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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
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
Performance characteristics of an underslung vertical-wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0
Performance characteristics of underslung vertical wedge inlet with porous suction at Mach numbers of 0.63 and 1.5 to 2.0.
Date:
August 3, 1956
Creator:
Allen, John L. & Piercy, Thomas G.
System:
The UNT Digital Library
Summary and Analysis of Horizontal-Tail Contribution to Longitudinal Stability of Swept-Wing Airplanes at Low Speeds
Report discussing available wind-tunnel data on low-speed horizontal-tail contribution to the static longitudinal stability of high-speed airplane configurations with unswept and sweptback wings. The effects of variations of tail position, wing plan form, airfoil section, trailing-edge flaps, stall-control devices, and ground interference on air-flow characteristics an tail contribution are also described.
Date:
August 23, 1955
Creator:
Neely, Robert H. & Griner, Roland F.
System:
The UNT Digital Library
Low-Speed Wind-Tunnel Tests of a 1/8-Scale Model of the Bell D-188A VTOL Airplane
Report discussing the results of an investigation to determine the low-speed power-off stability and control characteristics of a model of the Bell D-188A VTOL airplane. The static stability and control characteristics were generally satisfactory except above certain angles of attack and aileron effectiveness dropped off as the angle of attack was increased. Modifications for increasing the directional stability by altering the vertical tails are also described.
Date:
August 1, 1958
Creator:
McKinney, Marion O. & Smith, Charles C., Jr.
System:
The UNT Digital Library
Low-Speed Investigation of the Effect of Small Canard Surfaces on the Directional Stability of a Sweptback-Wing Fighter-Airplane Model
Memorandum presenting a low-speed investigation in the free-flight tunnel to determine the effect of small canard surfaces on the directional stability of a fighter-airplane model with an aspect ratio of 3.4 and a 42 degree sweptback wing. The canard surfaces were found to be generally ineffective at angles of attack below 20 degrees.
Date:
August 23, 1956
Creator:
Paulson, John W. & Boisseau, Peter C.
System:
The UNT Digital Library
An Investigation of the Dynamic and Static Stability Characteristics of a Group of Specialized Store Configurations at Transonic Speeds
Report presenting an investigation in the transonic tunnel to determine the dynamic and static stability characteristics of the Mark-6, Mark-4, TX-13, and Mark-5 special weapons and the effects of modifications of them for a range of Mach numbers.
Date:
August 21, 1953
Creator:
Henry, Beverly Z., Jr. & Braden, John A.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Yawing Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane
Report discussing testing of a model of the Douglas A4D-1 to determine its low-speed yawing stability derivatives. The model was tested in clean and landing configurations with horizontal and vertical tails on and off and an investigation into the effect of slats and flaps on the wing-alone derivatives.
Date:
August 25, 1954
Creator:
Wolhart, Walter D. & Fletcher, H. S.
System:
The UNT Digital Library
Development of a Supersonic Area Rule and an Application to the Design of a Wing-Body Combination Having High Lift-to-Drag Ratios
Report presenting a concept for interrelating the wave drag of wing-body combinations at moderate supersonic speeds with axial distributions of cross-sectional area has been developed. Details of preliminary experiments meant to test the concept are also provided.
Date:
August 18, 1953
Creator:
Whitcomb, Richard T. & Fischetti, Thomas L.
System:
The UNT Digital Library
Natural Icing of an Axial-Flow Turbojet Engine in Flight for a Single Icing Condition
Memorandum presenting an investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. A description of the change over time in tail-pipe temperature, engine jet thrust, fuel flow, ice collection, and acceleration qualities are provided.
Date:
August 12, 1948
Creator:
Acker, Loren W.
System:
The UNT Digital Library
Preliminary Results of Natural Icing of an Axial-Flow Turbojet Engine
Memorandum presenting a flight investigation in natural icing conditions to determine the effect of ice formations on the performance of an axial-flow turbojet engine. Tail-pipe temperature increased from 761 to 1065 degrees Fahrenheit and the jet thrust decreased from 1234 to 910 pounds during a period of 45 minutes in icing. No general conclusions can be reached from the data because the icing condition was relatively light.
Date:
August 6, 1948
Creator:
Acker, Loren W.
System:
The UNT Digital Library
Icing and De-Icing of a Propeller with Internal Electric Blade Heaters
"An investigation has been made in the NACA Cleveland icing research tunnel to determine the de-icing effectiveness of an experimental configuration of an Internal electric propeller-blade heater. Two atmospheric Icing conditions and two propeller operating conditions were Investigated in experiments with unheated blades and with heat applied to the blades both continuously and cyclically. Data are presented to show the effect of propeller speed, ambient air temperature and liquid-water concentration, and the duration of the heat-on and cycle times on the power requirements and de-icing performance of the blade heaters" (p. 1).
