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Annual Report of the National Advisory Committee for Aeronautics (42nd). Administrative Report Including Technical Report Nos. 1254 to 1295
Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date:
1957
Creator:
unknown
System:
The UNT Digital Library
Transonic Wind-Tunnel Tests of the Launch, Jettison, and Longitudinal Characteristics of an Airplane and Missile Model Combination
Report presenting tests of an airplane model equipped with missiles to investigate the capability of that combination to achieve satisfactory launching and jettisoning of the missiles. Information about pylon modifications, missiles in launch positions, missile trajectory, and missiles in jettison positions is provided.
Date:
November 20, 1957
Creator:
Cleary, Joseph W.; Frank, Joseph L. & Dewey, C. Forbes, Jr.
System:
The UNT Digital Library
Some Effects of Aileron Deflection on the Static Lateral and Directional Aerodynamic Characteristics of Four Contemporary Airplane Models
Memorandum presenting some effects of aileron deflection on the static lateral and directional aerodynamic characteristics of four airplane models which are representative of aircraft capable of flight at supersonic speeds. The results are presented for subsonic Mach numbers ranging from 0.60 to 0.90 and for supersonic Mach numbers ranging from 1.20 to 1.90. They are limited to the most pertinent aerodynamic effects of ailerons contributing to the lateral and directional characteristics of each airplane type.
Date:
July 23, 1957
Creator:
Smith, Willard G. & Intrieri, Peter F.
System:
The UNT Digital Library
Free Flight Investigation at Transonic Speeds of the Power-on Characteristics Including Some Effects of Sonic Propulsive Jets of a Four Engine Delta Wing Configuration
Report discussing a model of a delta-wing configuration with four engines mounted two to a nacelle below the wing that was tested a variety of Mach numbers and Reynolds numbers. The wing static-pressure coefficients, wing pressure coefficients, and lift coefficient of different configurations are described.
Date:
August 16, 1957
Creator:
Falanga, Ralph A. & Judd, Joseph H.
System:
The UNT Digital Library
Heat-Exchanger-Core Weights for Use With Hydrogen-Expansion Turbine
Memorandum presenting an analysis of probable heat-exchanger weights for stationary and rotary regenerator heat exchangers for use in a hydrogen-expansion turbine engine. This is because rotary regenerators offer possibilities for a considerably lighter heat-exchanger core, possibly one-fourth that of the stationary regenerators.
Date:
October 3, 1957
Creator:
Reynolds, Thaine W.
System:
The UNT Digital Library
Altitude chamber evaluation of an aircraft liquid hydrogen fuel system used with a turbojet engine
From Introduction: "The objective of this report are (1) to describe the complete fuel system, (2) to discuss the procedure used for transitions between JP-4 fuel and hydrogen, and (3) to present and discuss engine performance obtained with both fuels, and (4) to review the reliability of the fuel system."
Date:
August 19, 1957
Creator:
Braithwaite, Willis M.; Fenn, David B. & Algranti, Joseph S.
System:
The UNT Digital Library
Hydrogen for Turbojet and Ramjet Powered Flight
Memorandum presenting various reports regarding the use of hydrogen for turbojet and ramjet powered flight. Some of the characteristics considered include the combustion properties, potential fueling problems, and flight experience with hydrogen on-board.
Date:
April 26, 1957
Creator:
Lewis Flight Propulsion Laboratory
System:
The UNT Digital Library
High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels
Memorandum presenting an investigation to determine the performance of the J65-B-3 turbojet engine with JP-4 and gaseous-hydrogen fuels. With JP-4 fuel, the maximum altitude for stable combustion was from about 60,000 to 65,000 feet, and the ultimate blowout limit was at an altitude of about 75,000 feet. The steady-state performance with either fuel decreased considerably with increasing altitude.
Date:
April 2, 1957
Creator:
Kaufman, Harold R.
