National Advisory Committee for Aeronautics (NACA) - 206 Matching Results

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Stability and Control Characteristics at Low Speed of a Modified 1/10-Scale Model of the MX-1554A Design

Description: Report discussing the low-speed stability and control characteristics of a modified model of the MX-1554A with a triangular wing and triangular stabilizing surfaces, which are designed to give more satisfactory stability and control than previous versions. Other modifications included an increase in slotted-flap span, redesigned tip aileron, fuselage tail cone, and speed brakes. Results provided include the effect of flow-control devices, tank and pylon location, a ground board, rotary stabilit… more
Date: November 9, 1953
Creator: Lockwood, Vernard E. & Solomon, Martin
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Nonuniform Burnup and Poisoning Effects in a Reactor and Validity of Uniform Approximation

Description: Memorandum presenting the application of the nuclear-reactor simulator to an investigation of the validity of the customary assumption of uniform distributions of fuel burnup and fission-product poisoning in a reactor core. The two-group calculation results show the effects of the approximation on the reactivity, power distribution, and xenon-135 distribution for a specific power reactor in which the initial power density varied by a factor of approximately 4 over the core volume.
Date: March 9, 1953
Creator: Spooner, Robert B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Full-Scale Wind-Tunnel Tests of a North American FJ-3 Airplane with a Spoiler-Slot-Deflector Lateral Control System

Description: Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.
Date: April 9, 1956
Creator: Scallion, William I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analytical Studies of the Response to Longitudinal Control of Three Airplane Configurations in Landing Approaches

Description: Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.
Date: April 9, 1953
Creator: Bihrle, William, Jr. & Stone, Ralph W., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane

Description: Report presenting an investigation in the free-spinning tunnel on a model of the Republic F-105B airplane to determine the spin and recovery characteristics. Results indicated that even with perfect control technique, full movement of the rudder against the spin and of ailerons with the spin is not adequate to ensure satisfactory recovery; extensions of both canard surfaces should accompany the control technique. Results regarding ideal parachute design are also provided.
Date: October 9, 1957
Creator: Bowman, James S., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Electric Thrust Meter Suitable for Flight Investigation of Propellers

Description: A lightweight instrument that utilizes resistance-wire electric strain gases to measure propeller-shaft thrust has been developed. A wind-tunnel investigation on a propeller installed, on a single-engine pursuit airplane showed that the instrument gave a reliable indication of propeller-shaft thrust to an accuracy of +/-2 percent within its calibrated range. No attempt was made to determine the relation of indicated shaft thrust to net propeller thrust.
Date: May 9, 1949
Creator: Perkins, Porter J., Jr. & Millenson, Morton B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Low-Temperature Nuclear-Powered Ramjet Missile for High Altitudes

Description: From Summary: "The reactor operating conditions were varied to enable selection of values giving a good compromise between low uranium investment and loss gross weight at each altitude and flight Mach number considered. The corresponding values of reactor and missile operating conditions are presented in the report."
Date: November 9, 1955
Creator: Rom, F. E. & Sams, E. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Investigations of Air-Cooled Turbine Rotors for Turbojet Engines 1: Experimental Disk Temperature Distribution in Modified J33 Split-Disk Rotor at Speeds up to 6000 RPM

Description: "An experimental investigation is being conducted at the Lewis laboratory to establish general principles for the design of noncritical turbine rotor configurations. This investigation includes evaluation of cooling effectiveness, structural stability, cooling-air flow distribution characteristics, and methods of supplying cooling air to the turbine rotor blades. Prior to design of a noncritical rotor, a standard turbine rotor of a commerical turbojet engine was split in the plane of rotation a… more
Date: January 9, 1952
Creator: Schramm, Wilson B. & Ziemer, Robert R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Hovering and Transition Flight Tests of a 1/5-Scale Model of the Ryan X-13 VTOL Airplane

