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NACA Technical Notes
125
NACA Wartime Reports
105
NACA Research Memorandums
84
Atomic Energy Commission Reports
41
NACA Advanced Restricted Reports
37
NACA Memorandum Reports
31
NACA Advanced Confidential Reports
29
NACA Technical Memorandums
27
NACA Technical Reports
19
United States Bureau of Mines Reports
11
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525 Matching Results
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Investigation of Effects of Various Camouflage Paints and Painting Procedures on the Drag Characteristics of an NACA 65(Sub 421)-420, a = 1.0 Airfoil Section
Bulletin presenting an investigation of the effects of various camouflage paints and painting procedures on the drag characteristics of a 60-inch-chord low-drag airfoil in the NACA two-dimensional low-turbulence pressure tunnel.
Date:
July 1944
Creator:
Braslow, Albert L.
System:
The UNT Digital Library
Experimental Investigation of a New Type of Low-Drag Wing-Nacelle Combination
Report discusses the results of an experimental investigation of two low-drag wing-nacelle units suitable for use with pusher propellers. The benefits of adding a nacelle to the wing are detailed.
Date:
July 1942
Creator:
Allen, H. Julian & Frick, Charles W., Jr.
System:
The UNT Digital Library
Experimental and Theoretical Studies of Area Suction for the Control of the Laminar Boundary Layer on a Porous Bronze NACA 64A010 Airfoil
Note presenting a low-turbulence wind tunnel investigation of an NACA 64A010 airfoil with a porous surface of sintered bronze to determine the reduction in section drag coefficient that might be obtained at large Reynolds numbers by use of suction to produce continuous inflow through the surface of the model. Results regarding the uncompartmented model, compartmented model, observations on stability of laminar boundary layer, and theoretical calculations are provided.
Date:
July 1949
Creator:
Burrows, Dale L.; Braslow, Albert L. & Terervin, Neal
System:
The UNT Digital Library
Effects of sweepback on boundary layer and separation
"Following the law of stress adopted in the Navier-Stokes equations, the configuration of the viscous flow in planes at right angles to the axis of an infinite cylinder is found to be independent of the axial motion of the cylinder. In the limiting case of a yawed or swept wing of very high aspect ratio, certain boundary-layer and separation phenomena are thus determined independently by the crosswise component of velocity" (p. 1).
Date:
July 1947
Creator:
Jones, Robert T.
System:
The UNT Digital Library
Tank tests to determine the effect of varying design parameters of planing-tail hulls 2: effect of varying depth of step, angle of after- body keel, length of afterbody chine, and gross load
From Summary: "The second part of a series of tests made in Langley tank no. 2 to determine the effect of varying design parameters of planing-tail hulls is presented. Results are given to show the effects on resistance characteristics of varying angle of afterbody keel, depth of step, and length of afterbody chine. The effect of varying the gross load is shown for one configuration. The resistance characteristics of planing-tail hulls are compared with those of a conventional flying-boat hull. The forces on the forebody and afterbody of one configuration are compared with the forces on a conventional hull."
Date:
July 1946
Creator:
Dawson, John R.; McKann, Robert & Hay, Elizabeth S.
System:
The UNT Digital Library
Methods of analyzing wind-tunnel data for dynamic flight conditions
The effects of power on the stability and the control characteristics of an airplane are discussed and methods of analysis are given for evaluating certain dynamic characteristics of the airplane that are not directly discernible from wind tunnel tests alone. Data are presented to show how the characteristics of a model tested in a wind tunnel are affected by power. The response of an airplane to a rolling and a yawing disturbance is discussed, particularly in regard to changes in wing dihedral and fin area. Solutions of the lateral equations of motion are given in a form suitable for direct computations. An approximate formula is developed that permits the rapid estimation of the accelerations produced during pull-up maneuvers involving abrupt elevator deflections.
Date:
July 22, 1941
Creator:
Donlan, C. J. & Recant, I. G.
System:
The UNT Digital Library
Shear Buckling of Infinitely Long Simply Supported Metalite Type Sandwich Plates
"A theoretical solution is obtained for the problem of the shear buckling of infinitely long simply supported elastic Metalite type sandwich plates. An approximate correction is suggested for the determination of the critical shear stresses of plates that buckle in the plastic range" (p. 1).
