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Performance of Inconel 550 Turbine Blades in a Turbojet Engine and Effects of Different Forging Temperatures and Heat Treatments

Description: Report presenting an investigation to determine the effects of forging at 1950 degrees and 2150 degrees Fahrenheit as well as the effects of several heat treatments on the performance of Inconel 550 in a turbojet engine. Differences in engine performance of the different turbine blades could not be associated with consistent differences in microstructure or grain size. Results regarding blade performance, blade elongation during engine operation, microstructure of as-heat-treated blades, grain … more
Date: August 16, 1955
Creator: Gyorgak, C. A.; Johnston, J. R. & Weeton, J. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Preliminary Report on Experimental Investigation of Engine Dynamics and Controls for a 48-Inch Ram-Jet Engine

Description: Engine dynamics and controls data are presented for a ram-jet engine which was operated in a free-jet facility at a Mach number of 2.76 and altitudes from 68,000 to 82,000 feet. The predominant engine dynamic characteristics was dead time, with values ranging from 0.018 to 0.053 sec. The control systems were designed to hold a constant ratio of a diffuser static pressure to an inlet-cone reference static pressure.
Date: March 16, 1956
Creator: Vasu, George; Hart, Clint E. & Dunbar, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of impulse-type supersonic compressor with hub-tip ratio of 0.6 and turning to axial direction 2: stage performance with three different sets of stators

Description: Report presenting an impulse-type supersonic compressor designed for turning to the axial direction that was tested in air with three different sets of stator blades at eight angle settings.
Date: August 16, 1955
Creator: Wilcox, Ward W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of air-side performance of liquid-metal to air heat exhangers

Description: Report describing an experiment to obtain heat-transfer and pressure-drop data for the air side of a liquid-metal to air, shell-and-tube heat exchanger. Testing was conducted in a 500 kilowatt facility using sodium as the shell-side heating fluid. Results regarding the shell-and-tube heat exchanger and finned-tube heat exchanger friction factor are provided.
Date: March 16, 1956
Creator: Gedeon, Louis; Conant, Charles W. & Kaufman, Samuel J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Characteristics of a Hydraulic Control Determined from Transient Data Obtained with a Turbojet Engine at Altitude

Description: Memorandum presenting characteristics of a hydraulic control as determined by analyzing transient data obtained with a turbojet engine operating in the altitude wind tunnel. The excellent overall performance of the speed control is attributed to the elimination of large lags in the control system, thereby permitting the use of relatively high loop gains while still maintaining satisfactory damping in transients. Some information regarding the frequency-response analysis of speed control, simula… more
Date: June 16, 1954
Creator: Vasu, George; Hinde, William L. & Craig, R. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Static longitudinal aerodynamic characteristics of a 52 degree sweptback wing of aspect ratio 2.88 at Reynolds numbers from 2,000,000 to 11,000,000

Description: Report presenting the effects of changes in Reynolds number on the longitudinal aerodynamic characteristics of a 52 degree sweptback wing with an aspect ratio of 2.88 and NACA 64(sub 1)-112 airfoil sections. The model was tested with the leading edge both smooth and rough. Results regarding force and pitching-moment results, flow observations, and discussion of force and moment characteristics are provided.
Date: November 16, 1948
Creator: Fitzpatrick, James E. & Foster, Gerald V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Study of the canard configuration with particular reference to transonic flight characteristics and low-speed characteristics at high lift

Description: Report presenting a study of the flight characteristics of the canard configuration at transonic and supersonic speeds. Known problems concerning the low-speed characteristics of the canard are also investigated.
Date: November 16, 1949
Creator: Mathews, Charles W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance investigation of can-type combustor 1: instrumentation, altitude operational limits and combustion efficiency

Description: Report presenting an investigation of the performance of a single can-type combustor designed for a turbojet engine equipped with an 11-stage axial-flow compressor and a single-stage turbine. The investigation was conducted to determine the altitude operational limits of the engine for two fuels, combustion efficiencies at various simulated conditions of altitude and engine speed, combustor-outlet temperature distribution for several altitudes at constant engine speed, and combustor total-press… more
Date: September 16, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wind-Tunnel Investigation of Horizontal Tails 4: Unswept Plan Form of Aspect Ratio 2 and a Two-Dimensional Model

