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Airborne Reconnaissance Survey of Northwestern Arizona (Arizona Strip) and Southwestern Utah

Description: Abstract: From December 1953 to May 1954 an extensive airborne reconnaissance program was conducted in northwestern Arizona (Arizona Strip) and southwestern Utah. Five surface anomalies were detected, one of which has possible commercial value. All anomalies are within the boundaries of National Park Service jurisdiction, consequently, this report is not for public distribution until clearance is obtained from the National Park Service. A preliminary airborne reconnaissance program was also con… more
Date: August 1954
Creator: Meehan, R. J.; Lovejoy, Earl M. P. & Rambosek, A. J.
Item Type: Refine your search to only Report
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Altitude-chamber investigation of J73-GE-1A turbojet engine component performance

Description: Report presenting an investigation to determine the altitude performance characteristics of a J73-GE-1A turbojet engine conducted in an altitude chamber. The engine had a ten-percent oversize turbine-nozzle are compared with the production J73 engine. Results regarding radial pressure and temperature profiles, compressor performance, combustor performance, turbine performance, and tail-pipe-diffuser and exhaust-nozzle performance.
Date: December 9, 1954
Creator: Campbell, Carl E. & Sobolewski, Adam E.
Item Type: Refine your search to only Report
open access

Altitude investigation of 20-inch-diameter ram-jet engine with annular-piloted combustor

Description: From Introduction: "The combustor efficiency, combustor-inlet Mach number, and combustor total-pressure ratio of the annular-piloted combustor are presented herein. The effect of combustor-exit total pressure on combustor efficiency, and a comparison of configurations on the basis of specific fuel consumption are also presented."
Date: August 27, 1954
Creator: Henzel, James G. & Trout, Arthur M.
Item Type: Refine your search to only Report
open access

Altitude Investigation of Can-Type Flame Holder in 20-Inch-Diameter Ram-Jet Combustor

Description: From Introduction: "The combustor efficiency, combustor total-pressure ratio, combustor-outlet total pressure, combustor-inlet Mach number, and specific fuel consumption are presented. The effect of combustor length on efficiency and the effect of pilot operating conditions burning limits are also presented."
Date: June 3, 1954
Creator: Smolak, George R. & Wentworth, Carl B.
Item Type: Refine your search to only Report
open access

Altitude Investigation of Can-Type Flame Holder in 20-Inchdiameter Ram-Jet Combustor

Description: Memorandum presenting an investigation of a can-type flame holder employing a fuel-air-mixture control sleeve in a 20-inch-diameter ramjet combustor conducted by free-jet and direct-connect techniques at a simulated flight Mach number of 3.0 and altitudes from about 70,000 to 80,000 feet. Results regarding the effect of shortening combustion chamber and effect of pilot-burner variables are provided.
Date: June 3, 1954
Creator: Smolak, George R. & Wentworth, Carl B.
Item Type: Refine your search to only Report
open access

Altitude performance and operational characteristics of an XT38-A-2 turboprop engine

Description: From Introduction: "Reported herein are the over-all engine performance and the starting and windmilling characteristics. Data are presented in the form of performance maps at each flight condition to show the effects of altitude and flight Mach number on various engine-performance variables. The effect of engine deterioration with operating time on performance is also discussed."
Date: March 12, 1954
Creator: Essig, R. H. & Schulze, F. W.
Item Type: Refine your search to only Report
open access

Altitude Performance Characteristics of the J73-GE-1A Turbojet Engine

Description: From Introduction: "The over-all altitude-performance characteristics of this engine are reported herein, and the component performance characteristics are given in reference 1. The data are presented in the form of engine pumping characteristics to allow accurate calculation of engine performance at any operating or flight condition within the range covered by the experimental data. A curve is also presented that will allow determination of thrust in flight by the measurement of ambient static… more
Date: December 9, 1954
Creator: Campbell, Carl E. & Conrad, E. William
Item Type: Refine your search to only Report
open access

Altitude performance of compressor, turbine, and combustor components of 600-B9 turbojet engine

Description: From Introduction: "The purpose of this report is (1) to describe the performance of each component over a range of altitudes, (2) to show the effect of flight conditions on operating point of each component, and (3) to summarize briefly the effects of changes in component performance with flight condition on the over-all engine performance."
Date: March 15, 1954
Creator: Prince, William R. & Wile, Dorwin B.
Item Type: Refine your search to only Report
open access

Altitude-wind-tunnel investigation of several afterburner configurations having moderately high burner-inlet velocities

Description: From Introduction: "The screech investigation, reported in reference 1, included a large number of afterburner configurations. Several of these configurations are presented herein to show the effects of afterburner-inlet gas whirl pattern, flame-holder design, and fuel distribution on performance as determined by combustion efficiency, augmented thrust ratio, and special fuel consumption."
Date: November 17, 1954
Creator: Schulze, F. W.; Bloomer, H. E. & Miller, R. R.
Item Type: Refine your search to only Report
open access

The Ames 10- by 14-Inch Supersonic Wind Tunnel

Description: "The purpose of the present report is to describe the 10- by 14-inch supersonic wind tunnel and its operational characteristics over the nominal Mach number range from 2.7 to 6.3. Rather complete calibration data on characteristics of flow in the test section are presented and briefly discussed" (p. 2).
Date: January 1954
Creator: Eggers, A. J., Jr. & Nothwang, George J.
Item Type: Refine your search to only Report
open access