Description: Report discussing an investigation of the dynamic stability and control characteristics of a model of the Ryan X-13 jet VTOL airplane in hovering and transition flight. Flight control was smooth and easy without the gyroscopic effects of the engine represented, but adding a simulation of the gyroscopic effects caused the plane to become uncontrollable in hovering flight without artificial stabilization. The transition was found to be easy to perform with and without gyroscopic effects, but the … more
Date: September 9, 1958
Creator: Smith, Charles C., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Preliminary Investigation of Reflections of Oblique Waves from a Porous Wall

Description: "A porous wall was used in an attempt to eliminate reflections of oblique waves from a tunnel wall. Calculations were made of the required resistance characteristics of a wall in order that the flow through the wall, due to the pressure difference across a shock wave, would equal the component normal to the wall of the flow behind the shock wave. The resistance characteristic of a sintered bronze wall was measured and the reflections of waves impinging on the wall were observed at a Mach number… more
Date: November 9, 1950
Creator: Davis, Don D., Jr. & Wood, George P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Supplementary Free-Spinning-Tunnel Investigation of a 1/20-Scale Model of the McDonnell F2H-3 Airplane With External Stores Installed

Description: Memorandum presenting a supplementary investigation in the 20-foot free-spinning tunnel to determine the effect of external stores and lateral center-of-gravity displacement on the spin and spin-recovery characteristics of a scale model of the McDonnell F2H-3 airplane. Results regarding wing-tip tanks and experimental aerodynamic shapes are provided.
Date: June 9, 1952
Creator: Wilson, Jack H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Low-Pressure Performance of a Tubular Combustor With Gaseous Hydrogen

Description: Memorandum presenting an investigation to determine the combustion performance characteristics of gaseous hydrogen fuel in a single tubular turbojet combustor. The combustor was operated over a range of inlet-air pressures from 3.3 to 14.3 inches of mercury absolute. Results regarding stability limits and combustion efficiency are provided.
Date: May 9, 1955
Creator: Jonash, Edmund R.; Smith, Arthur L. & Hlavin, Vincent F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of the Landing on Water of a Model of a High-Speed Airplane - Langley Tank Model 229

Description: Memorandum presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a scale model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The test is part of an investigation of the feasibility of the operation from water of high-speed airplanes. The results of the test form a basis for evaluating the improvement in hydrodynamic characteristics.
Date: December 9, 1947
Creator: King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Additional Abstracts Pertaining to Seaplanes

Description: "About 500 additional references pertaining to hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings:GENERAL INFORMATION, HYDROSTATICS, HYDRODYNAMICS, AERODYNAMICS, OPERATION, and RESEARCH. The compilation is an extension of NACA RM No. L6I13, entitled "Abstracts Pertaining to Seaplanes," by Jerold M. Bidwell and Douglas A. King. An author index and a subject index are included" (p. 1).
Date: March 9, 1948
Creator: Bidwell, Jerold M. & King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Static tests of a shrouded and an unshrouded propeller

Description: Report presenting outdoor static testing made on two high-solidity propellers of different design, one shrouded and the other unshrouded. Three shrouds were tested to determine the effects of shroud length and exit area. Results regarding the action of shroud, results and comparison of propellers, and comparison with theory are provided.
Date: February 9, 1948
Creator: Platt, Robert J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A summary and analysis of data on dive-recovery flaps

Description: From Summary: "The results of numerous unrelated tests of dive-recovery flaps are collected in this report and presented in a form suitable for use in the preliminary design of dive-recovery flap installations. Since the data were obtained for airplane models of quite widely varying configurations, and are limited largely to a Mach number of 0.80, it is recommended that each new installation be carefully flight-tested before final approval. A flight-test procedure is outlined which will insure … more
Date: September 9, 1947
Creator: Boddy, Lee E. & Williams, Walter C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Tests of the landing on water of a model of a high-speed airplane - Langley tank model 229

Description: Report presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a dynamic model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The model skipped out of the water and experienced maximum normal accelerations up to 7.4g and maximum longitudinal accelerations up to 4.5g. Results of landing the basic model and landing the modified model that has a slightly different fuselage are provided.
Date: December 9, 1947
Creator: King, Douglas A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude cooling investigation of the R-2800-21 engine in the P-47g airplane 3: individual-cylinder temperature reduction by means of intake-pipe throttle and by coolant injection