System:
The UNT Digital Library
Experimental Investigation of Diffuser Pressure Ratio Control With Shock Positioning Limit on 28 Inch Ram-Jet Engine
Report presenting an investigation of the performance of a diffuser static-pressure-ratio control with a normal shock-positioning limit on a ramjet engine installed in an altitude free-jet facility. Testing occurred at Mach numbers of 2.35 and 2.50, altitudes of 50,000, 60,000 and 65,000 feet, and angles of attack of 0 and 7 degrees. Results regarding the effects of control constants, effects of disturbance size and operating point, effects of flight conditions, and control limitations and possible improvements are provided.
Date:
January 15, 1957
Creator:
Dunbar, William R.; Wentworth, Carl B. & Crowl, Robert J.
System:
The UNT Digital Library
Experimental Evaluation of Swirl Can Elements for Hydrogen Fuel Combustor
Memorandum presenting a study of the performance of swirl-can combustor elements for an experimental short-length turbojet combustor utilizing hydrogen fuel at high-altitude operating conditions. Fuel was injected into each element through a tangential, sonic orifice that created a swirling fuel-air mixture within each element. Results regarding combustor blowout, combustion efficiency, outlet temperature distribution, and preliminary performance of multielement combustor are provided.
Date:
May 13, 1957
Creator:
Rayle, Warren D.; Jones, Robert E. & Friedman, Robert
System:
The UNT Digital Library
Design and performance of flight-type liquid-hydrogen heat exchanger
Report presenting an investigation of a liquid-hydrogen fuel system developed to operate one of the turbojet engines in a twin-engine light bomber at an altitude of 50,000 feet and Mach number 0.75. The heat exchanger was evaluated in an altitude test chamber in conjunction with the complete aircraft fuel system. Results regarding calculated heat-exchanger performance, experimental heat-exchanger performance, and reliability are provided.
Date:
August 19, 1957
Creator:
Fenn, David B.; Braithwaite, Willis M. & Ordin, Paul M.
System:
The UNT Digital Library
Design and Performance of Fuel Control for Aircraft Hydrogen Fuel System
Memorandum presenting the system analysis, design, and performance of a control system for an experimental flight-type hydrogen fuel system. The fuel system was designed to investigate some of the problems associated with the utilization of hydrogen as an aircraft fuel. Speed control of the engine was obtained by coupling the hydrogen regulator to the JP-4 fuel control.
Date:
August 19, 1957
Creator:
Otto, Edward W.; Hiller, Kirby W. & Ross, Phil S.
System:
The UNT Digital Library
Flight Investigation of a Liquid Hydrogen Fuel System
Memorandum presenting testing of a twin-engine light bomber modified to utilize hydrogen fuel in one of the two engines during flight at an altitude of 50,000 feet. Three completely successful flights were made using hydrogen fuel. Data are presented to show the effect of tank agitation on fuel pressure and fuel losses.
Date:
August 19, 1957
Creator:
Mulholland, Donald R.; Acker, Loren W.; Christenson, Harold H. & Gough, William V.
System:
The UNT Digital Library
NACA Conference on Aircraft Loads, Structures, and Flutter
"This document contains reproductions of technical papers on some of the most recent research results on aircraft loads, flutter, and structures from the NACA laboratories. These papers were presented by members of the staff of the NACA laboratories at the Conference held at the Langley Aeronautical Laboratory March 5, 6, and 7, 1957. The primary purpose of this Conference was to convey to contractors of the military services and others concerned with the design of aircraft these recent research results and to provide those attending an opportunity to discuss the results" (p. 6).
Date:
March 5, 1957
Creator:
unknown
System:
The UNT Digital Library
Flight investigation of pentaborane fuel in 9.75-inch-diameter ram-jet engine with downstream fuel injection
Report presenting a flight test of pentaborane fuel in an air-launched ramjet engine with a design free-stream Mach number of 1.8. The ramjet used in the investigation had a revised spray bar-flameholder configuration. Results regarding propulsive thrust and propulsive-thrust specific fuel consumption are provided.
