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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
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
Wing-Body Combinations With Wings of Very Low Aspect Ratio at Supersonic Speeds
Memorandum presenting force and moment characteristics of configurations employing wings of very low aspect ratio as determined for Mach numbers of 1.97 and 3.33. The angle of attack range was from 0 to 17 degrees for Mach number 1.97 and from 0 to 30 degrees for Mach number 3.33. Results regarding experimental force and moment characteristics, comparisons of theoretical and experimental force and moment characteristics, and visual observations of flow over models are provided.
Date:
October 26, 1956
Creator:
Jorgensen, Leland H. & Katzen, Elliott D.
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
Static Lateral and Directional Stability and Control Characteristics of a Revised 1/22-Scale Model of the Republic F-105 Airplane at Mach Numbers of 1.41 and 2.01
Report discussing testing to determine the static lateral and directional stability and control characteristics of a model of the Republic F-105 airplane. The effects of various vertical tails and ventral fins, wing-tip fences, a canopy fin, fuselage nose shape, external stores, and deflection of horizontal tail, spoiler, and rudder were explored.
Date:
October 16, 1956
Creator:
Robinson, Ross B. & Foster, Gerald V.
System:
The UNT Digital Library
Stability and Control Characteristics at High Subsonic Speeds of a 1/30-Scale Model of the MX-1554A Design
Report discussing testing on a model of the proposed MX-1554A design to determine its stability and control characteristics in high speed flight. Information about the effect of speed brakes, tanks, and fences on the longitudinal characteristics is also provided.
Date:
October 29, 1953
Creator:
Lockwood, Vernard E.; Luoma, Arvo A. & Solomon, Martin
System:
The UNT Digital Library
Summary of Subsonic-Diffuser Data
Memorandum presenting a review of the subsonic-diffuser data available in the literature, which is then reduced to certain appropriate performance coefficients and presented as functions of the significant geometric and flow variables. Results regarding total-pressure-loss factor, diffuser effectiveness, recovery of diffuser effectiveness in the tailpipe, inlet speed effects, exit flow distributions, boundary-layer control, and effects of distorted inlet velocity distribution are provided.
Date:
October 12, 1956
Creator:
Henry, John R.; Wood, Charles C. & Wilbur, Stafford W.
System:
The UNT Digital Library
Free-flight Tests of 45 Deg Swept Wings of Aspect Ratio 3.15 and Taper Ratio 0.54 to Measure Wing Damping of the First Bending Mode and to Investigate the Possibility of Flutter at Transonic Speeds
Free flight tests of 45-deg swept wings of 3.15 aspect ratio and 0.54 taper ratio to measure wing damping and possible transonic flutter.
Date:
October 12, 1954
Creator:
O'Kelly, Burke R.; Lundstrom, Reginald R. & Lauten, William T., Jr.
System:
The UNT Digital Library
A Note on the Ability to Predict Transonic Drag-Rise Changes Due to Model Modifications
Memorandum presenting an experimental and analytical study made at transonic speeds up to Mach number 1.43 to determine the ability of present calculation procedures to predict transonic drag-rise changes which result from physical model changes. Both wing-body and wing-body-tail configurations were investigated.
Date:
October 3, 1957
Creator:
Pierpont, P. Kenneth
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Rolling Stability Derivatives of a 1/10-Scale Model of the Douglas A4D-1 Airplane
Report discussing an experimental investigation of the low-speed rolling stability derivatives of a model of the Douglas A4D-1. The model was tested under a variety of conditions, including in clean and landing configurations and with the horizontal and vertical tails on and off, and the study also explored the effects of slats and flaps on the derivatives of the wing. No analysis of the data is provided.
Date:
October 7, 1954
Creator:
Wolhart, Walter D. & Fletcher, H. S.
