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N.A.C.A. control position recorder
Report discussing a new instrument is described which is capable of simultaneously recording the position of the three controls of an airplane. The records are taken photographically on a standard N.A.C.A. film drum and the instrument can be quickly installed in any airplane.
Date:
May 1922
Creator:
Norton, F. H.
System:
The UNT Digital Library
Adaptation of aeronautical engines to high altitude flying
Report discussing Issues and techniques relative to the adaptation of aircraft engines to high altitude flight. Covered here are the limits of engine output, modifications and characteristics of high altitude engines, the influence of air density on the proportions of fuel mixtures, methods of varying the proportions of fuel mixtures, the automatic prevention of fuel waste, and the design and application of air pressure regulators to high altitude flying. Summary: 1. Limits of engine output. 2. High altitude engines. 3. Influence of air density on proportions of mixture. 4. Methods of varying proportions of mixture. 5. Automatic prevention of fuel waste. 6. Design and application of air pressure regulators to high altitude flying.
Date:
May 1923
Creator:
Kutzbach, K.
System:
The UNT Digital Library
The Aerodynamic Characteristics of a Model Wing Having a Split Flap Deflected Downward and Moved to the Rear
"Tests were made on a model wing with three different sized split trailing-edged flaps, in the NACA 7 by 10 foot wind tunnel. The flaps were formed of the lower rear portion of the wing and were rotated downward about axes at their front edges. The lift, drag, and center of pressure were measured with the axis in its original position and also with it moved back in even steps to the trailing edge of the main wing, giving in effect an increase in area. The split flaps when deflected about their original axis locations gave slightly higher maximum lift coefficients than conventional trailing-edge flaps, and the lift coefficients were increased still further by moving the axes toward the rear" (p. 1).
Date:
May 1932
Creator:
Weick, Fred E. & Harris, Thomas A.
System:
The UNT Digital Library
Aerodynamic characteristics of several 6-percent-thick airfoils at angles of attack from 0 degrees to 20 degrees at high subsonic speeds
Report presenting two-dimensional tests of eight 6-percent-thick symmetrical airfoils of the supersonic and subsonic types. Static pressures along the surfaces of each airfoil measured over a range of Mach numbers and angles of attack. Results regarding lift coefficient, drag coefficient, quarter-chord pitching-moment coefficient, and schileren photographs of the pressure distributions are provided.
Date:
May 1955
Creator:
Daley, Bernard N. & Lord, Douglas R.
System:
The UNT Digital Library
Airplane Performance as Influenced by the Use of a Supercharged Engine
"The question of the influence of a supercharged engine on airplane performance is treated here in a first approximation, but one that gives an exact idea of the advantage of supercharging. Considered here is an airplane that climbs first with an ordinary engine, not supercharged, and afterwards climbs with a supercharged engine. The aim is to find the difference of the ceilings reached in the two cases" (p. 1).
Date:
May 1920
Creator:
de Bothezat, George
System:
The UNT Digital Library
Airplane Superchargers
Discussed here are the principles and operation of aircraft engine superchargers used to maintain and increase engine power as aircraft encounter decreases in the density of air as altitude rises. Details are given on the design and operation of the centrifugal compressors. A method is given for calculating the amount of power needed to drive a compressor. The effects of the use of a compressor on fuel system operation and design are discussed. Several specific superchargers that were in operation are described.
Date:
May 1921
Creator:
Noack, W. G.
System:
The UNT Digital Library
Analysis of a Strut With a Single Elastic Support in the Span, With Applications to the Design of Airplane Jury-Strut Systems
Report presenting an analysis of a wing brace with a small auxiliary strut, which is attached to the wing spar at the upper end. The design is quite effective but has some difficult analysis problems. The report is broken into two parts; one is a theoretical investigation and one is an experimental investigation.
