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N.A.C.A. Flight-Path Angle and Air-Speed Recorder
"A new trailing bomb-type instrument for photographically recording the flight-path angle and air speed of aircraft in unaccelerated flight is described. The instrument consists essentially of an inclinometer, air-speed meter and a film-drum case. The inclinometer carries an oil-damped pendulum which records optically the flight-path angle upon a rotating motor-driven film drum. The air-speed meter consists of a taut metal diaphragm of high natural frequency which is acted upon by the pressure difference of a Prandtl type Pitot-static tube" (p. 1).
Date:
April 1926
Creator:
Coleman, Donald G.
System:
The UNT Digital Library
The Accuracy of the Substitute-Stringer Approach for Determining the Bending Frequencies of Multistringer Box Beams
"The accuracy of the substitute-stringer approach for including the effects of shear lag in the calculation of the transverse modes and frequencies of multistringer box beams is investigated. Box beams, the covers of which consist of normal-stress-carrying stringers on sheets which carry not only shear but also normal stress, are analyzed exactly. Frequencies of beams with various numbers of stringers, obtained by means of this exact analysis, serve to determine the possible accuracy of the frequencies obtained by the substitute-stringer approach" (p. 1).
Date:
April 1956
Creator:
Davenport, William W.
System:
The UNT Digital Library
Acoustic, thrust, and drag characteristics of several full-scale noise suppressors for turbojet engines
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.
System:
The UNT Digital Library
Aerodynamic characteristics at Reynolds numbers of 3.0 x 10(exp 6) and 6.0 x 10(exp 6) of three airfoil sections formed by cutting off various amounts from the rear portion of the NACA 0012 airfoil section
Report presenting an investigation of the two-dimensional aerodynamic characteristics of three airfoil sections formed by removing various portions of the original chord from the trailing edge of the NACA 0012 airfoil section. Results regarding lift, drag, and pitching moment and aerodynamic center are provided.
Date:
April 1950
Creator:
Smith, Hamilton A. & Schaefer, Raymond F.
System:
The UNT Digital Library
The Aerodynamic Characteristics of Airfoils as Affected by Surface Roughness
"The effect on airfoil characteristics of surface roughness of varying degrees and types at different locations on an airfoil was investigated at high values of the Reynolds number in a variable density wind tunnel. Tests were made on a number of National Advisory Committee for Aeronautics (NACA) 0012 airfoil models on which the nature of the surface was varied from a rough to a very smooth finish. The effect on the airfoil characteristics of varying the location of a rough area in the region of the leading edge was also investigated" (p. 1).
Date:
April 1933
Creator:
Hooker, Ray W.
System:
The UNT Digital Library
The aerodynamic design and calibration of an asymmetric variable Mach number nozzle with a sliding block for the Mach number range 1.27 to 2.75
From Introduction: "This paper presents the basic design method and experimental results of calibration of a nozzle which was constructed to conform to the analytically determined ordinates."
Date:
April 1953
Creator:
Burbank, Paige B. & Byrne, Robert W.
System:
The UNT Digital Library
The Aerodynamic Drag of Flying-Boat Hull Model as Measured in the NACA 20-Foot Wind Tunnel - 1
"The main purpose of this investigation is to make available to the designer useful information with regard to the aerodynamic drag of various types of flying-boat hull models. The present report is the first in a series covering investigation in this field. Through close cooperation between hydrodynamics and aerodynamics divisions it is hoped that results leading to improvements in hull design obtained" (p. 1).
Date:
April 1935
Creator:
Hartman, Edwin P.
System:
The UNT Digital Library
Analysis and comparison with theory of flow-field measurements near a lifting rotor in the Langley full-scale tunnel
From Introduction: "The time-averaged flows are considerably simpler to deal with theoretically than are the instantaneous flows, and the results of several theoretical analyses are available (refs. 2 to 6, for example). Several previous experimental investigations (see ref. 7 for a bibliography) have provided some qualitative information on the subject by the use of smoke in flight and in wind tunnels. However, quantitative measurements (refs. 8 to 10) are extremely scarce and, in general, are inadequate either to define the nature of the flow or to check the accuracy of the theoretical calculations."
Date:
April 1956
Creator:
Heyson, Harry H.
System:
The UNT Digital Library
Analysis of a spin and recovery from time histories of attitudes and velocities as determined for a dynamic model of a contemporary fighter airplane in the free-spinning tunnel
From Introduction: "In this paper are presented descriptions of the camera setups and associated equipment, the equations and methods used in determining the model attitudes and motions from the film, and time-history curves of the variables of the spin and recovery investigated. Discussions of the nature of the spin and recovery obtained and of factors ostensibly affecting these motions are included."
Date:
April 1956
Creator:
Scher, Stanley H.
System:
The UNT Digital Library
Analysis of an induction blowdown supersonic tunnel
From Introduction: "In the present paper, general ejector equations (see reference 4 or 5) and certain assumptions with regard to flow conditions and pressure losses have been utilized to calculate the running times of induction blowdown supersonic tunnels operating in the mentioned Mach number range."
Date:
April 1950
Creator:
Bidwell, Jerold M.
System:
The UNT Digital Library
An analysis of estimated and experimental transonic downwash characteristics as affected by plan form and thickness for wing and wing-fuselage configurations
From Introduction: "The purpose of the present paper is to present summary of the information gleaned from various transonic-bump investigations of wing and wing-fuselage configurations at two representative tail heights and to compare these results with theoretical estimations made in subsonic and supersonic Mach number range."
Date:
April 1956
Creator:
Weil, Joseph; Campbell, George S. & Diederich, Margaret S.