Description: Memorandum presenting the results of a wind-tunnel investigation of the low-speed aerodynamic characteristics of a horizontal-tail model of aspect ratio 2 with an unswept plan form and of a two-dimensional model. The two-dimensional model provides data which can be used as the basis for computing the three-dimensional lift and hinge-moment parameters by the lifting-surface-theory procedure. Results regarding the effectiveness and hinge-moment parameters, static longitudinal stability, scale eff… more
Date: December 16, 1948
Creator: Dods, Jules B., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The effects of Reynolds number at Mach numbers up to 0.94 on the loading on a 35 degree swept-back wing having NACA 65(1)A012 streamwise sections

Description: Report presenting an investigation of the effects of a variation of Reynolds number on the forces, moments, and surface pressures on a semispan model of a wing with 35 degrees of sweepback, an aspect ratio of 5, a taper ratio of 0.7, and the NACA 65(sub 1)A012 section in planes parallel to the plane of symmetry.
Date: June 16, 1952
Creator: Tinling, Bruce E. & Lopez, Armando E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Effect of Surface Roughness on the Performance of a 23 Degree Conical Diffuser at Subsonic Mach Numbers

Description: Report of an investigation to determine the effect of surface roughness on the performance of a 23 degree conical diffusers with 2:1 ratio of exit to inlet area and a constant-area tail pipe. Information about the pressure survey results, including total-pressure-loss coefficient, diffuser effectiveness, and boundary-layer profiles is provided.
Date: January 16, 1952
Creator: Persh, Jerome
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effects of Plan Form, Airfoil Section, and Angle of Attack on the Pressures Along the Base of Blunt-Trailing-Edge Wings at Mach Numbers of 1.41, 1.62, and 1.96

Description: Memorandum presenting an investigation at Mach numbers of 1.41, 1.62, and 1.96 to determine the effects of airfoil section and wing plan form on the pressures acting on the base of blunt-trailing-edge wings operating through an angle-of-attack range. The investigation included two groups of untapered wings of aspect ratio 2.7, with one group being unswept and the other with 45 degrees of sweepback. Results regarding the effects of wing location and body size, spanwise variations of base pressur… more
Date: September 16, 1952
Creator: Goin, Kennith L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Dynamic corrosion of a stainless-steel specimen by water at 500 degrees F using a toroid circulating apparatus

Description: A slug of air-saturated distilled water was circulated for 317 hours at a velocity of 15 feet per second in an AISI 347 stainless-steel toroid with a wall temperature of 500 F and a 30 F difference in temperature between the hot and cold sections. The depth of corrosion layer was 0.001 inch (0.028 in./yr) in the hot sector and 0.0007 inch (0.019 in./yr) in the cold sector; no mass transfer was observed. The results of gas,water,and X-ray diffraction analyses are given together with photomicrogr… more
Date: July 16, 1952
Creator: Desmon, Leland G. & Mosher, Don R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance characteristics at Mach numbers to 2.0 of various types of side inlets mounted on fuselage of proposed supersonic airplane 3: normal wedge inlet with semicircular cowl

Description: Report presenting an investigation of inlets utilizing two-dimensional compression wedges mounted normal to the fuselage surface with ram-type scoops for partial removal of the boundary layer. Two compression-wedge angles were included to simulate fixed positions of a variable-geometry configuration. Results regarding supersonic performance characteristics and subsonic and take-off performance characteristics are provided.
Date: October 16, 1952
Creator: Esenwein, Fred T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Results of flight tests to determine the drag of finite-length cylinders at high Reynolds numbers for a Mach number range of 0.5 to 1.3

Description: Report presenting the results of a free-flight investigation to determine the drag of circular, finite-length cylinders for a range of Mach numbers. For supersonic speeds, the drag of circular cylinders was found to be largely independent of fineness ratio and Reynolds number.
Date: June 16, 1952
Creator: Welsh, Clement J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Geometry on Secondary Flows in Blade Rows