Date:
July 1949
Creator:
Seide, Paul
System:
The UNT Digital Library
Physical Properties at Elevated Temperature of Seven Hot-Pressed Ceramics
Report presenting an investigation of seven hot-pressed ceramics for possible gas-turbine application. The properties, short-time tensile strength, thermal-shock resistance, coefficient of liner expansion, and density were determined. The ceramics tested were magnesium oxide, titanium carbide, zirconium carbide, boron carbide, silicon carbide with boron carbide, zircon, and zirconia with lime.
Date:
July 1949
Creator:
Gangler, James J.; Robards, Chester F. & McNutt, James E.
System:
The UNT Digital Library
Approximate Method for Predicting Form and Location of Detached Shock Waves Ahead of Plane or Axially Symmetric Bodies
Note presenting an approximate method developed to predict the location of detached shock waves ahead of two-dimensional and axially symmetric bodies. The method is based on the continuity relation, which is applied to the air that passes the sonic line.
Date:
July 1949
Creator:
Moeckel, W. E.
System:
The UNT Digital Library
Two-dimensional investigation of five related NACA airfoil sections designed for rotating-wing aircraft
Report presenting testing of five NACA airfoil sections intended for use in rotor blades in the two-dimensional low-turbulence tunnel. The airfoils varied in thickness and theoretical design lit coefficients. Results regarding pitching moment, lift, drag, and helicopter performance calculations are provided.
Date:
July 1949
Creator:
Schaefer, Raymond F.; Loftin, Laurence K., Jr. & Horton, Elmer A.
System:
The UNT Digital Library
Experimental Investigation of Moving Pressure Disturbances and Shock Waves and Correlation with One-Dimensional Unsteady-Flow Theory
Note presenting experimental pressure-time measurements along with schileren photographs of the unsteady-flow phenomena initiated in constant-cross-sectional-area passages. The methods of calculation of the flow phenomena are based on the assumptions of one-dimensional, nonviscous, unsteady flow.
Date:
July 1949
Creator:
Huber, Paul W.; Fitton, Cliff E., Jr. & Delpino, F.
System:
The UNT Digital Library
Characteristics of thin triangular wings with constant-chord partial-span control surfaces at supersonic speeds
Report presenting a theoretical analysis of the characteristics of constant-chord partial-span control surfaces on thin triangular wings at supersonic speeds by use of methods based on the linearized theory for supersonic flow. Two cases were treated with the analysis. Results regarding lift coefficient, rolling-moment coefficient, and hinge-moment coefficient due to flap deflection, hinge-moment coefficient due to angle of attack, and the pitching-moment coefficient due to flap lift.
Date:
July 1948
Creator:
Tucker, Warren A. & Nelson, Robert L.
System:
The UNT Digital Library
Aerodynamic Properties of Slender Wing-Body Combinations at Subsonic, Transonic, and Supersonic Speeds
From Introduction: "In an incomprehensible medium, the mutual interference of a fuselage and wing of high-aspect ratio (to which lifting-line theory is applicable) has been treated by Lennertz, Wiselsberger, Pepper, and Multhopp in reference 1, 2, 3, and 4. It is the purpose of this note to treat the effect of on the aerodynamic loading of the mutual interference between a low-aspect-ratio pointed wing and a fuselage consisting of a slender body of revolution."
Date:
July 1948
Creator:
Spreiter, John R.
System:
The UNT Digital Library
Thermodynamic Charts for Internal-Combustion-Engine Fluids
Note presenting thermodynamic properties of the products of combustion of five different mixtures of air with typical aircraft-engine fuel, which have been calculated from the most reliable thermodynamic data available. The calculations are presented in five charts of internal energy plotted against entropy with values of temperature, specific volume, pressure, and enthalpy indicated corresponding to five different percentages of the fuel-air ratio for perfect combustion.
Date:
July 1949
Creator:
McCann, W. J.
System:
The UNT Digital Library
Propeller-efficiency charts for light airplanes
Report presenting some charts on the reflection of a propeller on the basis of efficiency for application to a light airplane design. Various values of power are covered for several different airspeeds, propeller diameters, and blade numbers.
Date:
July 1947
Creator:
Crigler, John L. & Jaquis, Robert E.