Date:
May 1935
Creator:
Schwartz, A. Murray & Bogert, Reid
System:
The UNT Digital Library
Analysis of Available Data on the Effects of Tabs on Control-Surface Hinge Moments
From Introduction: "A collection balanced-aileron test data is given in reference 1. Reference 2 presents a collection of data applicable to the design of tail surfaces. The results of analyses of data for control surfaces with internal balances, plain-overhang and Frise balances, beveled trailing edges, and unshielded horn balances have already been published in references 3 to 6."
Date:
May 1946
Creator:
Crandall, Stewart M. & Murray, Harry E.
System:
The UNT Digital Library
Analysis of Circular Shell-Supported Frames
From Summary: "This paper deals with the single problem if circular shell-supported frames subjected to concentrated loadings. A mathematical attack is developed and presented in the form of nondimensional-coefficient curves."
Date:
May 1944
Creator:
Wignot, J. E.; Combs, Henry & Ensrud, A. F.
System:
The UNT Digital Library
Analysis of Ear Formation in Deep-Drawn Cups
From Introduction: "The purpose of this paper is to show that the number and location of ears can be computed on the basis of single-crystal behavior and a knowledge of the orientation of the polycrystalline aggregate. Although the proposed method is a general one, only face-centered cubic metals are considered in this paper."
Date:
May 1955
Creator:
McEvily, Arthur J., Jr.
System:
The UNT Digital Library
Analysis of Fully Developed Turbulent Heat Transfer and Flow in an Annulus With Various Eccentricities
From Introduction: "Most of the existing analyses for turbulent flow and heat transfer in passages have been confined to circular tubes or parallel plates (refs. 1 to 5). In reference 6, temperature distributions for rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients. Some work on the calculation of the velocity and shear-stress distributions in corners is reported in reference 7."
Date:
May 1955
Creator:
Deissler, Robert G. & Taylor, Maynard F.
System:
The UNT Digital Library
An Analysis of the Factors Affecting the State of Fuel and Air Mixtures
From Introduction: "It is the purpose of this paper to describe the physical properties that are necessary to specify mixture quality in a system containing fuel and dry air and to evaluate the theoretical rolation between these properties and the physical properties of the mixture."
Date:
May 1946
Creator:
Gilbert, Mitchell; Howard, John N. & Hicks, Bruce L.
System:
The UNT Digital Library
Analytical Evaluation of Aerodynamic Characteristics of Turbines With Nontwisted Rotor Blades
From Introduction: "The purpose the present report is to investigate the aerodynamic characteristics of nontwisted-rotor-blade turbines and to evaluate the characteristics of this type of design by comparison with the characteristics of free-vortex designs."
Date:
May 1951
Creator:
Slivka, William R. & Silvern, David H.
System:
The UNT Digital Library
The application of matrix methods to coordinate transformations occurring in systems studies involving large motions of aircraft
Report presenting the method and advantages of matrix algebra in setting up the geometric aspects of problems of airplane motion. The paper is divided into two parts. The first is about the aspects of matrix algebra required for use in orthogonal transformations and the other shows how to use orthogonal transformations in matrix form by applying them in several examples.
Date:
May 1957
Creator:
Doolin, Brian F.
System:
The UNT Digital Library
Application of the wire-mesh plotting device to incompressible cascade flows
From Summary: "The methods used in the application of the wire-mesh plotting device to find the flow pattern about a cascade of airfoils in compressible inviscid flow and some mathematical checks that increase the accuracy of this application are described. Results for two typical turbine-blade cascades are shown to compare well with experimental data. A method of utilizing the wire mesh to design turbine blades with a prescribed pressure distribution in incompressible flow is presented."
Date:
May 1950
Creator:
Westphal, Willard R. & Dunavant, James C.
System:
The UNT Digital Library
Appraisal of the Hazards of Friction-Spark Ignition of Aircraft Crash Fires
Note presenting a study to determine if common aircraft metals produce friction sparks capable of igniting combustibles that might be spilled in an airplane crash. Samples of aluminum, titanium, magnesium, chrome-molybdenum steel, and stainless steel were dragged over concrete and asphalt runways while a combustible mixture of gasoline, JP-4 fuel, kerosene, or preheated oil was sprayed around the sample.