Analysis and Construction of Design Charts for Turbines with Downstream Stators

Description: From Introduction: "This paper describes the theoretical treatment that has been given the combustion process as it occurs in turbojet combustors. Various parts of this work have been previously published (refs. 1 to 3); this report presents a brief summary of this previous work together with new data which amplify the conclusions of references 1 to 3. Similar studies have been made of the ram-jet combustion process (ref. 4 and 5); however, the analysis for ram-jet combustion differs in some de… more
Date: November 18, 1954
Creator: Cavicchi, Richard H. & Constantine, Anita B.
Item Type: Refine your search to only Report
open access

Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbine for Turbojet Engines 1: Turbine Performance and Engine Weight-Flow Capacity

Description: Memorandum presenting an analysis to determine the compressor pressure ratios and specific weight flows obtainable with single-stage air-cooled turbines for both nonafterburning and afterburning turbojet engines operating at a flight Mach number of 2 in the stratosphere. Wide ranges in turbine-inlet temperature, tip speed, hub-tip radius ratio, and coolant-flow ratio were considered.
Date: May 25, 1954
Creator: Rossbach, Richard J.; Schramm, Wilson B. & Hubbartt, James E.
Item Type: Refine your search to only Report
open access

Analysis of Factors Affecting Selection and Design of Air-Cooled Single-Stage Turbines for Turbojet Engines 2: Analytical Techniques

Description: Memorandum presenting computation methods for analyzing turbojet-engine performance for a series of air-cooled nonafterburning and afterburning engines where all the engine components are simultaneously aerodynamically limited. The coolant-flow ratio was arbitrarily assigned so that the results of the analysis can be applied to any specific air-cooled blade configurations.
Date: June 21, 1954
Creator: Rossbach, Richard J.
Item Type: Refine your search to only Report
open access

Analysis of Off-Design Operation of High Mach Number Supersonic Turbojet Engines

Description: From Introduction: "Because of the lack of data on compressor characteristics at 130 or 145 percent of design equivalent rotational speed, several simplifying assumptions were made regarding the compressor characteristics during operation at equivalent rotational speeds above the design value (hereinafter called "compressor overspeeding"). In addition to results based on these assumptions, the effect of deviation from these assumptions is discussed."
Date: February 4, 1954
Creator: English, Robert E. & Cavicchi, Richard H.
Item Type: Refine your search to only Report
open access

Analysis of performance of four symmetrical-diagram-type subsonic inlet-stage axial-flow compressors

Description: Report presenting an investigation of four axial-flow single-stage compressors with a hub-tip radius ratio of 0.5 with three objectives related to the ideal symmetrical-velocity-diagram design, the comparison of blade-element turning angle and loss data with cascade data, and the validity of the simplified radial-equilibrium equation. Results regarding the overall performance, blade-element performance, and radial equilibrium considerations are provided.
Date: January 20, 1954
Creator: Jackson, Robert J.
Item Type: Refine your search to only Report
open access

An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: The following report covers an investigation that was done to supplement available experimental data on flow fields behind wings of an aircraft at supersonic speeds, as well as to furnish more quantitative information on the choice of the theoretical method for a given configuration and the accuracy to be expected when using such a method.
Date: April 21, 1954
Creator: Boatright, William B.
Item Type: Refine your search to only Report
open access

An Analysis of Pressure Studies and Experimental and Theoretical Downwash and Sidewash Behind Five Pointed-Tip Wings at Supersonic Speeds

Description: "Flow-angle and pressure surveys behind five, thin, pointed-tip wings of varying plan form have been made at Mach numbers 1.62 and 2.41. Schlieren studies at a Mach number 1.93 for the same five plan-form wings were made to illustrate the behavior of the vortex sheet. The surveys were conducted at 1.5, 3, and 4 root chords behind three triangular wings of 50 degree, 63 degree, and 72 degree leading-edge sweep angle, and behind the 50 degree triangular wing reversed" (p. 1067).
Date: January 22, 1954
Creator: Boatright, William B.
Item Type: Refine your search to only Report
open access

Analysis of rocket, ram-jet, and turbojet engines for supersonic propulsion of long-range missiles 1: rocket-engine performance

Description: Report presenting theoretical performance characteristics and estimates of effective specific impulse and weight for rocket engines serving a main and booster power plants for missiles. The fuels used included ammonia-fluorine and JP4-oxygen propellants. At extremely high altitudes, the specific impulse depends primarily on the expansion ratio.
Date: July 9, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Item Type: Refine your search to only Report
open access

Analysis of Rocket, Ram-Jet, and Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2 - Rocket Missile Performance

Description: From Summary: "The theoretical performance of a two-stage ballistic rocket missile having a centerbody and two parallel boosters was investigated for J oxygen and ammonia-fluorine propellants. Both power-plant and missile parameters were optimized to give minimum cost on-the basis of the analysis for a range of 5500 nautical miles. After optimum values were found, each parameter was varied independently to determine its effect on performance of the missile."
Date: September 29, 1954
Creator: Huff, Vearl N. & Kerrebrock, Jack
Item Type: Refine your search to only Report
open access

Analysis of rocket, ramjet, and turbojet engines for supersonic propulsion of long-range missiles. 3: Ramjet engine performance

Description: Report presenting ramjet engine performance data over a range of engine design variables to permit selection and evaluation of a ramjet engine configuration for a long-range supersonic missile. Results include engine thrust, drag, fuel consumption, area ratios, and weight, and are suitable for use in design studies of missiles incorporating either internally or externally mounted ramjet engines.
Date: August 5, 1954
Creator: Weber, Richard J. & Luidens, Roger W.
Item Type: Refine your search to only Report
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