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Technical Report Archive and Image Library
148
Office of Scientific & Technical Information Technical Reports
108
National Advisory Committee for Aeronautics Collection
92
TRAIL Microcard Collection
31
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4
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1
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1
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1
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NACA Research Memorandums
61
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26
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17
Trace elements investigations report
13
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9
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9
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5
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262 Matching Results
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Investigation of a 1/22-Scale of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Static Longitudinal Stability and Control and Performance Characteristics at Transonic Speeds
Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.
Date:
April 26, 1956
Creator:
Luoma, Arvo A.
Object Type:
Report
System:
The UNT Digital Library
Some Flight Data for the Chance Vought Regulus 2 Missile
Report discussing tests of a model of the Chance Vought Regulus II missile to determine the lift, static stability, dynamic stability, trim, duct information, and drag for a range of Mach numbers.
Date:
April 23, 1956
Creator:
Wineman, Andrew R.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96
Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Date:
April 24, 1956
Creator:
Hadaway, William M.
Object Type:
Report
System:
The UNT Digital Library
An Analysis of Air-turborocket Engine Performance Including Effects of Component Changes
Report presenting analytical estimates of the thrust, efficiency, drag, and weight of the air-turborocket engine. The effects of changes in the engine components on design and off-design performance are emphasized. Results regarding the performance, effect of design parameters, effect of subsonic cruising Mach number, geometry variations, engine weight estimates, and comparison with turbojet engines are provided.
Date:
April 6, 1956
Creator:
Luidens, Roger W. & Weber, Richard J.
Object Type:
Report
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.
Object Type:
Report
System:
The UNT Digital Library
Vapor-Phase Oxidation and Spontaneous Ignition-Correlation and Effect of Variables
Note presenting the spontaneous ignition temperatures of eight structurally different hydrocarbons, which were correlated with the behavior of the same hydrocarbons toward vapor-phase oxidation. The results indicated that reducing the stoichiometry of a hydrocarbon-oxygen gas mixture to less than unity decreases the extent of oxidation, other conditions remaining unchanged.
Date:
April 1956
Creator:
Swarts, Donald E. & Orchin, Milton
Object Type:
Report
System:
The UNT Digital Library
Calculations of the rate of thermal dissociation of air behind normal shock waves at Mach numbers of 10, 12, and 14
Report presenting the rate equation for the dissociation of air, based on simple-collision theory, and the numerical values of the factors that enter it. The rate equation and conservation equations for a flowing dissociating gas are solved for the conditions behind normal shock waves at Mach numbers of 10, 12, and 14. Results regarding the adjustment of translation, rotation, and vibration and adjustment of dissociation are provided.
Date:
April 1956
Creator:
Wood, George P.
Object Type:
Report
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.
Object Type:
Report
System:
The UNT Digital Library
Flight investigation of the effectiveness of an automatic aileron trim control device for personal airplanes
Report presenting a flight investigation to determine the effectiveness of an automatic aileron trim control device installed in a persona airplane to augment the apparent spiral stability. The device utilizes a rate-gyro sensing element in order to switch an on-off type of control that operates the ailerons at a fixed rate through control centering springs. Results for the basic airplane, the airplane with automatic control, and the pilots' opinion of the automatic system are provided.
Date:
April 1956
Creator:
Phillips, William H.; Kuehnel, Helmut A. & Whitten, James B.
Object Type:
Report
System:
The UNT Digital Library
On Panel Flutter and Divergence of Infinitely Long Unstiffened and Ring-Stiffened Thin-Walled Circular Cylinders
Note presenting a theoretical investigation of the panel flutter and divergence of infinitely long, unstiffened and ring-stiffened thin-walled circular cylinders. Linearized unsteady potential-flow theory is utilized in conjunction with Donnell's cylinder theory to obtain equilibrium equations for panel flutter.
Date:
April 1956
Creator:
Leonard, Robert W. & Hedgepeth, John M.
