National Advisory Committee for Aeronautics (NACA) - 13,786 Matching Results

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An Analog Study of the Influence of Internal Modifications to a Wing Leading Edge on Its Transient Temperature Rise During Highspeed Flight

Description: Memorandum presenting an investigation made with an electrical heat-flow analog to determine the effect of internal modifications to a wing leading edge on the surface-temperature rise and temperature distribution for conditions of transient aerodynamic heating at high supersonic speeds. Results regarding the leading-edge temperature rise, influence of conduction on leading-edge temperature for skins of uniform thickness, and surface-temperature distribution are provided.
Date: March 17, 1958
Creator: Neel, Carr B.
Partner: UNT Libraries Government Documents Department
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Section Thrust Coefficients for a Full-Scale, Three-Blade, Supersonic-Type Propeller Operating at Low and Negative Blade Angles

Description: "An investigation has been conducted at the Langley 16-foot transonic tunnel at Mach number of about 0.14 (110 miles per hour) to determine the aerodynamic loading on a three-blade, 9.75-foot-diameter, supersonic-type propeller when used as a brake. The results of the slipstream survey are presented without analysis in tabular form for blade-angle settings at the 0.75 radial station from 16.4 degrees to -13.6 degrees in approximately 5 degree increments" (p. 1).
Date: March 17, 1958
Creator: Salters, Leland B., Jr. & Lewis, Martha C.
Partner: UNT Libraries Government Documents Department
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Two-dimensional cascade investigation at Mach numbers up to 1.0 of NACA 65-series blade sections at conditions typical of compressor tips

Description: Report presenting a two-dimensional high-speed cascade investigation of thin low-cambered NACA 65-series blade shapes at operating conditions typical of compressor tip sections. Testing occurred with porous walls and solid walls. Results regarding the variation of turning angle with Mach number, variation of turning angle with angle of attack, momentum loss, and schileren photographs are provided.
Date: March 17, 1958
Creator: Dunavant, James C. & Emery, James C.
Partner: UNT Libraries Government Documents Department
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Aerodynamic and inlet-flow-field characteristics at a free-stream Mach number of 3.0 for airplanes with circular fuselage cross sections and for two engine locations

Description: Report presenting an experimental investigation of several airplane configurations at Mach 3.0 in a continuous flow tunnel. The configurations had circular fuselage cross sections and a sweptback wing and either two nacelles or two side inlets.
Date: March 18, 1958
Creator: Dryer, Murray & Luidens, Roger W.
Partner: UNT Libraries Government Documents Department
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Analysis of two-stage counterrotating turbine efficiencies in terms of work and speed requirements

Description: From Introduction: "This report represents an extension of the material presented in reference 4 to the case of the counterrotating turbine where the inter-stage stator is omitted and the second-stage rotor blade velocity is in the direction opposite to that of the first-stage rotor."
Date: March 18, 1958
Creator: Wintucky, William T. & Stewart, Warner L.
Partner: UNT Libraries Government Documents Department
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Calculation of Flutter Characteristics for Finite-Span Swept or Unswept Wings at Subsonic and Supersonic Speeds by a Modified Strip Analysis

Description: Report presenting a method for calculating flutter characteristics of finite-span swept or unswept wings at subsonic and supersonic speeds. Flutter characteristics were calculated using this method for 12 wings of varying sweep angle, aspect ratio, taper ratio, and center-of-gravity position at a range of Mach numbers.
Date: March 18, 1958
Creator: Yates, E. Carson, Jr.
Partner: UNT Libraries Government Documents Department
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Investigation of Two Bluff Shapes in Axial Free Flight Over a Mach Number Range From 0.35 and 2.15

Description: Memorandum presenting a fineness-ratio-2.71 right circular cylinder and a fineness-ratio-4.0 circular cylinder with a rounded nose and a flared afterbody tested in free flight over a range of Mach and Reynolds numbers. Time histories, cross plots of force coefficients, rolling velocity, and longitudinal-force coefficient are presented for both cylinders.
Date: March 18, 1958
Creator: Coltrane, Lucille C.
Partner: UNT Libraries Government Documents Department
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Investigation of Two Bluff Shapes in Axial Free Flight Over a Mach Number Range From 0.35 to 2.15

