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Adaptation of Combustion Principles to Aircraft Propulsion, Volume 1, Basic Considerations in the Combustion of Hydrocarbon Fuels with Air

Description: The report summarizes source material on combustion for flight-propulsion engineers. First, several chapters review fundamental processes such as fuel-air mixture preparation, gas flow and mixing, flammability and ignition, flame propagation in both homogenous and heterogenous media, flame stabilization, combustion oscillations, and smoke and carbon formation. The practical significance and the relation of these processes to theory are presented. A second series of chapters describes the observed performance and design problems of engine combustors of the principal types. An attempt is made to interpret performance in terms of the fundamental processes and theories previously reviewed. Third, the design of high-speed combustion systems is discussed. Combustor design principles that can be established from basic considerations and from experience with actual combustors are described. Finally, future requirements for aircraft engine combustion systems are examined.
Date: April 1, 1955
Creator: Barnett, Henry C. & Hibbard, Robert R.

The adhesion of molten boron oxide to various materials

Description: This report includes the description and results of an experiment evaluating the amount of adhesion existing between the liquid boron oxide and various materials used in engines.
Date: April 1, 1958
Creator: Witzke, W. R.

Aerodynamic and hydrodynamic characteristics of models of some aircraft-towed mine-sweeping devices : TED No. NACA AR 8201

Description: This report details a study that was conducted by the U.S. Naval Air Development Center to "determine the feasibility of several airborne magnetic mine-sweeping methods. The advantages of a satisfactory airborne method are greater safety and speed than are possible with existing surface methods." The configurations and results of the double Q-sweep, the modified double-catenary sweep, and the M-sweep are examined.
Date: December 1, 1955
Creator: Shanks, Robert E.

Aerodynamic characteristics at supersonic speeds of a series of wing-body combinations having cambered wings with an aspect ratio of 3.5 and a taper ratio of 0.2: Effects of sweep angle and thickness ratio on the static lateral stability characteristics at M = 2.01

Description: Report presenting an investigation in the 4- by 4-foot supersonic pressure tunnel at Mach number 2.01 to determine the effects of sweep angle and thickness ratio on the static lateral stability characteristics of a series of wings with taper ratio 0.2 and aspect ratio 3.5. The results are presented with little analysis.
Date: August 1, 1952
Creator: Hamilton, Clyde V.

Aerodynamic Damping at Mach Numbers of 1.3 and 1.6 of a Control Surface on a Two-Dimensional Wing by a Free-Oscillation Method

Description: Memorandum presenting tests at two supersonic speeds to obtain experimentally the aerodynamic damping characteristics of a control surface on a two-dimensional wing. The control surface had a chord of 1.67 inches and a span of 7.25 inches and was supplied in three materials with different mass, inertia, and stiffness properties. Results regarding the presentation of data and comparison with theory and comparison with control-surface data for a triangular wing are provided.
Date: May 1, 1956
Creator: Tuovila, W. J. & Hess, Robert W.

Aerodynamic Design of Axial-Flow Compressors: Volume 1

Description: Compendium presenting a comprehensive integration of available aerodynamic design information on axial-flow compressors. The subjects of the first volume of this investigation are objectives and scope, compressor design requirements, compressor design system, potential flow in two-dimensional cascades, and viscous flow in two-dimensional cascades.
Date: August 1, 1956
Creator: Members of the Compressor and Turbine Research Division

Aerodynamic Design of Axial-Flow Compressors, Volume 2

Description: Available experimental two-dimensional-cascade data for conventional compressor blade sections are correlated. The two-dimensional cascade and some of the principal aerodynamic factors involved in its operation are first briefly described. Then the data are analyzed by examining the variation of cascade performance at a reference incidence angle in the region of minimum loss. Variations of reference incidence angle, total-pressure loss, and deviation angle with cascade geometry, inlet Mach number, and Reynolds number are investigated. From the analysis and the correlations of the available data, rules and relations are evolved for the prediction of the magnitude of the reference total-pressure loss and the reference deviation and incidence angles for conventional blade profiles. These relations are developed in simplified forms readily applicable to compressor design procedures.
Date: August 1, 1956

Aerodynamic design of axial-flow compressors: Volume 3

Description: Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimensional treatment by summarizing the literature on secondary flows and boundary layer effects. Charts for determining the effects of errors in design parameters and experimental measurements on compressor performance are given in Chapters XVI. Chapter XVII reviews existing literature on compressor and turbine matching techniques.
Date: August 1, 1956
Creator: Johnsen, Irving A.; Bullock, Robert O.; Graham, Robert W.; Costilow, Eleanor L.; Huppert, Merle C.; Benser, William A. et al.

An air-borne target simulator for use in optical sight tracking studies

Description: From Introduction: "The development of this air-borne optical target simulator and the results of evaluation flight tests (including a comparison of airplane tracking performance against the simulated and an actual target airplane) are presented herein."
Date: September 1, 1955
Creator: Doolin, Brian F.; Smith, G. Allan & Drinkwater, Fred J., III

Analysis of V-g records from the Grumman F8F-2 airplane

Description: From Introduction: "In the present paper, which supplements reference 1, V-g records obtained from F8F-2 airplanes in 1949 are analyzed statistically to determine the frequency of experiencing large values of normal load factor and airspeed. These results are compared with the results from the F8F-1 airplane."
Date: July 1, 1952
Creator: Thornton, James O

Analytical evaluation of effect of inlet-air temperature and combustion pressure on combustion performance of boron slurries and blends of pentaborane in octene-1

Description: From Summary: "The effects of variation in inlet-air temperature, combustion pressure, and boron or pentaborane concentration on combustion performance were discussed. It was shown how the theoretical data herein could be employed in obtaining the combustion efficiency of experimental combustors. Data were presented by which combustion efficiencies obtained with a water-quench heat balance could be adjusted for the heat of dissociation of the combustion products."
Date: June 1, 1955
Creator: Tower, Leonard K.

A brief hydrodynamic investigation of a Navy seaplane design equipped with a hydro-ski

Description: Report presenting testing of a model of a Navy Bureau of Aeronautics design in Langley tank no. 2 to determine the calm-water take-off and rough-water landing characteristics of the design with particular attention paid to the take-off resistance and landing accelerations. Results regarding resistance, take-off stability, landing stability, spray, and landing acceleration are provided.
Date: September 1, 1953
Creator: Fisher, Lloyd J. & Hoffman, Edward L.

Characteristics of loads in rough air at transonic speeds of rocket-powered models of a canard and a conventional-tail configuration

Description: Report presenting results from flight tests at transonic speeds for a canard and a conventional-tail rocket-powered model in continuous rough air. The use of an airspeed-fluctuation instrument for measuring the turbulence intensity experienced is described as well as the resulting improvement in the technique of testing rocket models in rough air. The short-period frequency was dominant in the center-of-gravity normal-acceleration response for both models.
Date: March 1, 1955
Creator: Vitale, A. James

Comparative dispersion data from ground-launched 2.25-inch rockets equipped with cruciform and monoplane fins

Description: Report presenting testing of about 150 rounds of 2.25-inch subcaliber aircraft rockets equipped with standard cruiform fins and twisted monoplane fins. No significant difference in dispersion was observed for the different configurations of fins on the rockets. Results regarding the stability of the different types of rockets, and general characteristics of the flight paths are provided.
Date: November 1, 1955
Creator: Purser, Paul E.

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.