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The 6-Foot-4-Inch Wind Tunnel at the Washington Navy Yard
Report discussing the 6-foot-4-inch wind tunnel and its auxiliary equipment has proven itself capable of continuous and reliable output of data. The real value of the tunnel will increase as experience is gained in checking the observed tunnel performance against full-scale performance. Such has been the case of the 8- by 8-foot tunnel, and for that reason the comparison in the calibration tests have been presented.
Date:
August 1935
Creator:
Desmond, G. L. & McCrary, J. A.
System:
The UNT Digital Library
The 300 H.P. Benz Aircraft Engine
This report provides a description of the Benz 300 H.P. aircraft engine containing 12 cylinders placed at a 60° angle. It includes a detailed description of the development of the constructional points, particularly the cylinders, pistons, and connecting rods, as well as the engine fitting, lubrication, oil pumps, bearings, oil tank, fuel pump, carburetors, and cooling system. There are seven pages of illustrative figures at the end of the report.
Date:
January 1921
Creator:
Heller, A.
System:
The UNT Digital Library
The 1350 F stress-rupture properties of two wrought alloys and three cast alloys
From Summary: "These properties compare favorably with those of the strongest similar alloys previously investigated. However, compared with a 60Cr-25Fe-15Mo alloy, the three cobalt-chronium-nickel cast alloys are inferior. A correlation of NACA and OSRD (Project NRC-8) data is presented, showing the variation of rupture strengths with temperature in the range of 1350^o to 2000^o for alloys."
Date:
November 1947
Creator:
Reynolds, E. E.; Freeman, J. W. & White, A. E.
System:
The UNT Digital Library
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
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
N.A.C.A. Langley field wind tunnel apparatus: The tilting manometer
A description is given of a tilting manometer designed to meet the requirements of a manometer for use in the wind tunnel at the Langley Memorial Aeronautical Laboratory. This gauge was designed to meet the requirements of a manometer in use in connection with a static pressure plate to indicate the wind speed in the tunnel. The requirements are noted. The sensitivity of the gauge must be made inversely proportional to the pressure to be measured. The gauge must be accurately and quickly set for any desired pressure.
Date:
January 1921
Creator:
Norton, F. H. & Bacon, D. L.
System:
The UNT Digital Library
N.A.C.A. Recording Air Speed Meter
A new type of air speed meter is described which was designed by the technical staff of the National Advisory Committee for Aeronautics. The instrument consists essentially of a tight metal diaphragm of high natural period which is acted upon by the pressure difference of a pitot-static head. The resulting deflection of this diaphragm is recorded optically on a moving film.
Date:
October 1921
Creator:
Norton, F. H.
System:
The UNT Digital Library
N.A.C.A. Stall-Warning Indicator
"The stall-warning indicator employs a total-head tube located close to the wing surface in a region wherein local stalling occurs before the main portion of the wing stalls. The artificial production of a localized stalled region is accomplished by means of a sharp leading edge extending a few inches along the span. An abrupt drop in the total pressure relative to a static reference taken at some convenient point occurs at the stall in this region" (p. 1).
Date:
October 1938
Creator:
Thompson, F. L.
System:
The UNT Digital Library
Abnormal grain growth in M-252 and S-816 alloys
Report discussing an experimental investigation was carried out on air- and vacuum-melted M-252 and S-816 alloys to find conditions of heating and hot-working which resulted in abnormal grain growth. The experiments were mainly limited to normal conditions of heating for hot-working and heat treatment and normal temperatures of solution treatment were used to allow grain growth after susceptibility to abnormal grain growth was developed by various experimental conditions. Results indicated that small reductions of essentially strain-free metal were the basic cause of such grain growth.
Date:
November 1957
Creator:
Decker, R. F.; Rush, A. I.; Dano, A. G. & Freeman, J. W.
System:
The UNT Digital Library
Abnormal grain growth in nickel-base heat-resistant alloys
From Introduction: "The data included in this report for Nimonic 80A alloy, for instance, represent experiments carried out to help clarify a production problem of grain-size control in an alloy which has been extensively used. The general procedure of the investigation was to carry out controlled laboratory experiments on samples of bar stock to find conditions of heating and hot-working which resulted in abnormal grain growth."
Date:
December 1957
Creator:
Decker, R. F.; Rush, A. I.; Dano, A. G. & Freeman, J. W.