Description: Report presenting testing of a fineness-ratio-2.71 right circular cylinder and a fineness-ratio-4.0 circular cylinder with a rounded nose and flared afterbody over a range of Mach and Reynolds numbers. Time histories, cross plots of force coefficients, rolling velocity, and longitudinal-force coefficient are provided for the two cylinders.
Date: March 18, 1958
Creator: Coltrane, Lucille C.
Partner: UNT Libraries Government Documents Department
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NACA Conference on High-Speed Aerodynamics

Description: This document contains reproductions of technical papers presented by staff members of the NACA Laboratories at the NACA Conference on High-Speed Aerodynamics held at the Ames Aeronautical Laboratory of the NACA, March 18, 19, and 20, 1958. The primary purpose of this conference was to convey to the military services and their contractors the results of recent research results and to provide those attending an opportunity to discuss the results. The papers in this document were prepared for pre… more
Date: 1958-03-18/1958-03-20
Partner: UNT Libraries Government Documents Department
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NACA Conference on High-Speed Aerodynamics: A Compilation of Papers Presented

Description: A reproduction of the technical papers presented by staff members of the NACA Laboratories at the NACA Conference on High-Speed Aerodynamics at the Ames Aeronautical Laboratory during March 18-20, 1958. The primary purpose of the conference was to convey to military services and contractors the results of recent research and to provide an opportunity to discuss the results.
Date: 1958-03-18/1958-03-20
Partner: UNT Libraries Government Documents Department
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Preliminary investigation of land-water operation with a 1/10-scale model of a jet airplane equipped with hydro-skis

Description: Report presenting an investigation of a scale model of a jet airplane equipped with hydro-skis to study the transition between ramp and water during take-off and landing operations. Hydro-skis were installed so that they utilized the existing landing-gear shock absorbers. Results regarding the twin-ski configuration and tri-ski configuration are provided.
Date: March 18, 1958
Creator: Thompson, William C.
Partner: UNT Libraries Government Documents Department
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Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01

Description: From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."
Date: March 24, 1958
Creator: Spearman, M. Leroy & Robinson, Ross B.
Partner: UNT Libraries Government Documents Department
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The Effects of Body Vortices and the Wing Shock-Expansion Field on the Pitch-Up Characteristics of Supersonic Airplanes

Description: Memorandum presenting a technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement the calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.
Date: March 24, 1958
Creator: Nielsen, Jack N.
Partner: UNT Libraries Government Documents Department
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The Effects of Body Vortices and the Wing Shock-Expansion Field on the Pitch-Up Characteristics of Supersonic Airplanes

Description: Memorandum describing a calculative technique for predicting the influence of body vortices and the wing shock-expansion field on the pitch-up characteristics of supersonic airplanes to supplement calculative methods for wing vortices which are well known. The method is applied to the prediction of the pitch-up characteristics of four airplanes with high tails, of which one serves as a calculative example.
Date: March 24, 1958
Creator: Nielsen, Jack N.
Partner: UNT Libraries Government Documents Department
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Feasibility of Nose-Cone Cooling by the Upstream Ejection of Solid Coolants at the Stagnation Point

Description: Report presenting an investigation in a chemical jet at a stagnation temperature of 4,000 degrees Fahrenheit at a Mach number of 2.8 to determine the feasibility of cooling models by the ejection of a solid coolant at the stagnation point. A series of conical models were tested with glass, Lucite, nylon, Teflon, and Texolite rods as coolants. Results regarding the cooling properties of each of the materials are provided, and all materials performed adequately with the exception of Teflon.
Date: March 24, 1958
Creator: Kinard, William H.
Partner: UNT Libraries Government Documents Department
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Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers From 1.90 to 3.07

Description: Report presenting an investigation of a rocket-powered model to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Information about heat-transfer measurements, average heat transfer on cylindrical portions of leading edges, and local heat transfer is provided.
Date: March 24, 1958
Creator: O'Neal, Robert L. & Bond, Aleck C.
Partner: UNT Libraries Government Documents Department
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Preliminary Study of Airplane Configurations Having Tail Surfaces Outboard of the Wing Tips