Description: "Flight tests were conducted on a R-2800-21 engine in the P-47G airplane to determine the effect on the wall temperatures of cylinder 10 of throttling the charge in the intake pipe and of injecting a water-ethanol coolant into the intake pipe. Cylinder 10 was chosen for this investigation because it runs abnormally hot (head temperatures of the order of 45 F higher than those of the next hottest cylinder) at the medium and high-power conditions. Tests with interchanged cylinders showed that the… more
Date: October 9, 1946
Creator: Bell, E. Barton; Valerino, Michael F. & Manganiello, Eugene J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aeronautical study of a wing-fuselage combination employing a wing swept back 63 degrees: Characteristics at supersonic speeds of a model with the wing twisted and cambered for uniform load

Description: Report presenting the lift, drag, and pitching-moment characteristics of a wing-fuselage combination employing a wing with the leading edge swept back 63 degrees and cambered and twisted for a uniform load at a lift coefficient of 0.25 and Mach number 1.53. The experimental results are compared to those from other investigations. A maximum lift-drag ratio of 8.9 and a minimum drag coefficient of 0.0145 was obtained.
Date: January 9, 1950
Creator: Hall, Charles F. & Heitmeyer, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Further Investigation of a Gas Turbine with National Bureau of Standards Body 4811C Ceramic Rotor Blades

Description: Memorandum presenting an investigation of 4811C ceramic blades and the problems involved in the adaption of ceramic materials to stressed turbine components. Results regarding spin tests and rotating heat-shock runs are provided.
Date: March 9, 1950
Creator: Freche, John C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation at Low Speed of a Wing Swept-Back 63 Degrees and Twisted and Cambered for a Uniform Load at a Lift Coefficient of 0.5

Description: Report discusses the results of testing to determine the low-speed longitudinal stability characteristics and spanwise distribution of load of a wing model with the leading edge swept back 63 degrees, an aspect ratio of 3.5, and a large amount of twist and camber. The results are compared to tests of a model of an untwisted and uncambered wing of identical plan form. Measurements of force, pressure-distribution, and comparison of theoretical and experimental span loading are described.
Date: May 9, 1950
Creator: Weiberg, James A. & Carel, Hubert C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of the Effects of Wing Aspect Ratio and Tail Location on Static Longitudinal Stability Below the Mach Number of Lift Divergence

Description: "An analysis is presented of the influence of wing aspect ratio and tail location on the effects of compressibility upon static longitudinal stability. The investigation showed that the use of reduced wing aspect ratios or short tail lengths leads to serious reductions in high-speed stability and the possibility of high-speed instability" (p. 1).
Date: January 9, 1948
Creator: Axelson, John A. & Crown, J. Conrad
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Investigation of a Wing-Fuselage Combination With External Stores

Description: Report presenting an investigation of a basic wing-fuselage combination with several types of external-store installations meant to delay the advent of airplane buffet caused by external stores. Modifications for airplane design in order to minimize the effect of drag are provided. Some of the arrangements tested included the tandem-mounted arrangement, flush-mounted arrangement, store with a fan-shaped tail, and auxiliary airfoil arrangement.
Date: July 9, 1948
Creator: Silvers, H. Norman & Spreemann, Kenneth P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Flight Tests to Determine the Effect of Airfoil Section Profile and Thickness Ratio on the Zero-Lift Drag of Low-Aspect-Ratio Wings at Supersonic Speeds

Description: Report discussing flight tests of airplane-like models to determine the effect of airfoil section profile and thickness ratio on the zero-lift drag of low-aspect-ratio wings at supersonic speeds. Five rectangular wings with the same aspect ratio and a variety of airfoil thicknesses were tested to determine the effect of thickness ratio.
Date: February 9, 1948
Creator: Katz, Ellis
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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