System:
The UNT Digital Library
Absolute Coefficients and the Graphical Representation of Aerofoil Characteristics
It is argued that there should be an agreement as to what conventions to use in determining absolute coefficients used in aeronautics and in how to plot those coefficients. Of particular importance are the absolute coefficients of lift and drag. The author argues for the use of the German method over the kind in common use in the United States and England, and for the Continental over the usual American and British method of graphically representing the characteristics of an airfoil.
Date:
June 1921
Creator:
Munk, Max
System:
The UNT Digital Library
Absolute Dimensions of Karman Vortex Motion
Note presenting an investigation of the Karman vortex street, which is a flow arrangement occurring behind a plate. The equations governing the flow and some of the hypotheses behind it are provided.
Date:
January 1923
Creator:
Heisenberg, Werner
System:
The UNT Digital Library
Accelerations and passenger harness loads measured in full-scale light-airplane crashes
From Introduction: "Light-airplane accident data, compiled by Crash Injury Research of Cornell University Medical College, indicate that human beings have often withstood declarations in excess of those imposed in airplane crashes involving extensive damage to the airplane structure (ref. 1). This study also correlates the extent of damage to the airplane structure with the injury incurred by the occupants during crash accidents."
Date:
August 1953
Creator:
Eiband, A. Martin; Simpkinson, Scott H. & Black, Dugald O.
System:
The UNT Digital Library
Accelerations in Transport-Airplane Crashes
From Introduction: "A study of crash-impact survival in light airplanes is reported in references 1 and 2. A similar study for fighter airplanes is reported in reference 3. This report discusses crash-impact survival in transport airplanes."
Date:
February 1958
Creator:
Preston, G. Merritt & Pesman, Gerard J.
System:
The UNT Digital Library
Accuracy of Approximate Methods for Predicting Pressures on Pointed Nonlifting Bodies of Revolution in Supersonic Flow
Note presenting an investigation of the accuracy and range of applicability of the linearized theory, second-order theory, tangent-cone method, conical-shock-expansion theory, and Newtonian theory for predicting pressure distributions on pointed bodies of revolution at zero angle of attack. Three shapes, cone, ogive, and a modified optimum body, are investigated over a wide range of fineness ratios and Mach numbers. The results indicated that for most combinations of fineness ratio and Mach number, one of the approximate methods will give reasonable results.
Date:
August 1952
Creator:
Ehret, Dorris M.
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
An accurate and rapid method for the design of supersonic nozzles
From Introduction: "This report presents a computational procedure which provides for the rapid and accurate calculation of any streamline in a series of special flows. Detailed information is given on the boundary conditions and equations used for computing the characteristic nets and stream function."
Date:
February 1955
Creator:
Beckwith, Ivan E. & Moore, John A.
System:
The UNT Digital Library
An Accurate Method of Measuring the Moments of Inertia of Airplanes
From Summary: "This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent."
Date:
October 1930
Creator:
Miller, M. P.
System:
The UNT Digital Library
Achievement of Continuous Wall Curvature in Design of Two-Dimensional Symmetrical Supersonic Nozzles
"Auxiliary boundary conditions are derived to assure continuity of wall curvature in applying the method of characteristics to the design of two-dimensional symmetrical supersonic nozzles. An illustrative example is included" (p. 1).
Date:
January 1952
Creator:
Evvard, J. C. & Marcus, Lawrence R.
System:
The UNT Digital Library
Acoustic analysis of ram-jet buzz
From Introduction: "The surging of a system containing a centrifugal- or axial-flow compressor (e.g., refs. 1 to 4) is an example of self-sustained oscillation. Inlets designed for supersonic jet engines also have been observed to induce oscillations (e.g., refs. 5 to 11) which are usually referred to as "buzz." The origin of buzz in ram-jet engines is the subject of the present report."
Date:
November 1955
Creator:
Mirels, Harold
System:
The UNT Digital Library
Acoustic radiation from two-dimensional rectangular cutouts in aerodynamic surfaces
From Introduction: "The experiments in high-speed flow showed that an intense, high-frequency acoustic radiation is an essential feature of the problem. Consequently, a study of the acoustic field (involving schlieren observations and frequency and intensity measurements) was undertaken. This report presents the salient features of the study, which was mainly exploratory."
Date:
August 1955
Creator:
Krishnamurty, K.
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
Acoustical Treatment for the NACA 8- by 6-Foot Supersonic Propulsion Wind Tunnel
"This report presents results of a research and engineering program performed during the first half of 1950 that resulted in an acoustical treatment for the 8- by 6-foot supersonic wind tunnel at the Lewis Flight Propulsion Laboratory" (p. 1).
Date:
June 1955
Creator:
Beranek, Leo L.; Labate, Samuel & Ingard, Uno
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