System:
The UNT Digital Library
Analysis of harmonic forces produced at hub by imbalances in helicopter rotor blades
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.
System:
The UNT Digital Library
Analysis of heat addition in a convergent-divergent nozzle
From Introduction: "The purpose of this report is to treat analytically heat addition heat addition to a divergent stream with initially sonic flow and to employ the results thus obtained in evaluating the effect of delayed combustion on convergent-divergent nozzle performance."
Date:
April 1953
Creator:
Hearth, Donald P. & Perchonok, Eugene
System:
The UNT Digital Library
Analysis of Static Aeroelastic Behavior of Low-Aspect-Ratio Rectangular Wings
"Slender-body theory is used in conjunction with late theory to analyze the static aeroelastic-divergence behavior of low-aspect-ratio rectangular wings of constant thickness when chordwise deformations are considered. In the analysis, the spanwise variation of the deflection is restricted to a parabola but the chordwise variation is allowed complete freedom. Results show the variation of the divergence speed and mode shape with the aspect ratio" (p. 1).
Date:
April 1957
Creator:
Hedgepeth, John M. & Waner, Paul G., Jr.
System:
The UNT Digital Library
An Analysis of the Compressive Strength of Honeycomb Cores for Sandwich Construction
Note presenting an analysis that was undertaken as part of an investigation of low-density fibrous core materials for sandwich construction. This particular investigation found that honeycomb structure exhibit promise as core materials because of their high strength-weight ratios. A formula has been derived that considerably reduced the amount of testing necessary to evaluate the effectiveness of the materials.
Date:
April 1947
Creator:
Norris, Charles B.
System:
The UNT Digital Library
An analysis of the factors that affect the exhaust process of a four-stroke-cycle reciprocating engine
From Introduction: "An investigation was made to determine the relative significance of the factors that affect the exhaust process; the effects that an exhaust-process change has on cylinder charging were given special attention. Differential equations of this nature have been developed by Kemble (reference 1) but the forms of these equations are such that general conclusions regarding the various factors affecting the exhaust process cannot be determined."
Date:
April 1947
Creator:
Stanitz, John D.
System:
The UNT Digital Library
Analysis of Turbulent Flow and Heat Transfer on a Flat Plate at High Mach Numbers With Variable Fluid Properties
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.
System:
The UNT Digital Library
Analytic determination of the discharge coefficients of flow nozzles
From Introduction: "In rounded-approach nozzles with discharge coefficients close to unity, the frictional effects are concentrated in the boundary layer. A method of obtaining an analytical relation among the discharge coefficient, Reynolds number, and the nozzle geometry by utilization of elementary boundary-layer theory is presented herein."
Date:
April 1955
Creator:
Simmons, Frederick S.
System:
The UNT Digital Library
The Application of Green's Theorem to the Solution of Boundary-Value Problems in Linearized Supersonic Wing Theory
Note presenting general methods of solution for the two- and three-dimensional steady-state and two-dimensional unsteady-state equations. Four applications of the general solutions are given.
Date:
April 1949
Creator:
Heaslet, Maxwell A. & Lomax, Harvard
System:
The UNT Digital Library
The application of high-temperature strain gauges to the measurement of vibratory stresses in gas-turbine buckets
The feasibility of measuring the vibration in the buckets of a gas turbine under service conditions of speed and temperature was determined by use of a high temperature wire strain gauge cemented to a modified supercharger turbine bucket. A high-temperature wire strain gauge and the auxiliary mechanical and electrical equipment developed for the investigation are described.
Date:
April 1947
Creator:
Kemp, R. H.; Morgan, W. C. & Manson, S. S.
System:
The UNT Digital Library
An Application of Statistical Data in the Development of Gust-Load Criterions
"In conjunction with assumptions concerning the proportion of time spent at various speeds, statistical gust data were used to determine gust load factors that could be exceeded a given number of times during the operational life of an airplane. The results indicated that present gust load factors might be considerably lowered in certain cases with a consequent decrease in structural weight. Modification of the present criterion, however, must await the accumulation of data not presently available" (p. 1).
Date:
April 1947
Creator:
Bland, Reginald B. & Reisert, T. D.
System:
The UNT Digital Library
Application of the generalized shock-expansion method to inclined bodies of revolution traveling at high supersonic airspeeds
The generalized shock-expansion method is applied to obtain solutions to the flow field about pointed bodies of revolution at high supersonic airspeeds and small angles of attack. Simple explicit expressions are obtained for the surface Mach numbers and surface pressures in the special case of slender bodies. In the case of inclined cones, algebraic solutions are obtained defining the entire flow field. Experimental pressure-distribution data for cones and ogives at Mach numbers from 3 to 5 are included. (author).
Date:
April 1955
Creator:
Savin, Raymond C.
System:
The UNT Digital Library
Application of Transonic Similarity
"From a review of the different similarity approaches to compressible potential flow, the meaning and limitations of transonic similarity are traced back to their origin. Although the main text deals with the quasi two-dimensional flow, special suggestions for the case of axisymmetric bodies are added in an appendix" (p. 1).
Date:
April 1952
Creator:
Busemann, Adolf
System:
The UNT Digital Library
An Approach to the Prediction of the Frequency Distribution of Gust Loads on Airplanes in Normal Operations
Note presenting the statistical concepts of random variables and probability distributions as applied to the sharp edge gust formula as a basis for the prediction of the gust-load history of airplanes in service operations. The results are applied in an example and the predicted load experience is compared with the available flight loads data for the case.
Date:
April 1952
Creator:
Press, Harry
System:
The UNT Digital Library