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148
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108
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92
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61
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26
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262 Matching Results
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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
Component Performance Investigation of J71 Experimental Turbine 4 - Effect of First-Stator Adjustment; Over-All Performance of J71-97 Turbine With 132-Percent-Design Stator Area
An experimental invesitgation of the effect of increasing the first-stator area of the J71-97 experimental three-stage turbine from 97 percent of design to 132 percent revealed (1) the maximum efficiency obtained decreased from 0.891 to 0.869, (2) the choking equivalent weight flows increased by approximately 13.6 percent, and (3) at the turbine match points required to maintain the compressor at constant design equivalent conditions the turbine efficiency decreased from 0.87 to 0.86.
Date:
April 17, 1956
Creator:
Davison, Elmer H.; Petrash, Donald A. & Schum, Harold J.
Object Type:
Report
System:
The UNT Digital Library
On the Instability of Methods for the Integration of Ordinary Differential Equations
Memorandum presenting an investigation of the instability of methods for the integration of ordinary differential equations. Examples and a criterion for stability of integration methods is provided. The criterion is applied to well-known integration formulas.
Date:
April 1956
Creator:
Rutishauser, Heinz
Object Type:
Report
System:
The UNT Digital Library
Static Longitudinal Stability Characteristics of a Series of 90-Millimeter Artillery Shells at Mach Numbers of 0.8, 0.9, 1.0, and 1.2
Wind-tunnel tests have been made to determine the static longitudinal stability of several models of a short-range artillery shell at Mach numbers of 0.8, 0.9, 1.0, and 1.2. The results of the tests indicated that the best of the spool-shaped shells was statically stable in pitch at all test Mach numbers for an angle-of-attack range up to about 10 degrees. The best of the finned shells was stable to a maximum angle of attack of about 6 degrees.
Date:
April 10, 1956
Creator:
Spooner, Stanley H.
Object Type:
Report
System:
The UNT Digital Library
Component Performance Investigation of J71 Experimental Turbine 3 - Effect of Third-Stage Shrouding on Over-All Performance
"A negligible effect on turbine efficiency and only a small decrease in turbine weight flow were observed when the J71 experimental turbine with 97-percent-design stator areas was modified to include shrouding of the third-stage rotor" (p. 1).
Date:
April 17, 1956
Creator:
Petrash, Donald A.; Schum, Harold J. & Davison, Elmer H.
Object Type:
Report
System:
The UNT Digital Library
A Transonic Wind-Tunnel Investigation of a Seaplane Configuration having a 40 Deg Sweptback Wing, TED No. NACA DE 387
From Summary: "During the course of an aerodynamic loads investigation of a model of the Martin XP6M-1 flying boat in the Langley 16-foot transonic tunnel, longitudinal-aerodynamic-performance information was obtained. Data were obtained at speeds up to and exceeding those anticipated for the seaplane in level flight and included the Mach number range from 0.84. to 1.09. The angle of attack was varied from -2deg to 6deg and the average Reynolds number, based on wing mean aerodynamic chord, was about 3.7 x 10(exp 6)."
Date:
April 6, 1956
Creator:
Hieser, Gerald; Kudlacik, Louis & Gray, W. H.
Object Type:
Report
System:
The UNT Digital Library
Component Performance Investigation of J71 Experimental Turbine 2 - Internal-Flow Conditions with 97-Percent-Design Stator Areas
"An experimental investigation of the internal-flow conditions of a J71 experimental turbine equipped with 97-percent-design stator areas was conducted at equivalent design speed and near equivalent design work. The results of the investigation indicate that the stage work distribution closely approximates design, the actual distribution being 44.1, 33.4, and 22.5 percent for the first, second, and third stages, respectively. The first-, second-, and third-stage efficiencies were 0.894, 0.858, and 0.792, respectively" (p. 1).
Date:
April 11, 1956
Creator:
Rebeske, John J., Jr. & Petrash, Donald A.
Object Type:
Report
System:
The UNT Digital Library
Component performance investigation of J71 experimental turbine 1: Over-all performance with 97-percent-design stator areas
From Summary: "The over-all component performance characteristics of a J71 experimental three-stage turbine with 97 percent design stator areas were determined over a range of speed and pressure ratio at inlet-air conditions of approximately 35 inches of mercury absolute and 700 degrees R. The turbine break internal efficiency at design operating conditions was 0.877; the maximum efficiency of 0.886 occurred at a pressure ratio of 4.0 at 120 percent of design equivalent rotor speed. In general, the turbine yielded a wide range of efficient operation, permitting flexibility in the choice of different modes of engine operation."
Date:
April 11, 1956
Creator:
Schum, Harold J. & Davison, Elmer H.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Ni(sub 3)Al Phrase of Nickel-Aluminum Alloys
Note presenting an investigation to determine the effects of homogenization treatments and of composition on the tensile properties of as-cast alloys in the Ni(sub 3)Al-intermetallic-phase region. Results regarding the effects of the casting method, hot-workability of stoichiometric Ni(sub 3)Al, mechanical properties, and microstructure of Ni(sub 3)Al are provided.
Date:
April 1956
Creator:
Grala, Edward M.
Object Type:
Report
System:
The UNT Digital Library
Self shielding in rectangular and cylindrical geometries
Report presenting the steady-state diffusion and transport theory solutions of several self-shielding problems for multiregion cells of rectangular and cylindrical geometries. Results regarding the rectangular case and cylindrical case are provided.