Object Type:
Report
System:
The UNT Digital Library
Effect of shallow water on the hydrodynamic characteristics of a flat-bottom planing surface
Report presenting an investigation on the tank no. 2 monorail to determine the effect of shallow water on the hydrodynamic characteristics of a flat-bottom planing surface. Values of lift, drag, and trimming moment at a constant speed over a range of trim, wetted lengths, and clearances between the model and a false bottom in the tank.
Date:
April 1956
Creator:
Christopher, Kenneth W.
Object Type:
Report
System:
The UNT Digital Library
A Theory for the Elastic Deflections of Plates Integrally Stiffened on One Side
Note presenting an elastic-deflection theory for anisotropic plates which exhibit coupling between bending and stretching. The theory provides a basis for analyzing plates integrally stiffened on one side. Example calculations show that in the case of a simply supported square plate loaded in compression and with equal flexural stiffnesses in the principal directions, coupling may significantly lower the in-plane compressive load at which deflections grow rapidly.
Date:
April 1956
Creator:
Crawford, Robert F.
Object Type:
Report
System:
The UNT Digital Library
Some effects of fuselage flexibility on longitudinal stability and control
Report presenting some effects of fuselage flexibility on longitudinal stability and control of a large airplane as determined by application of a semirigid analytical technique. The consideration of fuselage flexibility appears to introduce no serious problems as far as dynamic longitudinal stability in the subcritical speed range is determined. Results regarding period and damping, longitudinal stability margins, and elevator-control motion are provided.
Date:
April 1956
Creator:
Klawans, Bernard B. & Johnson, Harold I.
Object Type:
Report
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.
Object Type:
Report
System:
The UNT Digital Library
Initial results of a flight investigation of a gust-alleviation system
Report presenting a flight investigation of a gust-alleviation system designed to alleviate normal accelerations in the frequency range of 0 to 2 cycles per second. The system is designed to improve passenger comfort in turbulent air. The system is capable of reducing the normal accelerations due to gusts by 50 percent at 0.6 cycle per second and 40 percent at a frequency of 2 cycles per second.
Date:
April 1956
Creator:
Kraft, Christopher C., Jr.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Measurements of the Aerodynamic Yawing Derivatives of a Triangular, a Swept, and an Unswept Wing Performing Pure Yawing Oscillations, With a Description of the Instrumentation Employed
Report presenting an investigation to determine the effect of motion periodicity on the aerodynamic derivatives due to yawing velocity and yawing acceleration for a 60 degree delta wing, a 45 degree sweptback wing, and an unswept wing. Results were obtained from steady-state yawing-flow tests and tests of model performing pure sinusoidal yawing oscillations. Results regarding the static longitudinal characteristics, derivatives due to yawing velocity, and derivatives due to yawing acceleration are provided.
Date:
April 2, 1956
Creator:
Queijo, M. J.; Fletcher, Herman S.; Marple, C. G. & Hughes, F. M.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Jet Effects on a Flat Surface Downstream of the Exit of a Simulated Turbojet Nacelle at a Free-Stream Mach Number of 1.39
Report presenting an investigation utilizing a blowdown-type tunnel to determine the effects of a propulsive jet on a zero angle-of-attack wing surface located in the vicinity of both a choked convergent nozzle and a convergent-divergent nozzle. Static-pressure surveys were made on a flat surface located in the vicinity of the propulsive jet. Results regaridng the jet-off and jet-on pressure coefficients, shock waves, and incremental normal force are provided.
Date:
April 2, 1956
Creator:
Bressette, Walter E. & Leiss, Abraham
Object Type:
Report
System:
The UNT Digital Library
Effect of inlet-duct length in uniform-flow field on turbojet-engine operation
Report presenting a high-pressure-ratio axial-flow turbojet engine in the altitude wind tunnel to determine the effect of inlet-duct length on engine operation. Data were obtained with a short bellmouth inlet and a 20-foot duct section of uniform diameter between the inlet and compressor. Results regarding the steady-state characteristics, acceleration characteristics, compressor stall limits, and surge characteristics are provided.
