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Annual Report of the National Advisory Committee for Aeronautics (42nd). Administrative Report Including Technical Report Nos. 1254 to 1295
Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date:
1957
Creator:
unknown
System:
The UNT Digital Library
Stabilization of 50-Percent Magnesium - JP-4 Slurries With Some Aluminum Soaps of C(Sub 8) Acids
Report presenting an exploratory investigation of three aluminum disoaps of C(sub 8) acids to determine the gelling properties and stabilizing ability in slurries of 50 percent magnesium power and JP-4 fuel. All of the soaps were found to gel the slurries satisfactorily and to exhibit adequate reproducibility of gel properties. Results regarding the soap behaviors, effects of temperature, viscosity, and formation of the gel structures are provided.
Date:
May 13, 1954
Creator:
Caves, Robert M.
System:
The UNT Digital Library
Collection of zero-lift drag data on bodies of revolution from free-flight investigations
Report presenting a compilation of most of the zero-lift drag obtained from free-flight measurements on fin-stabilized bodies of revolution. Results regarding friction drag, base pressure and base drag, pressures on a forward facing step, and fin pressure drag are provided.
Date:
September 3, 1957
Creator:
Stoney, William E., Jr.
System:
The UNT Digital Library
Summary of Methods of Measuring Angle of Attack on Aircraft
Note presenting wind-tunnel calibrations of three types of angle-of-attack sensing devices - the pivoted vane, the differential pressure tube, and the null-seeking pressure tube. Flight data on the position errors for three sensor locations - ahead of the fuselage nose, ahead of the wing tip, and on the forebody of the fuselage - are also presented. Various methods for calibrating angle-of-attack installations in flight are briefly described.
Date:
August 1958
Creator:
Gracey, William
System:
The UNT Digital Library
Normal component of induced velocity for entire field of a uniformly loaded lifting rotor with highly swept wake as determined by electromagnetic analog
Report presenting values of the nondimensional normal component of induced velocity throughout the flow field of a uniformly loaded lifting rotor operating in the upper half of the helicopter speed range in the form of graphs and tables. The results obtained should be useful for estimating the induced velocity distribution about lifting rotors in general and for synthesizing the distributions over the rotor disk for the case of any specified non-uniform loading.
Date:
June 1958
Creator:
Castles, Walter, Jr.; Durham, Howard L., Jr. & Kevorkian, Jirair
System:
The UNT Digital Library
Stability Derivatives of Cones at Supersonic Speeds
"The aerodynamic stability derivatives due to pitching velocity and vertical acceleration are derived for circular cones traveling at supersonic speeds. Both first-order and a combination of first and second order potential solutions are obtained, and in calculations for the forces, no approximations are made to the tangency condition or the isentropic pressure relation. In addition, expressions for the forces, moments, and stability derivatives of arbitrary bodies of revolution are derived from Newtonian impact theory" (p. 1).
Date:
September 1956
Creator:
Tobak, Murray & Wehrend, William R.
System:
The UNT Digital Library
A Limited Correlation of Atmospheric Sounding Data and Turbulence Experienced by Rocket-Powered Models
Note presenting an analysis and comparison of atmospheric turbulence as experienced by rocket-powered models and temperature lapse-rate data obtained from rawinsonde soundings in 38 cases by using an assumed temperature lapse-rate stability boundary as a basis for comparison. A limited correlation has been obtained which indicates that atmospheric conditions classified as being unstable will generally be turbulent, but a marginal or stable classification does not necessarily indicate smooth air.
Date:
April 1957
Creator:
Mason, Homer P. & Gardner, William N.
System:
The UNT Digital Library
Theoretical analysis of the motions of an aircraft stabilized in roll by a displacement-response, flicker-type automatic pilot
Report presenting a general analysis that allows the rolling motions of an aircraft using a displacement-response, flicker-type automatic pilot to be determined. The system is not ideal for many stabilization problems due to inherent residual oscillations, but it offers a simple and economical solution in situations in which steady state oscillations are not a problem. Results regarding some general remarks, transient and steady states, stabilization boundaries, amplitude equations, and period equations are provided.
Date:
July 7, 1948
Creator:
Curfman, Howard J., Jr. & Gardner, William N.
