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The aerodynamic forces and moments on a 1/10-scale model of a fighter airplane in spinning attitudes as measured on a rotary balance in the Langley 20-foot free-spinning tunnel

Description: From Introduction: "This investigation provides general information on the magnitudes and directions of the aerodynamic forces and moments acting on a fighter airplane in fully developed spins. The investigation includes the determination of the effects on the aerodynamic forces and moments of varied rudder setting with and against the spin, of tail modifications, and of deflected flaps and lowered landing gear."
Date: September 1950
Creator: Stone, Ralph W., Jr.; Burk, Sanger M., Jr. & Bihrle, William, Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamic investigation of a parabolic body of revolution at Mach number of 1.92 and some effects of an annular supersonic jet exhausting from the base

Description: Report discussing an aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base.
Date: September 1956
Creator: Love, Eugene S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8

Description: Report presenting an investigation to determine the aerodynamic characteristics of a group of NACA 16-series airfoils related in camber and thickness over a range of Mach numbers. All of the currently available force-test data for NACA 16-series airfoils obtained under the same test conditions in the 24-inch high-speed tunnel are presented.
Date: September 1948
Creator: Lindsey, W. F.; Stevenson, D. B. & Daley, Bernard N.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Aileron as an Aid to Recovery From the Spin

Description: From Introduction: "In order to afford a means of comparison and to obtain a clear understanding of the results, a study of the effects of normal angular deflections of the ailerons, with and against the spin, was included in the investigation. Ailerons deflected with the spin means that the ailerons are deflected with right aileron up and left aileron down in a right spin. The results of the investigation are discussed in this paper."
Date: September 1940
Creator: Neihouse, A. I.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airfoil lift with changing angle of attack

Description: From Summary: "Tests have been made in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics to determine the effects of pitching oscillations upon the lift of an airfoil. It has been found that the lift of an airfoil, while pitching, is usually less than that which would exist at the same angle of attack in the stationary condition, although exceptions may occur when the lift is small or if the angle of attack is being rapidly reduced. It is also shown that the behavio… more
Date: September 1927
Creator: Reid, Elliott G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airfoil profiles for minimum pressure drag at supersonic velocities: Application of shock-expansion theory, including consideration of hypersonic range

Description: From Summary: "A comparison of optimum profiles determined by the shock-expansion method of this report with corresponding profiles determined by the linearized-theory method of a previous report shows only small differences in shape at Mach numbers up to infinity even though the linearized theory at high supersonic Mach numbers breaks down completely insofar as the drag of the profile is concerned. Curves are presented which show that for thin airfoils the use of a trailing-edge thickness cons… more
Date: September 17, 1952
Creator: Chapman, Dean R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Alterations and Tests of The "Farnboro" Engine Indicator

Description: "The 'Farnboro' electric indicator was tested as received from the manufacturers, and modifications made to the instrument to improve its operation. The original design of disk valve was altered so as to reduce the mass, travel, and seat area. Changes were made to the recording mechanism, which included a new method of locating the top center position on the record. The effect of friction on the motion of the pointer while taking motoring and power cards was eliminated by providing a means of p… more
Date: September 1930
Creator: Collins, John H., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis for Control Application of Dynamic Characteristics of Turbojet Engine With Tail-Pipe Burning

Description: "The first basic problem that must be solved before control synthesis can proceed is that of determining the dynamic characteristics of the engine. Accordingly, an analysis of the dynamic behavior of the turbojet engine with tail-pipe burning was made at the NACA Lewis laboratory and is presented herein" (p. 1).
Date: September 1950
Creator: Feder, Melvin S. & Hood, Richard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of acceleration, airspeed, and gust-velocity data from a four-engine transport airplane in operations on an eastern United States route

Description: Report presenting time-history data obtained by the NACA VGH recorder from a model of a four-engine civil transport airplane during operations on an eastern United States route in order to determine magnitude and frequency of occurrence of gusts, gust accelerations, and associated airspeeds. The results are compared with results from two similar operations. The gust-load history for the operation was more severe than that for the other two operations.
Date: September 1955
Creator: Coleman, Thomas L. & Fetner, Mary W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Dr. Schaffran's Propeller Model Tests

Description: Note presenting an analysis of the propeller model tests of Dr. Schaffran. Only the thrust is examined. The results indicate that the thrust produced by three-blade and four-blade propellers follows the same laws as with two-blade propellers, and that all conclusions reached from Dr. Durand's tests can be upheld.
Date: September 1923
Creator: Munk, Max M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of effect of variations in primary variables on time constant and turbine-inlet-temperature overshoot of turbojet engine

Description: From Introduction: "The design of turbojet-engine control systems is intimately related to the dynamic characteristics of the engine and has advanced to the stage where theoretically correct control constants can be determined for fixed dynamic properties (references 1 and 2). The use of the thermodynamic equations presupposes that the engine processes are quansi-static. Such an assumption is shown to be valid for a turbojet engine in references 3 and 4.
Date: September 1950
Creator: Heidmann, Marcus F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of Performance of a Jet Engine From Characteristics of Components 2: Interaction of Components as Determined From Engine Operation