Date:
April 1956
Creator:
Schneider, Harold; Saper, Paul G. & Kadow, Charles F.
Object Type:
Report
System:
The UNT Digital Library
Method of calculating core dimensions of crossflow heat exchanger with prescribed gas flows and inlet and exit states
Report presenting a calculation procedure by which the dimensions of the core of a gas-to-gas crossflow heat exchanger with prescribed heat-transfer surface can be determined rapidly. The procedure is based on a number of charts that may be prepared for each surface with prescribed entrance conditions, pressure drops, and temperature changes.
Date:
April 1956
Creator:
Eckert, E. R. G. & Diaguila, Anthony J.
Object Type:
Report
System:
The UNT Digital Library
Discharge coefficients for combustor-liner air-entry holes 1: Circular holes with parallel flow
Report presenting an experimental investigation to determine the effects of various geometric and flow factors on the discharge coefficients for circular holes with flow parallel to the plane of the hole. The geometric and flow factors considered were hole diameter, wall thickness at the hole, parallel-flow duct height, boundary-layer thickness, parallel-flow velocity, static-pressure level, and pressure ratio across the test hole.
Date:
April 1956
Creator:
Dittrich, Ralph T. & Graves, Charles C.
Object Type:
Report
System:
The UNT Digital Library
Theoretical pressure distributions for some slender wing-body combinations at zero lift
Report presenting pressure distributions calculated for some symmetrical wing-body combinations at zero lift. Of particular interest is the effect of indenting the body on the distribution of pressure over the wing.
Date:
April 1956
Creator:
Byrd, Paul F.
Object Type:
Report
System:
The UNT Digital Library
Investigation at high subsonic speeds of a body-contouring method for alleviating the adverse interference at the root of a sweptback wing
Report presenting an investigation of a body-contouring method for alleviating adverse interference of a high-aspect-ratio sweptback wing at high speeds. Modifying the body shape did not significantly affect the aerodynamic characteristics at subcritical speeds, but beneficial results were obtained at free-stream Mach numbers above critical. Results regarding force and pressure studies are provided.
Date:
April 1956
Creator:
McDevitt, John B. & Haire, William M.
Object Type:
Report
System:
The UNT Digital Library
Determination of vortex paths by series expansion technique with application to cruciform wings
Report presenting a series method of determining two-dimensional vortex paths is considered and applied to the computation of vortex positions behind a slender equal-span cruciform wing at any angle of bank as a function of the distance behind the trailing edge.
Date:
April 1956
Creator:
Alksne, Alberta Y.
Object Type:
Report
System:
The UNT Digital Library
Some effects of guide-vane turning and stators on the rotating stall characteristics of a high hub-tip ratio single-stage compressor
Report presenting an investigation of the rotating stall characteristics of several guide-vane-rotor and guide-vane-rotor-stator configurations. Guide vanes of 4 different turning angles were tested. Results regarding initial rotating stall point, number of stall zones formed, surge, flow fluctuations due to rotating stall, pressure fluctuations due to rotating stall, and stall propagation rate are provided.
Date:
April 1956
Creator:
Costilow, Eleanor L. & Huppert, Merle C.
Object Type:
Report
System:
The UNT Digital Library
Results of a flight investigation to determine the zero-lift drag characteristics of a 60 degree delta wing with NACA 65-006 airfoil section and various double-wedge sections at Mach numbers from 0.7 to 1.6
Report presenting results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models with 60 degree sweptback delta wings presented for a range of Mach numbers. The airfoil sections tested included the NACA 65-006 and a series of double-wedge sections with various thicknesses and positions of maximum thickness.
Date:
April 1956
Creator:
Welsh, Clement J.
Object Type:
Report
System:
The UNT Digital Library
Investigation by the transonic-bump method of a 35 degree sweptback semispan model equipped with a flap operated by a series of servovanes located ahead of and geared to the flap
Report presenting an investigation in the 7- by 10-foot tunnel to determine the feasibility of using a serovane control at high-subsonic and low-transonic speeds. The control could presumedly be deflected with relatively low control forces compared to flap-type controls. Through the range tested, the servovane control produced increments of lift, pitching moment, and rolling moment int he correct direction over most of the angle-of-attack range tested.
Date:
April 1956
Creator:
Phillips, William H. & Thompson, Robert F.
Object Type:
Report
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.
Object Type:
Report
System:
The UNT Digital Library
Perforated sheets as a porous material for distributed suction and injection
Report presenting measurements of the resistance to air flow of a series of perforated metal sheets with open areas ranging from less than 1 percent up to 41 percent. The results showed that the permeability of a perforated sheet is governed principally by its open-area ratio.
Date:
April 1956
Creator:
Dannenberg, Robert E.; Gambucci, Bruno J. & Weiberg, James A.
Object Type:
Report
System:
The UNT Digital Library
Performance and Operational Studies of a Full-Scale Jet-Engine Thrust Reverser
Note presenting an axial-flow turbojet engine equipped with a hemispherical target thrust reverser that was pylon-mounted beneath the wing of a cargo airplane. Results regarding the performance of full-depth hemisphere, operational problems, and performance of modified hemisphere are provided.
Date:
April 1956
Creator:
Kohl, Robert C.
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