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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
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
Investigations on Reductions of Friction on Wings, in Particular by Means of Boundary Layer Suction
Memorandum presenting investigation on reductions of friction on wings, especially by means of boundary-layer suction. The report is broken up into several sections, including: causes of transition, laminar profiles with the transition taking place, laminar boundary-layer suction, investigation of the laminar pressure increase, investigation of the slot flow for laminar boundary-layer suction with single slots, tests about keeping a boundary layer for high Reynolds laminar with the aid of boundary-layer suction, and an investigation of a slightly-cambered laminar suction profile of 10.5-percent thickness.
Date:
August 1947
Creator:
Pfenninger, Werner
System:
The UNT Digital Library
Comparison of relative sensitivities of the knock limits of two fuels to six engine variables
Report presenting knock testing of a sensitive fuel and a relatively insensitive fuel in a full-scale air-cooled cylinder. Six engine variables were investigated: fuel-air ratio, compression ratio, inlet-air temperature, spark advance, exhaust pressure, and cylinder temperature.
Date:
August 1946
Creator:
Cook, Harvey A.; Held, Louis F. & Pritchard, Ernest I.
System:
The UNT Digital Library
Strain-Gage Study of Internally Cooled Exhaust Valves Having Various Throat Designs
Note presenting three internally cooled exhaust valves with the same external dimensions but different throat designs were investigated to determine a method of obtaining increased coolant-flow area with increasing stresses. The valves were statistically loaded to simulate stresses in the throat region caused by valve closure.
Date:
August 1946
Creator:
Holms, Arthur G. & Faldetta, Richard D.
System:
The UNT Digital Library
Investigations of Free Turbulent Mixing
Note presenting a discussion of the integral relations for flow of the boundary-layer type. It is shown that the characteristic laws of spread of jets, wakes, and so forth, can be obtained directly for the laminar case and, with the help of dimensional reasoning, for the turbulent case as well. Measurements of the mean velocity, the intensity and scale of the turbulent fluctuations, and of the turbulent shear in a two-dimensional mixing zone are presented.
Date:
August 1947
Creator:
Liepmann, Hans Wolfgang & Laufer, John
System:
The UNT Digital Library
Lautal as a Material for Airplane Construction
Lautal is a refinable aluminum alloy which, unlike duralumin, contains no magnesium. According to the statements of the Lauta Works, lautal contains: aluminum, 94%; copper, 4%; silicon, 2%. The use of lautal as a construction material is discussed in relation to specific weight, production methods, and riveting tests.
Date:
August 1929
Creator:
Brenner, Paul
System:
The UNT Digital Library
Historical Notes on Aerodynamic Research
"It is obviously interesting to know the names of those who were the first contributors to aeronautical science. Therefore, without claiming to give a complete history, I present in this article a summary list of names in chronological order relating to the history of experiments on the resistance of the air and its application to aeronautics" (p. 1).
Date:
August 1924
Creator:
Dollfus, Charles
System:
The UNT Digital Library
Buckling Tests of Light-Metal Tubes
Report presenting an attempt to determine mathematically the buckling-strength curves of various centrally loaded light-metal tubes which exhibit conspicuous differences of behavior under compressive loads. For this purpose, Von Karman's method is used after adapting it to special conditions.
Date:
August 1929
Creator:
Schroeder, August
System:
The UNT Digital Library
On the stability of oscillations of an airplane wing
During a flight with a Van Berkel W. B. seaplane it was observed that the wing could perform violent oscillations. A theoretical and experimental investigation led to the conclusion, that in some cases an unstable oscillation of the wing-aileron system under the influence of the elastic and aerodynamic forces is possible without further external causes.
Date:
August 1923
Creator:
Von Baumhauer, A. G. & Koning, C.
System:
The UNT Digital Library
Carburetion in Aviation Engines
This report tries to solve the problem of supplying the engine cylinders with a mixture of fuel and air in the right ratio to obtain the greatest power from the engine with the least consumption of fuel.
Date:
August 1923
Creator:
Poincaré
System:
The UNT Digital Library
Recent Suggestions in Diesel-Engine Construction
Different methods for increasing the efficiency of diesel engines are presented and some new designs are given.
Date:
August 1927
Creator:
Bielefeld, F. Ernst
System:
The UNT Digital Library
Metal Construction Development Part 1: General, Strip Metal Construction - Fuselage
Memorandum presenting a general overview of aircraft constructed from metal and fuselages constructed from strip metal.
