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Full-Scale Free-Jet Investigation of a Two-Shock Side-Inlet Diffuser at Mach 2.75 and a Comparison With a Single-Shock Diffuser

Description: Memorandum presenting a full-scale free-jet investigation of a two-shock side-inlet diffuser at Mach umber 2.75 in an altitude test chamber. Data were obtained over ranges of free-stream total pressure and temperature. Results regarding diffuser mass-flow ratio, critical pressure recovery, diffuser static-pressure variation, and diffuser-outlet flow conditions are provided.
Date: April 24, 1957
Creator: McAulay, John E.
Partner: UNT Libraries Government Documents Department

Free-Jet Performance Configurations of the XRJ43-MA-3 Ram-Jet Engine

Description: "A free-jet investigation of the performance of the XRJ43-MA-3 ram-jet engine has been conducted in an altitude test chamber at the NACA Lewis Laboratory. It is the purpose of this report to compare the performance and rich blow-out limits of the various engine configurations and diffuser orientations with the basic or standard engine configuration" (p. 1).
Date: August 29, 1955
Creator: McAulay, John E. & Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

Altitude Component Performance of the YJ73-GE-3 Turbojet Engine

Description: Memorandum presenting an investigation to determine the altitude performance characteristics of the YJ73-GE-3 turbojet engine in an altitude chamber. The component performance was determined at two positions of the inlet guide vanes over a range of engine speeds, exhaust-nozzle areas, and flight conditions. Results regarding compressor performance, combustor performance, turbine performance, and altitude performance of components at rated conditions are provided.
Date: January 10, 1955
Creator: McAulay, John E. & Campbell, Carl E.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of Performance Characteristics of a J47D Prototype (RX1-1) Turbojet Engine With Variable-Area Exhaust Nozzle

Description: Performance of a J47D (RX1-1) turbojet engine equipped with afterburner, variable-area exhaust nozzle, and integrated electronic control was determined over a range of flight conditions. These data were obtained with the electronic control both operative and inoperative. For operation with scheduled exhaust nozzle area, the minimum specific fuel consumption of 1.15 pounds of fuel per hour per pound of net thrust occurred at about 7200 rpm at altitudes from 5000 to 25,000 feet at a flight Mach number of 0.19.
Date: September 5, 1951
Creator: Conrad, E. William & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Preliminary Transient Performance Data on the J73 Turbojet Engine, 3: Altitude, 45,000 Feet

Description: "A program was undertaken to determine the J73 turbojet engine compressor stall and surge characteristics and combustor blow-out limits encountered during transient engine operation. Data were obtained in the form of oscillograph traces showing the time history of several engine parameters with changes in engine fuel flow. The data presented in this report are for step and ramp changes in fuel flow at an altitude of 45,000 feet and flight Mach numbers of 0 and 0.8" (p. 1).
Date: July 16, 1953
Creator: McAulay, John E. & Wallner, Lewis E.
Partner: UNT Libraries Government Documents Department

Some Operating Experience and Problems Encountered During Operation of a Free-Jet Facility

Description: During a free-jet investigation of a 28-inch ram-jet engine at a Mach number of 2.35, flow pulsation at the engine inlet were discovered which proved to have an effect on the engine performance and operational characteristics, particularly the engine rich blowout limits. This report discusses the finding of the flow pulsations, their elimination, and effect. Other facility characteristics, such as the establishment of flow simulation and the degree of subcritical operation of the diffuser, are also explained.
Date: February 13, 1957
Creator: McAulay, John E. & Prince, William R.
Partner: UNT Libraries Government Documents Department

Some Altitude Operational Characteristics of a Prototype Iroquois Turbojet Engine, COORD. NO. AF-P-6

Description: The evaluation of the altitude operational characteristics was part of the over-all investigation of the early developmental Iroquois engine. Engine steady-state windmilling characteristics were evaluated over a range of flight Mach numbers from 0.48 to 1.72 at altitudes of 35,000 and 50,000 feet. Engine altitude ignition limits were obtained over a range of flight Mach numbers from 0.5 to 1.5 with the standard engine ignition system and also with an oxygen boost system. A short investigation of high-speed altitude reignition following combustor blowout was conducted.
Date: June 17, 1958
Creator: Peters, Daniel J. & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Compressor Performance Characteristics of a Python Turbine-Propeller Engine Investigated in Altitude Wind Tunnel

Description: Report presenting an investigation in the altitude wind tunnel to determine the performance of the Python turbine-propeller engine. Compressor-performance data were obtained for a range of simulated altitudes at a single cowl-inlet ram pressure ratio while the engine was run over its full operable range of engine speeds. Results regarding the deterioration of compressor performance, compressor performance, including efficiency and performance maps, and velocity and static-pressure profiles are provided.
Date: May 1, 1951
Creator: Jansen, Emmert T. & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Altitude Wind Tunnel Investigation of the Prototype J40-WE-8 Turbojet Engine Without Afterburner