Date:
May 1957
Creator:
Campbell, John A.
System:
The UNT Digital Library
Appreciation and determination of the hydrodynamic qualities of seaplanes
Report presenting a summary of the hydrodynamic qualities of interest in the normal operation of a seaplane, established over a period of years by model testing and by some knowledge of full-size operation. Results regarding longitudinal stability and control, landing stability, seaworthiness, performances, and lateral stability and control are provided.
Date:
May 1947
Creator:
Parkinson, John B.
System:
The UNT Digital Library
An approximate analytical method for studying entry into planetary atmospheres
Report presenting a single, ordinary, nonlinear differential equation of second order that can be used for determining entry into an exponential planetary atmosphere. The reduced equation includes various terms, some of which represent the gravity force, the centrifugal acceleration, and the lift force. A number of solutions for lifting and nonlifting vehicles entering at various initial angles are obtained from the complete nonlinear equation.
Date:
May 1958
Creator:
Chapman, Dean R.
System:
The UNT Digital Library
Approximate indicial lift functions for several wings of finite span in incompressible flow as obtained from oscillatory lift coefficients
Report presenting the unsteady-lift functions for a wing undergoing a sudden change in sinking speed for delta wings with three aspect ratios and rectangular and elliptical wings with three aspect ratios. Results regarding the delta-plan-form K1 function, indical spanwise loading distributions, effect of plan-form shape on the K1 function, and effect of aspect ratio on the K1 and K2 functions are provided.
Date:
May 1956
Creator:
Drischler, Joseph A.
System:
The UNT Digital Library
Approximate Relations and Charts for Low-Speed Stability Derivatives of Swept Wings
Contains derivations, based on a simplified theory, of approximate relations for low-speed stability derivatives of swept wings. Method accounts for the effects and, in most cases, taper ratio. Charts, based on the derived relations, are presented for the stability derivatives of untapered swept wings. Calculated values of the derivatives are compared with experimental results.
Date:
May 1948
Creator:
Toll, Thomas A. & Queijo, M. J.
System:
The UNT Digital Library
The attenuation characteristics of four specially designed mufflers tested on a practical engine setup
Attenuation characteristics of four different resonator mufflers were determined in both cold tests and engine field tests and compared with the theoretical calculations. These mufflers were specifically designed for a helicopter. Engine-exhaust sound pressures, temperatures, and noise levels from the helicopter were measured. The experimental muffler cold tests indicated close a agreement with theory, whereas the engine tests indicated some discrepancies. Test results show the usefulness of the theoretical equation used for predicting muffler attenuation characteristics.
Date:
May 1953
Creator:
Stokes, George M. & Davis, Don D., Jr.
System:
The UNT Digital Library
An automatic electrical analyzer for 45 degree strain-rosette data
Report presenting a device that automatically analyses the data from a 45 degree strain rosette. The rosette strains are properly combined by means of an electric circuit to yield a direct meter reading of maximum shear strain and major and minor principal strains.
Date:
May 1944
Creator:
Manson, S. S.
System:
The UNT Digital Library
Bending of Rectangular Plates with Large Deflections
"The solution of von Karman's fundamental equations for large deflections of plates is presented for the case of a simply supported rectangular plate under combined edge compression and lateral loading. Numerical solutions are given for square plates and for rectangular plates with a width-span ratio of 3:1. The effective widths under edge compression are compared with effective widths according to von Karman, Bengston, Marguerre, and Cox and with experimental results by Ramberg, McPherson, and Levy" (p. 1).
Date:
May 1942
Creator:
Levy, Samuel
System:
The UNT Digital Library
Bending Stresses Due to Torsion in a Tapered Box Beam
Note presenting a method for the calculation of bending stresses due to torsion in a tapered box beam. A special taper was assumed in which all flanges, if extended, would meet at a point. The results obtained by this method were compared with experimental data obtained from tests performed on a tapered box beam.
Date:
May 1947
Creator:
Kruszewski, Edwin T.
System:
The UNT Digital Library