Description: Memorandum presenting an investigation of the influence of blade-row geometry on secondary flows in a two-dimensional cascade by varying independently stagger angle, aspect ratio, solidity, and angle of attack and by providing blade fillets. Stagger angle and aspect ratio had no appreciable effect on this secondary flow, whereas solidity and angle of attack did affect the flow patterns indicating the turning as a major parameter.
Date: October 16, 1952
Creator: Hansen, A. G.; Costello, G. R. & Herzig, H. Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Engine and Control Limits on Steady-State and Transient Performance of Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Memorandum presenting steady-state and transient characteristics of the J34-WE-32 turbojet engine with electronic power regulator as obtained in the altitude wind tunnel to determine the effects of engine and control limits on the performance. Limits on the fuel valve and exhaust nozzle area influence any schedule of speed and temperature. Results regarding the effect of limits on operating schedule, effect of altitude on safe operating range, effect of minimum fuel flow settings on transient p… more
Date: January 16, 1953
Creator: Vasu, George & Hinde, William L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Low-Lift Buffet Characteristics Obtained From Flight Tests of Unswept Thin Intersecting Surfaces and of Thick 35 Degree Sweptback Surfaces

Description: Report presenting testing of two rocket-propelled research models to determine the effect of the intersection of thin aerodynamic surfaces and the effect of moderate sweepback of thick aerodynamic surfaces on low-lift buffeting. Results regarding trim changes and drag are also provided. It was discovered that low-lift buffeting may be induced at high subsonic speeds by interference due to the intersection of thin aerodynamic surfaces.
Date: January 16, 1953
Creator: Mason, Homer P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Influence of a canard-type control surface on flow field in vicinity of symmetrical fuselage at Mach numbers 1.8 and 2.0

Description: Report presenting an experimental investigation of the flow field downstream of a canard-type control surface and in the vicinity of a symmetrical body in the 8- by 6-foot supersonic tunnel at Mach numbers of 1.8 and 2.0. The results indicated severe total pressure losses and large flow deflections in the control surface wake.
Date: July 16, 1952
Creator: Wise, George A. & Dryer, Murray
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

An experimental investigation of the zero-lift pressure distribution over a wedge airfoil in closed, slotted, and open-throat tunnels at transonic Mach numbers

Description: Report presenting pressure distributions and Schileren photographs of the flow around a 10-percent-thick diamond airfoil at zero lift in two-dimensional closed, slotted, and open-throat tunnels. Results regarding the effect of slot area ratio and effect of slot spacing are provided.
Date: June 16, 1952
Creator: Nelson, William J. & Bloetscher, Frederick
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Preliminary Investigation of the Static and Dynamic Longitudinal Stability of a Grunberg Hydrofoil System

Description: "A preliminary investigation has been made in order to determine the static and dynamic longitudinal stability characteristics and the force characteristics of a Grunberg hydrofoil system comprising a main lifting hydrofoil and planing-surface stabilizers. The tests showed that a rearward movement of the center of gravity decreased the static and dynamic stability but increased the lift-drag ratio. In smooth water, adequate static stability was observed for all conditions tested" (p. 1).
Date: September 16, 1952
Creator: Land, Norman S.; Chambliss, Derrill B. & Petynia, William W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Use of Fences to Increase Uniformity of Boundary Layer on Side Walls of Supersonic Wind Tunnels

Description: "An investigation of the use of solid fences installed on the side walls of a supersonic wind tunnel to retard the development of transverse flow and thus to increase the uniformity of the side-wall boundary layer is reported. Beneficial results were obtained with fences which had depths of the order of the boundary-layer displacement thickness and which followed potential-flow streamlines through the nozzle. Reduction of the number of fences on each side wall from four to two eliminated their … more
Date: July 16, 1952
Creator: Haefeli, Rudolph C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Small-Scale Transonic Investigation of the Effects of Full-Span and Partial-Leading-Edge Flaps on the Aerodynamic Characteristics of a 50 Degree 38 Foot Sweptback Wing of Aspect Ratio 2.98

Description: Memorandum presenting a small-scale investigation of the effects of full-span and partial-span leading-edge flaps on the aerodynamic characteristics of a sweptback wing in the 7- by 10-foot tunnel over a Mach number range of 0.70 to 1.10. Lift, drag, pitching moment, and bending moment were obtained for the basic wing and for the wing with full-span and partial-span leading-edge-flap deflections of approximately 3, 6, and 9 degrees.
Date: July 16, 1952
Creator: Spreeman, Kenneth P. & Alford, William J., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of air inlets at transonic and low supersonic speeds

Description: A general discussion of the air-inlet problem is presented. Recently obtained drag and pressure-recovery data for transonic-type nose, scoop, and wing-root inlets are summarized. Preliminary results concerning the performance of the sharp-edged supersonic-type inlets at transonic and subsonic speeds also are given.
Date: February 16, 1952
Creator: Nichols, Mark R. & Pendley, Robert E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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