Description: Report presenting some of the concepts and applications underlying the basic arrangement of airplane configurations with tail surfaces outboard of the wing tips. The arrangement was created to be consistent with good supersonic performance characteristics and to avoid some of the stability and trim-drag problems seen with other supersonic configurations. Results regarding stability and control characteristics, lift and drag characteristics, and an analytical study of effects of some design vari… more
Date: March 24, 1958
Creator: Sleeman, William C., Jr.
Partner: UNT Libraries Government Documents Department
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Wind-Tunnel Data on the Longitudinal and Lateral-Directional Rotary Derivatives of a Straight-Wing, Research Airplane Configuration at Mach Numbers From 2.5 to 3.5

Description: Memorandum presenting the results of wind-tunnel oscillation tests to measure the rotary derivatives of a research airplane configuration at supersonic speeds. Measurements were made of the damping in yaw, pitch, and roll, the static longitudinal and directional stability derivatives, the effective-dihedral derivative, the rolling moment due to yawing, and the yawing moment due to rolling. The configuration was found to be statistically stable throughout the Mach number range, although its stab… more
Date: March 25, 1958
Creator: Beam, Benjamin H. & Endicott, Kenneth C.
Partner: UNT Libraries Government Documents Department
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Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines

Description: From Introduction: " Considerable analytical and experimental research has been done to find means of reducing the noise levels of the turbojet transports. Noise levels can be decreased by engine redesign to reduce the jet-exit velocity (ref. 1), proper flight-climb techniques (ref. 2), and the use of noise-suppression exhaust nozzles (refs. 3 to 5). The present report is concerned with the last method."
Date: April 1958
Creator: Ciepluch, Carl C.; North, Warren J.; Coles, Willard D. & Antl, Robert J.
Partner: UNT Libraries Government Documents Department
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Analysis of harmonic forces produced at hub by imbalances in helicopter rotor blades

Description: From Introduction: "First, an analysis of loads transmitted to the hub by balanced blades will be given. In the second section, the additional loads transmitted to the hub in a direction normal to the plane of rotation of the blades by imbalances in a rotor are derived. In the entire analysis, the results are given in terms of the forces transmitted to the hub by a single rotating helicopter blade in flight, and these are regarded as known or given."
Date: April 1958
Creator: Morduchow, M. & Muzyka, A.
Partner: UNT Libraries Government Documents Department
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Analysis of Turbulent Flow and Heat Transfer on a Flat Plate at High Mach Numbers With Variable Fluid Properties

Description: From Introduction: "In the turbulent case, however, the results of the various analyses disagree markedly because of the different assumptions made by various authors. These analyses are reviewed in references 1 to 3. The analysis is extended to flow and heat transfer in a boundary layer at high Mach numbers in this paper. (Some preliminary results were presented in ref. 11.)"
Date: April 1958
Creator: Deissler, R. G. & Loeffler, A. L., Jr.
Partner: UNT Libraries Government Documents Department
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An Approximate Method for Design or Analysis of Two-Dimensional Subsonic-Flow Passages

Description: Note presenting a method for the design and analysis of two-dimensional subsonic-flow passages with isentropic nonviscous flow. The method is based on the relation between the pressure change across a stream tube and the centrifugal force resulting from the curvature of the flow. In an example, the method was applied to the design of an expanding elbow at each of two Mach numbers.
Date: April 1958
Creator: Valentine, E. Floyd
Partner: UNT Libraries Government Documents Department
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Central Automatic Data Processing System

Description: A series of papers describing a system that will automatically record as many as 300 pressures, 200 voltages, and 24 frequencies in as little as 30 seconds to an accuracy of 0.15 percent or better of full-scale range. The information is able to be used in any high-speed, general-purpose digital computer. The computer will accept the encoded data produced by the recording system and automatically calibrates it, takes averages, forms ratios, and does terminal calculations such as mass flow, momen… more
Date: April 1958
Creator: Staff of the Lewis Laboratory
Partner: UNT Libraries Government Documents Department
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