System:
The UNT Digital Library
Investigation of Flow Conditions and the Nature of the Wall-Constriction Effect Near and at Choking by Means of the Hydraulic Analogy
Report presenting an investigation of the closed wind-tunnel phenomenon of choking and the wall-constriction effects in the subsonic Mach number range where supersonic Mach numbers appear using the hydraulic analogy. Application of the results to wind tunnel testing, the subsonic choking phenomena, and effects of the walls are described.
Date:
September 1, 1948
Creator:
Matthews, Clarence W. & Wright, Ray H.
System:
The UNT Digital Library
Langley Free-Flight-Tunnel Investigation of the Automatic Lateral Stability Characteristics of a Model Equipped with a Gyro Stabilizing Unit that Provided either Flicker-Type or Hunting Control
Memorandum presenting an investigation to determine the automatic lateral stability characteristics of a model equipped with a gyro stabilizing unit that gave response to bank and yaw. Stable flights were obtained with the flicker-type automatic control, and the amplitude of the oscillations was decreased by adding the attachment which provided hunting control.
Date:
January 11, 1949
Creator:
Schade, Robert O.
System:
The UNT Digital Library
NACA Transonic Wing-Tunnel Test Sections
Memorandum presenting an approximate subsonic theory developed for the solid blockage interference in circular wind tunnels with walls slotted in the direction of flow. The theory indicated the possibility of obtaining zero blockage interference. Tests in a circular slotted tunnel based on the theory confirmed the theoretical predictions.
Date:
October 25, 1948
Creator:
Wright, Ray H. & Ward, Vernon G.
System:
The UNT Digital Library
An Application of the Rocket-Propelled-Model Technique to the Investigation of Low-Lift Buffeting and the Results of Preliminary Tests
"The rocket-propelled-model technique has been applied to the investigation of low-lift buffeting. Results of preliminary tests show that severe buffeting, wing dropping, and normal-force changes occur almost simultaneously near zero lift over a Mach number range near 0.9 on unswept wings 12 percent thick. On unswept wings 7 percent thick, buffeting did not occur; however, mild wing dropping and normal-force changes were experienced" (p. 1).
Date:
September 2, 1952
Creator:
Mason, Homer P. & Gardner, William N.
System:
The UNT Digital Library
The Effects of Camber and Leading-Edge-Flap Deflection on the Pressure Pulsations on Thin Rigid Airfoils at Transonic Speeds
Report discussing an investigation into the effects of camber and leading-edge-flap deflection on the pressure pulsations on thin rigid airfoils at a range of Mach numbers. The ideal camber or flap deflection was found to be dependent on Mach number and normal-force coefficient. The results of this testing, which used a 64A006 airfoil, was compared to previous testing using a 65A006 airfoil.
Date:
October 27, 1952
Creator:
Humphreys, Milton D. & Kent, John D.
System:
The UNT Digital Library
Low-Lift Buffet Characteristics Obtained From Flight Tests of Unswept Thin Intersecting Surfaces and of Thick 35 Degree Sweptback Surfaces
Report presenting testing of two rocket-propelled research models to determine the effect of the intersection of thin aerodynamic surfaces and the effect of moderate sweepback of thick aerodynamic surfaces on low-lift buffeting. Results regarding trim changes and drag are also provided. It was discovered that low-lift buffeting may be induced at high subsonic speeds by interference due to the intersection of thin aerodynamic surfaces.
Date:
January 16, 1953
Creator:
Mason, Homer P.
System:
The UNT Digital Library
Supplementary Bibliography of NACA Reports Related to Instrumentation and Research Techniques
Memorandum listing NACA reports related to a variety of research topics, including instruments, research equipment, and research techniques.
Date:
June 19, 1952
Creator:
The Division of Research Information
System:
The UNT Digital Library
Method of Estimating the Stick-Fixed Longitudinal Stability of Wing-Fuselage Configurations Having Unswept or Swept Wings
Memorandum presenting a method for calculating the stick-fixed longitudinal stability of a wing-fuselage configuration at subcritical Mach numbers. The method applies to unswept- and swept-wing configurations. The stability parameters estimated by the method show reasonable agreement with the experimental values for the 23 configurations used in the comparison.
Date:
January 22, 1952
Creator:
McLaughlin, Milton D.