Description: Report presenting an investigation of a method to analyze and to estimate performance of jet engines, which was applied to the study of the characteristics of a research turbojet engine built for the investigation. Results regarding the compressor performance, turbine performance, combustion chamber, and interaction of jet engine components are provided.
Date: September 1948
Creator: Goldstein, Arthur W.; Alpert, Sumner; Beede, William & Kovach, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Pure-Bending Flutter of a Cantilever Swept Wing and Its Relation to Bending-Torsion Flutter

Description: From Introduction: "The present paper is intended to give some features of flutter in bending alone and contains results of analyses made to determine some effects of wing mass-density ratio, angle of sweepback, length-semichord ratio, and Mach number. Some relations of pure-blending flutter to the conventional bending-torsion flutter are also given."
Date: September 1951
Creator: Cunningham, H. J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Analysis of Ramjet Engines Using Supersonic Combustion

Description: From Introduction: "The concept of supersonic combustion is by no means new, although little work appears to have been published on the subject. For example, an analysis of supersonic combustion to provide lift under a wing is given in reference 1. Reference 2 discusses applications to hypersonic ramjets being studied at the University of Michigan."
Date: September 1958
Creator: Weber, Richard J. & MacKay, John S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of shock motion in ducts during disturbances in downstream pressure

Description: From Summary: "The effect of small downstream pressure distributions on the position of a normal shock in a duct with area variation is analyzed. For the analysis, the gas flow is treated as quasi-one-dimensional, and boundary layer is neglected. The analysis shows that there is a first-order lag relation between shock position and small downstream disturbances in pressure which occur at frequencies below a given limit."
Date: September 1957
Creator: Hurrell, Herbert G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of the airspeeds and normal accelerations of Boeing S-307 airplanes in commercial transport operation

Description: From Introduction: "The present paper has been prepared to give the results of the analysis of the V-G records obtained from three Boeing S-307 airplanes operating in Caribbean region and the northern part of South America during the period from 1940 to 1944."
Date: September 1946
Creator: Peiser, A. M. & Walker, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of the airspeeds and normal accelerations of Douglas DC-3 airplanes in commercial transport operation

Description: From Introduction: "The present report is the second prepared to give the results of an analysis of V-G data from commercial transport airplanes. The present report is concerned with an analysis of data obtained with Douglas DC-3 airplanes flying over three transcontinental routes in the United States."
Date: September 1946
Creator: Peiser, A. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of the airspeeds and normal accelerations of Martin M-130 airplanes in commercial transport operation

Description: From Introduction: "Acceleration and airspeed data obtained from V-G records collected during commercial transport operations (references 1 and 2) are being analyzed in some detail to determine the flight loads and operating speeds as functions of airplane, route, season, and prewar and wartime operations."
Date: September 1948
Creator: Walker, Walter G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of the Creep Behavior of a Square Plate Loaded in Edge Compression

Description: From Introduction: "In reference 1 results of creep tests and empirical method for predicting collapse times are presented for plates loaded in compression on two opposite edges and with the remaining edges unloaded and supported in V-groove fixtures. Other approximate methods for handling plates having types of edge support are suggested in reference 2; however, experimental verification for these methods is quite limited. In reference 3 an analysis based on small-deflection theory is made of … more
Date: September 1958
Creator: McComb, Harvey G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An analysis of the effect of lift-drag ratio and stalling speed on landing-flare characteristics

Description: From Introduction: "The flare assumed is based primarily on reference 1, in which information permitting calculation of the flare characteristics of an airplane was obtained from flight tests. The results of calculations for airplanes having constant lift-drag ratio during the flare are plotted in chart form."
Date: September 1949
Creator: Lovell, J. Calvin & Lipson, Stanley
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of the Horizontal-Tail Loads Measured in Flight on a Multiengine Jet Bomber

Description: "The primary objectives of the present paper are to report the horizontal-tail-loads measurements for configuration B which have not previously been reported and to summarize the horizontal-tail-loads results obtained with both configurations. The manner in which the aerodynamic-loads data were analyzed to include structural temperature effects and fuselage flexibility effects constitutes an important part of the present paper" (p. 1).
Date: September 1955
Creator: Aiken, William S., Jr. & Wiener, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An Analysis of Turbojet-Engine-Inlet Matching

Description: From Introduction: "This report presents a method of representing inlet air-flow capacities by the same parameter used to represent engine air-flow requirements so that the determination of the inlet operation condition at the match point can be simplified. Methods for analyzing the inlet geometric variations required to improve the power-plant performance at the match point are discussed and several examples are presented to illustrate the technique."
Date: September 1953
Creator: Wyatt, DeMarquis D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Turbulent Flow and Heat Transfer in Noncircular Passages

Description: From Introduction: "In reference 1, wall temperature distributions for turbulent flow in rectangular and triangular ducts were calculated by using experimental velocity distributions and average heat-transfer coefficients, together with assumed similarity of the wall heat-transfer and wall shear-stress variations; no attempt was made to calculate either the heat-transfer coefficients or the velocity and temperature distributions in the fluid field. Some calculations of velocity and shear-stress… more
Date: September 1958
Creator: Deissler, Robert G. & Taylor, Maynard F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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