System:
The UNT Digital Library
Investigation of the Validity of an Ideal Theory of Elasto-Plasticity for Wrought Aluminum Alloys
Note presenting an investigation to determine the relation between stresses and plastic strains of wrought aluminum alloys for three types of loading: tension, compression, and torsion. A secondary objective was to identify which assumptions of an ideal theory of elasto-plasticity are invalid for the alloys. Universal stress-strain curves as predicted by the theory were not obtained with wrought aluminum alloys.
Date:
July 1948
Creator:
Thomsen, E. G.; Cornet, I.; Lotze, I. & Dorn, J. E.
System:
The UNT Digital Library
X-Ray Diffraction Investigation of Minor Phases of 20 High-Temperature Alloys
Report presenting the use of x-ray diffraction methods to identify the minor phases present in 20 high-temperature alloys in current use. The minor phases were noted in seven of the 20 alloys. A description of the relation of the alloys to one another and their chemical properties are provided.
Date:
July 1948
Creator:
Rosenbaum, B. M.
System:
The UNT Digital Library
Characteristics of Thin Triangular Wings With Constant-Chord Full-Span Control Surfaces at Supersonic Speeds
Note presenting a theoretical analysis of the characteristics of constant-chord full-span control surfaces on thin triangular wings at supersonic speeds by use of methods based on the linearized equation for supersonic flow. Expressions were found for the lift effectiveness, pitching-moment coefficient, hinge-moment coefficient due to control deflection, and hinge-moment coefficient due to angle of attack.
Date:
July 1948
Creator:
Tucker, Warren A.
System:
The UNT Digital Library
Sound-Level Measurements of a Light Airplane Modified to Reduce Noise Reaching the Ground
"An army liaison-type airplane, representative of personal airplanes in the 150 to 200 horsepower class, has been modified to reduce propeller and engine noise according to known principles of airplane-noise reduction. Noise-level measurements demonstrate that, with reference to an observer on the ground, a noisy airplane of this class can be made quiet - perhaps more quiet than necessary. In order to avoid extreme and unnecessary modifications, acceptable noise levels must be determined" (p. 1).
Date:
July 1948
Creator:
Vogeley, A. W.
System:
The UNT Digital Library
Tank tests of a 1/10-size model of a hypothetical flying boat with a hull length-beam ratio of 9.0
Report presenting an investigation of the hydrodynamic characteristics of a powered dynamic model of a hypothetical flying boat with a hull length-beam ratio of 9.0 in Langley tank no. 1. Results regarding trim limits of stability, center-of-gravity limits for stable take-off, landing stability, resistance, and spray characteristics are provided.
Date:
July 1948
Creator:
Haar, Marvin I.
System:
The UNT Digital Library
Investigation of Axial-Flow Fan and Compressor Rotors Designed for Three-Dimensional Flow
Report presenting an investigation to determine whether three-dimensional flows may be efficiently utilized in axial-flow fan and compressor rotors. Two rotors, one with approximately uniform and one with solid-body downstream tangential-velocity distributions, were designed and tested at the designated blade angle. Results regarding the overall fan characteristics, surveys, and comparisons to theory are provided.
Date:
July 1948
Creator:
Kahane, A.
System:
The UNT Digital Library
Effect of Screens in Wide-Angle Diffusers
Note presenting an experimental investigation at low airspeeds of the filling effect observed when a screen or similar resistance is placed across a diffuser. The filling effect is found to be real in that screens can prevent separation or restore separated flow in diffusers even of extreme divergence and to depend principally on screen location and pressure-drop coefficient of the screen.
Date:
July 1948
Creator:
Schubauer, Galen Brandt & Spangenberg, Wesley G.
System:
The UNT Digital Library
Sound from dual-rotating and multiple single-rotating propellers
Report presenting sound measurements for static conditions in a range of tip Mach numbers for three different dual-rotating-propeller configurations and one combination of two single-rotating propellers operating side by side in the same plane of rotation. The results obtained are compared with a theoretical analysis of the problem and excellent agreement is found.
Date:
July 1948
Creator:
Hubbard, Harvey H.
System:
The UNT Digital Library
A Device for Measuring Sonic Velocity and Compressor Mach Number
Note presenting a device that measures the velocity of sound in fluids at stagnation and is especially adaptable to turbine and compressor testing for which the composition of the working fluid may be in doubt. The Helmholtz resonator is used for measuring sonic velocity and compressor Mach number in these devices.
Date:
July 1948
Creator:
Huber, Paul W. & Kantrowitz, Arthur
System:
The UNT Digital Library