System:
The UNT Digital Library
Experimental investigation of effects of simulated nacelles and wing-root freedoms on supersonic flutter characteristics of a cambered, modified, swept, tapered wing
Report presenting an investigation to determine the effects of simulated engine nacelles and wing-root freedoms on the flutter characteristics of a cambered, modified, swept, tapered, semispan wing through a range of Mach numbers. Wings were tested with and without nacelles and with the model restrained, free to roll, and free to translate in the vertical direction. Results regarding the effect of nacelles, flutter boundary, and effect of wing-mount freedom are provided.
Date:
October 16, 1957
Creator:
Hanson, Perry W.
System:
The UNT Digital Library
A Flight and Analog Study of the Effect of Elevating the Radar-Boresight Axis Upon Stability and Tracking Performance of an Automatically Controlled Interceptor
Report presenting flight and analog-simulator tests with a prototype automatic interceptor in order to study the effects of elevating the radar-boresight axis on the stability and tracking performance of the system. Results regarding effects of interceptor rolling motion upon tracking errors, similarity of flight results and analog-computer results, effect of elevating the radar-boresight axis upon stability, effect of elevating the radar-boresight axis upon the required bank-angle feedback, and application of the principle of elevated radar-boresight axis are provided.
Date:
October 16, 1957
Creator:
Cheatham, Donald C. & Mathews, Charles W.
System:
The UNT Digital Library
Free Spinning and Recovery Characteristics of 1/36-Scale Model of the Republic F-105B Airplane
Report presenting an investigation in the free-spinning tunnel on a model of the Republic F-105B airplane to determine the spin and recovery characteristics. Results indicated that even with perfect control technique, full movement of the rudder against the spin and of ailerons with the spin is not adequate to ensure satisfactory recovery; extensions of both canard surfaces should accompany the control technique. Results regarding ideal parachute design are also provided.
Date:
October 9, 1957
Creator:
Bowman, James S., Jr.
System:
The UNT Digital Library
Wind Tunnel Investigation at High Subsonic Speeds of Drag at 0 Degrees Angle of Attack of Swept-Wing Fuselage Models With Pylon Mounted and Semisubmerged Missiles
Report discussing testing on two wing-fuselage models with 45 degree sweptback wings and various missile arrangements, one with pylons underneath the wing and one with the missiles semisubmerged in the sides of the fuselage. A comparison of the drag of both types of models was made.
Date:
October 8, 1956
Creator:
King, Thomas J., Jr.
System:
The UNT Digital Library
Synthesis and Hydrolysis-Rate Studies of Decaborane Derivatives
Report discussing a series of experiments involving the reaction of water with decaborane and HEF-3, a boron fuel containing ethyldecaborane. The chemical properties of the hydrolysis reaction are described. Two isomers were also prepared to assist with the syntheses, and their melting points, molecular weights, and solubilities in certain solvents are included.
Date:
October 8, 1957
Creator:
Lucas, D. & Lipschitz, A.
System:
The UNT Digital Library
Investigations of Slot Configurations for Film-Cooled Turbine Blades by Flow Visualization Methods
Memorandum presenting a procedure for obtaining qualitative information on the effectiveness of different slot configurations to make the flow of the cooling air visible. Two methods are utilized: one utilizes the traces caused by a reaction between paint spread over the blade surface and a gas mixed with the cooling air, while the other utilized smoke mixed with the cooling air to make it visible. From the visual observations, the use of a continuous slot as a means of creating the cooling film over the blade surface appeared to be superior to the use of holes or grooves.
Date:
October 10, 1950
Creator:
Eckert, E. R. G.; Jackson, Thomas W. & Francisco, Allen C.
System:
The UNT Digital Library
Transonic Aerodynamic Characteristics of a 1/15-Scale Model of the Convair B-58 Airplane
Report presenting an investigation of a model of the Convair B-58 airplane weapons system in the transonic tunnel for a range of Mach and Reynolds numbers. Results regarding drag characteristics, lift-curve slope, and longitudinal stability parameter are provided.
Date:
October 19, 1956
Creator:
Swihart, John M.
