John R.; Wood, Charles C. & Wilbur, Stafford W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Description: 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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds

Description: Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.
Date: October 12, 1954
Creator: O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic loadings associated with swept and unswept spoilers on a flat-plate at Mach numbers of 1.61 and 2.01

Description: Report presenting an investigation at two Mach numbers to examine the flow, force, and moment characteristics associated with spoilers mounted on a flat plate at a range of sweep angles. Pressure measurements were obtained over the plate and spoiler faces. The pressures were integrated to determine the spoiler lift, pitching-moment, drag, and hinge-moment characteristics.
Date: March 12, 1956
Creator: Lord, Douglas R. & Czarnecki, K. R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition

Description: Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date: August 12, 1948
Creator: Acker, Loren W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine. 7: Rotor-Blade Fabrication Procedures

Description: "An experimental investigation was conducted to determine the cooling effectiveness of a wide variety of air-cooled turbine-blade configurations. The blades, which were tested in the turbine of a - commercial turbojet engine that was modified for this investigation by replacing two of the original blades with air-cooled blades located diametrically opposite each other, are untwisted, have no aerodynamic taper, and have essentially the same external profile. The cooling-passage configuration is … more
Date: September 12, 1951
Creator: Long, Roger A. & Esgar, Jack B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Method for Calculating the Lift and Center of Pressure of Wing-Body-Tail Combinations at Subsonic, Transonic, and Supersonic Speeds

Description: Report presenting a method for calculating the lift and pitching-moment characteristics of circular cylindrical bodies in combination with triangular, rectangular, or trapezoidal wings or tails through the subsonic, transonic, and supersonic speed ranges. A computing table and set of design charts are presented to reduce the calculations to routine operations. Information about lift, center of pressure, effects of wing incidence, and limitations and extensions of the method is provided.
Date: November 12, 1953
Creator: Nielsen, Jack Norman; Kaattari, George E. & Anastasio, Robert F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Rocket-Powered-Model Investigation of the Effects of Aeroelasticity on the Rolling Effectiveness of an 8.06-Percent-Scale McDonnell F3H-1 Airplane Wing at Mach Numbers From 0.5 to 1.4

Description: Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.
Date: April 12, 1954
Creator: English, Roland D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Review of NACA Research Through 1954 on Boron Compounds as Fuels for Jet Aircraft (Project Zip)

Description: Report discussing a project to determine a high-energy fuel suitable for turbojet-powered aircraft. Components of the project include thermal and combustion properties, experiments with combustors using boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and boron fuel use in ramjet flights. The most promising fuel found in the report is pentaborane.
Date: April 12, 1957
Creator: Olson, Walter T.; Breitwieser, Roland & Gibbons, Louis C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Local Heat Transfer to Blunt Noses at High Supersonic Speeds

Description: Memorandum presenting a brief summary of the recent theoretical and experimental work on local heat-transfer rates on blunt-nose bodies. Results regarding the calculation of local flow conditions, prediction of stagnation-point heating rates, and calculation of heating rates over entire nose are provided.
Date: July 12, 1957
Creator: Stoney, William E., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Several Jet-Engine Air-Inlet Configurations on the Low-Speed Static Longitudinal Stability Characteristics and Quantity Flow of a 1/6-Scale Model of the MX-1764 Airplane

Description: Memorandum presenting an investigation in the 7- by 10-foot tunnel to determine the effect of wing-root leading-edge and scoop-type jet-engine air-inlet configurations on the static longitudinal stability characteristics and the duct-flow characteristics of a scale model of the MX-1764 airplane. The addition of the inlet configurations to the model generally resulted in slight reductions in longitudinal stability and increases of maximum lift coefficient.
Date: January 12, 1954
Creator: Croom, Delwin R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Acceleration Schedule Control for Accelerating a Turbojet Engine and Its Use With a Speed Control

Description: Memorandum presenting a study of an acceleration-limiting control on a turbojet engine in order to determine its feasibility as an acceleration control. A proportional-plus-integral type of controller was used in the investigation. Results regarding the one-loop control and two-loop control are provided.
Date: May 12, 1958
Creator: Gerus, Theodore F.; Powers, Albert G. & Heppler, Herbert J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Some Factors Affecting the Static Longitudinal and Directional Stability Characteristics of Supersonic Aircraft Configurations

Description: Memorandum presenting a survey of the problems introduced by the increased longitudinal stability and reduced directional stability of aircraft operating in the low supersonic speed range. Information regarding longitudinal stability and directional stability are provided.
Date: July 12, 1957
Creator: Spearman, M. Leroy
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

In-Flight Gains Realized by Modifying a Twin Side-Inlet Induction System

Description: Memorandum presenting an investigation of the effects of modifying a twin side-inlet duct system on an interceptor airplane as recorded and analyzed over an altitude range from about 25,000 to 51,000 feet throughout the transonic speed range to a Mach number of about 1.2. The modifications consisted primarily of redesigning the inlet lip, increasing the cross-sectional area of the inlet and diffuser, and adding a region of duct contraction ahead of the engine.
Date: December 12, 1957
Creator: Saltzman, Edwin J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Total-Pressure-Recovery Characteristics of a Model of the McDonnell XF3H-1 Inlets and Forebody in a Free Jet at a Mach Number of 1.55

Description: Report presenting free jet tests of a model of the inlets and forebody of the McDonnell XF3H-1 airplane with the original and two alternate nose shapes. Results regarding the total-pressure recovery after diffusion, maximum mass-flow ratio, inlet total-pressure profile, shadowgraphs, flow variation, and pressure oscillations are provided.
Date: March 12, 1952
Creator: Merlet, Charles F. & Carter, Howard S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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