Date:
April 11, 1956
Creator:
Lubick, Robert J.; Chelko, Louis J. & Wallner, Lewis E.
Object Type:
Report
System:
The UNT Digital Library
Three-dimensional transonic flow theory applied to slender wings and bodies
The present paper re-examines the derivation of the integral equations for transonic flow around slender wings and bodies of revolution, giving special attention to conditions resulting from the presence of shock waves and to the reduction of the relations to the special forms necessary for the discussion of sonic flow, that is, flow at free-stream Mach number 1.
Date:
April 2, 1956
Creator:
Heaslet, Max A. & Spreiter, John R.
Object Type:
Report
System:
The UNT Digital Library
An evaluation of four experimental methods for measuring mean properties of a supersonic turbulent boundary layer
From Summary: "Surveys were made through a turbulent boundary layer on a flat plate by means of a pitot probe, an x-ray densitometer, and hot-wire and cold-wire probes. Results from these surveys were analyzed to determine (a) the reliability of the basic data and hence the methods by which they were obtained, and (b) how well the actual distributions of properties in the boundary layer compare with those commonly assumed in semiempirical and theoretical analyses. All surveys were made at the same longitudinal station on the flat plate. The tests were conducted in a an 8- by 8-inch supersonic nozzle. The free-stream Mach number was 3.03 and the Reynolds number was approximately 210,000 based on boundary-layer thickness."
Date:
April 19, 1956
Creator:
Nothwang, George J.
Object Type:
Report
System:
The UNT Digital Library
Fuselage side inlets : a study of some factors affecting their performance and a comparison with nose inlets
Report presenting basic principles affecting the performance of side-inlet air-induction systems as well as an examination of the performance of several fuselage side inlets and a comparison with nose inlets. Methods for improving the performance of both types of inlets are reviewed.
Date:
April 2, 1956
Creator:
Mossman, Emmet A.; Pfyl, Frank A. & Lazzeroni, Frank A.
Object Type:
Report
System:
The UNT Digital Library
Flight investigation of the effect of vertical-tail size on the rolling behavior of a swept-wing airplane having lateral-longitudinal coupling
Report presenting flight testing over a range of Mach numbers to determine the rolling behavior of a swept-wing airplane with lateral-longitudinal coupling. Results regarding the size of the tail area, speed effects, engine gyroscopic effects, and wing-tip extensions are provided.
Date:
April 10, 1956
Creator:
Finch, Thomas W.; Peele, James R. & Day, Richard E.
Object Type:
Report
System:
The UNT Digital Library
Experimental Results From a Test in Rough Air at High Subsonic Speeds of a Tailless Rocket Model Having Cruciform Triangular Wings, and a Note on the Calculation of Mean Square Loads of Aircraft in Continuous Rough Air
Report presenting results of testing of a rocket model with cruciform 60 degree triangular wings in continuous rough air at transonic speeds. The wing arrangement tested appears to be useful for improving the accuracy of the results. Results regarding the characteristics of the rough-air response, variation of acceleration with Mach number, and evaluation of the cruciform arrangement are provided.
Date:
April 13, 1956
Creator:
Vitale, A. James & Mitchell, Jesse L.
Object Type:
Report
System:
The UNT Digital Library
Evaluation of an automatic inlet-pressure control valve for study of transient engine performance characteristics
Report presenting an evaluation of data obtained with an automatic constant inlet-pressure control valve designed to facilitate the study of transient engine performance characteristics in the altitude wind tunnel. The engine characteristics obtained by use of the pressure valve were compared with those obtained with a bellmouth inlet operating in simulated free-stream conditions.
Date:
April 6, 1956
Creator:
Wallner, Lewis E.; Lubick, Robert J. & Bloomer, Harry E.
Object Type:
Report
System:
The UNT Digital Library