System:
The UNT Digital Library
Investigation of the Kingfisher XAUM-2 Flying Torpedo in the Langley Full Scale Tunnel, TED No. NACA DE 327
Report presenting an investigation of a model of the Kingfisher XAUM-2 flying torpedo to determine the pressure recoveries within the jet engine nacelle and to determine the effects of several changes in model configuration on the aerodynamic characteristics of the model. The effectiveness of elevons and tabs as control devices was also investigated.
Date:
October 6, 1949
Creator:
Cocke, Bennie W. & Barnett, U. Reed
System:
The UNT Digital Library
Analysis of Rocket, Ramjet, Turbojet Engines for Supersonic Propulsion of Long-Range Missiles 2: Rocket Missile Performance
Memorandum presenting an investigation of the theoretical performance of a two-stage ballistic rocket missile with a centerbody and two parallel boosters for JP4-oxygen and ammonia-fluorine propellants. The missile using the ammonia-fluorine propellant weighs about one-half as much as a missile using JP4-oxygen. Results regarding the optimum missile and effect of variation of design parameters are provided.
Date:
October 11, 1954
Creator:
Huff, Vearl N. & Kerrebrock, Jack
System:
The UNT Digital Library
The Subsonic Lateral and Longitudinal Static Stability Characteristics Up to Large Angles of Sideslip for a Triangular-Wing Airplane Model Having a Ventral Fin
"Wind-tunnel tests were conducted to determine the effects of a ventral fin on the static characteristics of a triangular-wing airplane model. Data were obtained for angles of sideslip up to 18 degrees at angles of attack of 0, 6, 12, and 18 degrees at Mach numbers from 0.25 to 0.94. The results of the tests indicated that the ventral fin did not produce as much yawing moment per unit of exposed area at any angle of sideslp as the vertical tail" (p. 1).
Date:
October 25, 1956
Creator:
Buell, Donald A. & Tinling, Bruce E.
System:
The UNT Digital Library
An Investigation of the Low-Speed Stability and Control Characteristics of a 1/10-Scale Model of the McDonnell XF3H-1 Airplane
Report presenting an investigation of the low-speed, power-off stability and control characteristics of a model of the McDonnell XF3H-1 airplane. Flight testing occurred in the clean and slat- and flaps-extended conditions over a range of lift coefficients.
Date:
October 11, 1951
Creator:
Draper, John W.
System:
The UNT Digital Library
Wind-Tunnel Tests of a Series of Practice Bombs
Report discussing zero-lift drag data for several bomb configurations at various Mach numbers. Seven configurations were tested with different combinations of interchangeable noses and tail cones with fins, some with different surface conditions. Surface conditions were not found to affect the drag, but the thickness of the tail fins and shape of the noses did change the shape of the drag curve.
Date:
October 25, 1957
Creator:
Ward, Donald H.
System:
The UNT Digital Library
Performance Comparison at Mach Numbers 1.8 and 2.0 of Full Scale and Quarter Scale Translating-Spike Inlets
"The performance of a full-scale translating-spike inlet was obtained at Mach numbers of 1.8 and 2.0 and at angles of attach from 0 deg to 6 deg. Comparisons were made between the full-scale production inlet configuration and a geometrically similar quarter-scale model. The inlet pressure-recovery, cowl pressure-distribution, and compressor-face distortion characteristics of the full-scale inlet agreed fairly well with the quarter-scale results" (p. 1).
Date:
October 21, 1957
Creator:
Hearth, Donald P.; Anderson, Bernhard H. & Dryer, Murray
System:
The UNT Digital Library
Performance of a Double-Ramp Side Inlet With Combinations of Fuselage, Ramp, and Throat Boundary-Layer Removal, Mach Number Range, 1.5 to 2.0
Double-ramp side inlet with combinations of fuselage, ramp, and throat boundary layer removal.
Date:
October 22, 1956
Creator:
Simon, Paul C.
System:
The UNT Digital Library