Date:
August 1948
Creator:
Lewis, James P. & Stevens, Howard C., Jr.
System:
The UNT Digital Library
Transonic Wind-Tunnel Investigation of Static-Pressure Fluctuations in Duct of a Scale Inlet Model of a Supersonic Fighter-Bomber Airplane
Report presenting a transonic investigation of the static-pressure fluctuations in the left duct of a scale inlet model of a supersonic fighter-bomber airplane in the transonic tunnel. Results regarding amplitude characteristics of pressure fluctuations, power-spectral analyses, and flow distortions at compressor face are provided.
Date:
August 6, 1957
Creator:
Brooks, Joseph D.
System:
The UNT Digital Library
Preliminary Analysis of Performance of Turbojet Engines Used as Pumps for Boundary-Layer Control
Memorandum presenting a determination of the effects on engine performance of using turbojet engines for boundary-layer control by suction at the engine inlet or by bleeding air from the compressor outlet for three current production engines. Results regarding bleed, suction, and variable-area turbine are provided.
Date:
August 16, 1955
Creator:
Conrad, E. William
System:
The UNT Digital Library
Aerodynamic Characteristics at a Mach Number of 6.8 of Two Hypersonic Missile Configurations, One With Low-Aspect-Ratio Cruciform Fins and Trailing-Edge Flaps and One With a Flared Afterbody and All-Movable Controls
Report presenting an investigation to determine the aerodynamic characteristics in pitch at a Mach number of 6.8 of hypersonic missile configurations with cruciform trailing-edge flaps and all-movable control surfaces. Testing indicated that all-movable controls on the flared-afterbody model should be capable of producing much larger values of trim lift and of normal acceleration than the trailing-edge-flap configuration. Some of the configurations tested include body alone, body with 5 degree fins and trailing-edge flaps, and body with 10 degree flare and all-movable controls.
Date:
August 4, 1958
Creator:
Robinson, Ross B. & Bernot, Peter T.
System:
The UNT Digital Library
Investigation of a 1/22-Scale Model of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Lateral, Directional, and Additional Longitudinal Static Stability and Control
Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 at Mach numbers from 0.60 to 1.13. The primary focus of this report are the static lateral and directional stability and control characteristics of the model. Results regarding force and moment results, longitudinal characteristics, lateral and directional characteristics.
Date:
August 23, 1957
Creator:
Luoma, Arvo A.
System:
The UNT Digital Library
A Method for Numerically Calculating the Area and Distribution of Water Impingement on the Leading Edge of an Airfoil in a Cloud
Note presenting a method for determining, by step-by-step integration, the trajectories of water drops around any body in two-dimensional flow for which the streamline velocity components are known or can be computed. The equations are presented in general form and then, to illustrate the procedure, water-drop trajectories are calculated about a 12-percent-thick symmetrical Joukowski profile chosen to simulate an NACA 0012 section. The method provides a means for the relatively rapid calculation of the trajectory of a single drop without the utilization of a differential analyzer.
Date:
August 1947
Creator:
Bergrun, Norman R.
System:
The UNT Digital Library
Preliminary Results of Heat Transfer from a Stationary and Rotating Ellipsoidal Spinner
"Convective heat-transfer coefficients in dry air were obtained for an ellipsoidal spinner of 30-inch maximum diameter for both stationary and rotating operation over a range of conditions including airspeeds up to 275 miles per hour, rotational speeds up to 1200 rpm, and angles of attack of zero and 4 degrees. The results are presented in terms of Nusselt numbers, Reynolds numbers, and convective heat-transfer coefficients. The studies included both uniform heating densities over the spinner and uniform surface temperatures" (p. 1).
Date:
August 6, 1953
Creator:
von Glahn, U.
System:
The UNT Digital Library
Theoretical Investigation of Submerged Inlets at Low Speeds
From Summary: "The general characteristics of the flow field in a submerged air inlet are investigated by theoretical, wind-tunnel, and visual-flow studies. Equations are developed for calculating the laminar and turbulent boundary-layer growth along the ramp floor for parallel, divergent, and convergent ramp walls, and a general equation is derived relating the boundary-layer pressure losses to the boundary-layer thickness. It is demonstrated that the growth of the boundary layer on the floor of the divergent-ramp inlet is retarded and that a vortex pair is generated in such an inlet."
Date:
August 1951
Creator:
Sacks, Alvin H. & Spreiter, John R.
System:
The UNT Digital Library
High Efficiency of Seaplanes
A table is presented which includes data for calculating the index of efficiency. The author uses this data to conclude that seaplanes cannot be considered inferior to terrestrial airplanes.
Date:
August 1921
Creator:
Pegna, G.
System:
The UNT Digital Library