Date:
April 22, 1957
Creator:
Disher, John H. & Jones, Merle L.
System:
The UNT Digital Library
Annual Report of the National Advisory Committee for Aeronautics (41st). Administrative Report Including Technical Report Nos. 1210 to 1253
Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Date:
1957
Creator:
unknown
System:
The UNT Digital Library
A Study of Injection Processes for 15-percent Fluorine-85- Percent Oxygen and Heptane in a 200-pound-thrust Rocket Engine
Injection techniques for fluorine, oxygen, and heptane in 200-pound thrust rocket engine.
Date:
January 15, 1957
Creator:
Heidmann, M. F.
System:
The UNT Digital Library
Analytical Investigation of Fuel-Cooled Turbine Blades With Return-Flow Type of Finned Coolant Passages
Memorandum presenting an investigation of coolant-flow rates for a turbine rotor blade with return-flow type of coolant-passage configuration formed by fins within a capped blade shell with both hydrogen and methane fuels as coolants. Results regarding spanwise blade and coolant temperature distributions, effects of coolant inlet temperature on hydrogen-coolant-flow requirements, comparison of return-flow-blade coolant requirements, effect of fin thickness and fin height, comparison of hydrogen and methane as coolants, and feasibility of fuel-cooled turbines are provided.
Date:
June 26, 1957
Creator:
Nachtigall, Alfred J. & Slone, Henry O.
System:
The UNT Digital Library
Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine
Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date:
June 12, 1957
Creator:
Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
System:
The UNT Digital Library
Investigation of Rotating-Stall Limits in a Supersonic Turbofan Engine
Memorandum presenting a theoretical mixed-jet one-spool turbofan engine analyzed over a range of flight Mach numbers up to 2.95. The engine was characterized by an eight-stage fan-compressor unit. Results regarding performance maps, rotating stall, turbofan inlet axial velocity, and weight-flow variations are provided.
Date:
October 3, 1957
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1
Memorandum presenting an evaluation of the performance increase resulting from the addition of 20 percent fluorine to the oxygen-RP-1 propellant combination in a 5000-pound-thrust rocket engine at a chamber pressure of 650 pounds per square inch absolute. Runs were made with the engine water cooled and regeneratively cooled.
Date:
April 24, 1957
Creator:
Tomazic, William A.; Kutina, Franklin J., Jr. & Rothenberg, Edward A.
System:
The UNT Digital Library
Altitude Performance of a Turbojet Engine Using Pentaborane Fuel
Memorandum presenting a turbojet engine with a two-stage turbine operated with pentaborane fuel continuously for 11.5 minutes at a simulated altitude of 55,000 feet at a flight Mach number of 0.8. The engine incorporated an NACA combustor designed specifically for use with pentaborane fuel. Results regarding oxide formation and deposition, engine operating point, effect of oxide deposits on component performance, effect of oxide deposition on overall performance, and some operational comments are provided.
Date:
May 20, 1957
Creator:
Sivo, Joseph N.
System:
The UNT Digital Library
Analyses for Turbojet Thrust Augmentation With Fuel-Rich Afterburning of Hydrogen, Diborane, and Hydrazine
Turbojet thrust augmentation with fuel-rich afterburning of hydrogen, diborane, and hydrazine was computed. Results regarding takeoff thrust augmentation and flight thrust augmentation are provided.
Date:
June 18, 1957
Creator:
Morris, James F.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Mutual Interference Loads on a Supersonic Bomber Configuration and Store During Separation at Mach Numbers of 1.57, 1.77, and 2.01
Report discussing an investigation into the mutual interference loads on a supersonic bomber configuration and store during separation of the store. Tests were performed at several airplane angles of attack, store angles of attack, and airplane sidestep angles. The aerodynamic characteristics of the various components and coefficients of forces are provided in tables.
Date:
October 25, 1957
Creator:
Morris, Owen G. & Turner, Kenneth L.
System:
The UNT Digital Library