Description: From Introduction: "As part of a comprehensive investigation of the J40 turbojet engine conducted at the NACA Lewis altitude wind tunnel, the steady-state engine performance of the prototype J40-WE-8 turbojet engine without afterburner was obtained and is presented herein. A basic redesign of the compressor and other modifications in the compressor and the combustor were incorporated in the XJ40-WE-6 turbojet engine (references 2 and 3). In this report the modified engine is designated "the prototype J40-WE-8 without afterburner."
Date: August 6, 1953
Creator: McAulay, John E. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department

Altitude-Wind-Tunnel Investigation of Turbine Performance in J47 Turbojet Engine

Description: From Introduction: "Performance data are presented in this report to show the characteristics of the turbine operating as an integral part of the engine. Typical results are graphically presented to show the effects of changes in altitude, flight Mach number, and exhaust-nozzle-outlet area on turbine performance. All turbine-performance data obtained are given in tabular form."
Date: September 21, 1950
Creator: Thorman, H. Carl & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Altitude Performance Characteristics of Tail-Pipe Burner With Converging Conical Burner Section on J47 Turbojet Engine

Description: From Introduction: "The effect of flame-holder and fuel-system design on the burner performance and the effect of altitude and flight Mach number on over-all performance with a fixed-area exhaust nozzle are reported in reference 1 to 4. Altitude performance characteristics of a tail-pipe burner having a converging conical burner section are presented in this report. Tail-pipe burner performance at several flight conditions is given in both tabular and graphical forms and compared with performance of the standard engine and of the tail-pipe burner reported in reference 2."
Date: December 19, 1950
Creator: Prince, William R. & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Preliminary Free-Jet Performance of XRJ43-MA-3 Flight-Weight Ram-Jet Engine at Mach Numbers of 2.35, 2.50, and 2.70

Description: From Summary: "The performance of the XRJ43-MA-3 flight-weight ram-jet engine has been investigated in a free-jet facility as part of the development program for the "Bomarc," ram-jet powered, interceptor-type missile. The engine performance was obtained at Mach numbers of 2.35, 2.50, and 2.70, altitudes from 50,000 to 75,000 feet, and Miami hot day and cold day inlet temperatures at an angle of attack of +4 deg. At each flight condition investigated, the engine control set an inner-ring fuel flow which was held constant as outer-ring fuel flow was varied."
Date: November 18, 1955
Creator: McAulay, John E. & Prince, William R.
Partner: UNT Libraries Government Documents Department

Effects of Inlet-Flow-Air Distortion on Steady-State Altitude Performance of an Axial-Flow Turbojet Engine

Description: Report presenting the effects of inlet-air-flow distortion on the steady-state performance of a current axial-flow turbojet engine studied in an NACA altitude test chamber at a range of altitudes and simulated Mach number of 0.8. Radial distortions of various shapes up to 22 percent of the average engine-inlet total pressure and circumferential distortions up to 26 percent were imposed. Results regarding propagation through the engine, compressor-interstage performance and stall, effects on component performance, effects on overall engine performance, and effect on compressor blade vibration are provided.
Date: September 27, 1955
Creator: Conrad, E. William; Hanson, Morgan P. & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Altitude Performance Investigation of Two Single-Annular Type Combustors and the Prototype J40-WE-8 Turbojet Engine Combustor With Various Combustor-Inlet Air Pressure Profiles

Description: Report presenting data obtained three single annular-type combustors with different combustor inlet-air pressure profiles over a range of engine speeds. Results regarding effect of changing combustor inlet-air pressure profile and hole geometry on combustor performance, performance of the prototype J40-WE-8 turbojet engine combustor, correlation of combustion efficiency with engine fuel-air ratio and combustion parameter, and comparison of several combustors from different turbojet engines are provided.
Date: May 29, 1953
Creator: Sobolewski, Adam E.; Miller, Robert R. & McAulay, John E.
Partner: UNT Libraries Government Documents Department

Performance of the Components of the XJ34-WE-32 Turbojet Engine Over a Range of Engine and Flight Conditions

Description: Performance of the compressor, combustor, and turbine operating as integral parts of the XJ34-WE-32 turbojet engine was determined in the Lewis altitude wind tunnel over a range of altitudes from 5000 to 55,000 feet and flight Mach numbers from 0.28 to 1.05. Data were obtained for each of four exhaust-nozzle areas and are presented in graphical and tabular form.
Date: June 9, 1952
Creator: McAulay, John E.; Sobolewski, Adam E. & Smith, Ivan D.
Partner: UNT Libraries Government Documents Department