Date:
August 1929
Creator:
Pollard, H. J.
System:
The UNT Digital Library
Engines and Fuels
The report considers the effect on engines of the varying types of fuels now in use. Different types of fuels are examined and the influence of physical characteristics are considered.
Date:
August 1923
Creator:
unknown
System:
The UNT Digital Library
Vorticism in Aeronautics
Since the war there has been a considerable advance in knowledge on the subject of the airfoil and its behavior. The theory is now sufficiently advanced to make it possible to predict and to calculate certain results which previously could only be attained by direct experiment. The vortex theory receives special attention.
Date:
August 1923
Creator:
Sayers, W. H.
System:
The UNT Digital Library
Structural Details of German Light Airplanes
This report presents a review of German light airplane construction. Some of the topics discussed include: engines, fuselages, wings, landing gear, and other mechanical parts.
Date:
August 1930
Creator:
Schrenk, Martin
System:
The UNT Digital Library
Designing Seaplane Hulls and Floats
Experimental data, such as the results of tank tests of models, render it possible to predict, at least in principle, as to how a hull or float of a given shape will comport itself. We will see further along, however, how uncertain these methods are and how they leave room for empiricism, which will reign for a long time yet in seaplane research bureaus.
Date:
August 1926
Creator:
Benoit
System:
The UNT Digital Library
Stresses Near the Juncture of a Closed and an Open Torsion Box as Influenced by Bulkhead Flexibility
Report discussing an open box joined to a closed box subjected to torsional loading. A stiff bulkhead and a flexible bulkhead were tested at the discontinuity and the results were compared to a previously published theory. Stress distribution was found to not be sensitive to bulkhead stiffness when the stiffness is large, but the calculations became sensitive to errors in estimating when the stiffness was small.
Date:
August 1945
Creator:
Kuhn, Paul & Brilmyer, Harold G.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Control-Surface Characteristics 3: A Small Aerodynamic Balance of Various Nose Shapes Used With a 30-Percent-Chord Flap on an NACA 0009 Airfoil
Report presenting tests in the 4- by 6-foot vertical wind tunnel of an NACA 0009 airfoil with a 30-percent-chord flap with a small amount of aerodynamic balance. In the investigation, the effect of balance nose shape and gap at the nose of the flap has been determined. The results indicate that, in general, the lift effectiveness of the flap was unaffected by the addition of a small amount of aerodynamic overhang, and the balance effectiveness of the flap was increased.
Date:
August 1941
Creator:
Ames, Milton B., Jr.
System:
The UNT Digital Library
Wind-tunnel investigation of control-surface characteristics II : a large aerodynamic balance of various nose shapes with a 30-percent-chord flap on an NACA 0009 airfoil
Report presenting testing of an NACA 0009 airfoil with a 30-percent-chord flap with a 49.5-percent flap-chord balance with various nose shapes and two gaps. The results indicated that the flap is overbalanced when deflected, regardless of nose shape. Results regarding lift, hinge moment of flap, drag, pitching moment, and effect of differential balancing tab are provided.
Date:
August 1941
Creator:
Sears, Richard I. & Hoggard, H. Page, Jr.
System:
The UNT Digital Library
Wind-Tunnel Investigation of a Full-Span Retractable Flap in Combination With Full-Span Plain and Internally Balanced Ailerons on a Tapered Wing
Report discusses the results of an investigation into a full-span retractable flap in combination with a full-span plain and internally balanced ailerons on a tapered wing of a typical fighter airplane.The flap was designed to improve lateral control during high lifts for landing and take-off. The effects on the maximum life coefficient, aileron effectiveness, estimated rates of roll, and stick forces are provided.
Date:
August 1943
Creator:
Rogallo, F. M.; Lowry, John G. & Fischel, Jack
System:
The UNT Digital Library
An experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface
Report presenting the results of an experimental investigation of the unsteady lift induced on a wing in the downwash field of an oscillating canard control surface. The results indicated that existing theories provide a reliable guide for the estimation of the magnitude of the lift derivatives and centers of pressure at low values of reduced frequency and low angles of attack.
Date:
August 15, 1955
Creator:
Reese, David E., Jr.
System:
The UNT Digital Library