System:
The UNT Digital Library
Summary of Results Obtained by Transonic-Bump Method on Effects of Plan Form and Thickness on Lift and Drag Characteristics of Wings at Transonic Speeds
Memorandum presenting a summary of the effects of plan form and thickness on the lift and drag characteristics of wings at transonic speeds. The data was obtained during a transonic research program conducted in the high-speed 7- by 10-foot tunnel by the transonic-bump method. Results regarding lift, drag at zero lift, and drag due to lift are provided.
Date:
November 30, 1951
Creator:
Polhamus, Edward C.
System:
The UNT Digital Library
Cooperative Investigation of Relationship Between Static and Fatigue Properties of Heat-Resistant Alloys at Elevated Temperatures
Memorandum presenting a study of the relationship between the static and dynamic properties of heat-resistant alloys at high temperatures. An auxiliary objective is to provide a better basis for evaluating the results from the various types of fatigue machines.
Date:
March 7, 1951
Creator:
NACA Subcommittee on Heat-Resisting Materials
System:
The UNT Digital Library
Effects of External Store Mounting on the Buffet, Trim, and Drag Characteristics of Rocket-Powered Fuselage and Store Combinations Between Mach Numbers of 0.7 and 1.4
Memorandum presenting an investigation made of the effects of store mounting on the buffet, trim, and drag characteristics of fuselage-mounted external stores between Mach numbers of 0.7 and 1.4 by the use of the rocket-propelled-model technique. Results of the tests are presented in the incremental accelerations in the stores due to buffeting, trim normal- and side-force coefficients, tail helix angles, and drag coefficients plotted against Mach number.
Date:
December 10, 1953
Creator:
Mason, Homer P.
System:
The UNT Digital Library
Theoretical study of the tunnel-boundary lift interference due to slotted walls in the presence of the trailing-vortex system of a lifting model
Report presenting some equations that give the interference on the trailing-vortex system of a uniformly loaded finite-span wing in a circular tunnel containing partly open and partly closed walls, with special reference to symmetrical arrangements of the open and closed portions. Methods are given for extending the equations to include tunnel shapes other than circular.
Date:
April 7, 1953
Creator:
Matthews, Clarence W.
System:
The UNT Digital Library
Some Effects of Leading-Edge Roughness on the Aileron Effectiveness and Drag of a Thin Rectangular Wing Employing a Full-Span Plain Aileron at Mach Numbers From 0.6 to 1.5
Report presenting an investigation of the effects of adding leading-edge roughness to the surfaces of an unswept, untapered, 6-percent-thick, circular-arc-airfoil wing equipped with a full-span, 0.2-chord, plain, trailing-edge aileron. Results regarding the rolling-effectiveness data, addition of roughness on a wing, and variation of drag coefficient are provided.
Date:
November 4, 1953
Creator:
English, Roland D.
System:
The UNT Digital Library
Some Effects of Aeroelasticity at Mach Numbers From 0.7 to 1.6 on the Rolling Effectiveness of Thin Flat-Plate Delta Wings Having 45 Degree Swept Leading Edges and Full-Span Constant-Chord Ailerons
From Summary: "The aeroelastic effects on wing-aileron rolling effectiveness and drag of thin flat-plate delta wings with 45 degree swept leading edge and plain constant-chord ailerons have been investigated. This investigation has been carried out over a Mach number range of 0.7 to 1.6 by means of rocket-propelled test vehicles in free flight. The results show a near-linear decrease in lateral control effectiveness with a decrease in the wing torsional stiffness. An aileron-effectiveness reversal was experienced with the more flexible delta-wing models."
Date:
February 19, 1952
Creator:
Marley, Edward T. & English, Roland D.
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.
System:
The UNT Digital Library
Flight Measurements of Lift and Drag for the Bell X-1 Research Airplane Having a 10-Percent-Thick Wing
Report presenting drag coefficients during power-off transonic flight for the Bell X-1 airplane with a 10-percent-thick wing over a range of Mach numbers and pressure altitudes. The data was compared to an X-1 with an 8-percent-thick wing and a wind tunnel test with a 10-percent-thick wing. Information about necessary angle of attack, drag-rise Mach number, maximum lift-drag ratio, and drag coefficient at zero lift is provided.
Date:
September 3, 1953
Creator:
Saltzman, Edwin J.
System:
The UNT Digital Library