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Theoretical Analysis of the Interference Effects of Several Supersonic Tunnel Walls Capable of Absorbing the Shock Caused by the Nose of a Model
Memorandum presenting a theoretical analysis of the supersonic flow about two-dimensional and three-dimensional axially symmetric models restricted by theoretical walls capable of removing the nose shock. Results regarding the supersonic-tunnel interference due to nonreflecting walls and supersonic-tunnel interference due to porous walls are provided.
Date:
May 26, 1958
Creator:
Matthews, Clarence W.
System:
The UNT Digital Library
Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines
Report discussing performance estimates for several airplanes using General Electric AC-210 ramjet nuclear-powered engines. Assumptions used for designing the engines, radiation shield, and airframe are described. Potential tradeoffs in regards to power and weight reduction are also discussed.
Date:
April 11, 1958
Creator:
Weber, Richard J. & Connolley, Donald J.
System:
The UNT Digital Library
Aerodynamic Characteristics of a 45 Degree Swept Wing Fighter Airplane Model and Aerodynamic Loads on Adjacent Stores and Missiles at Mach Numbers of 1.57, 1.87, 2.16, and 2.53
Report discussing tests to determine the aerodynamic characteristics of a model of a 45 degree swept-wing fighter airplane and to determine the loads on attached stores and detached missiles. An investigation into aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications of aerodynamic characteristics was also carried out at various Mach numbers. Results are presented, but caution is provided in regards to extrapolating results from the model onto a full-scale aircraft.
Date:
June 24, 1958
Creator:
Oehman, Waldo I. & Turner, Kenneth L.
System:
The UNT Digital Library
Hydrodynamic Characteristics of Missiles Launched Under Water
Report presenting some of the hydrodynamic problems associated with launching an air missile from underwater. The results of an experiment with models are also provided, including deviation angle, effect of forward speed of the submarine, curved path of the missile, and potential environmental disruptions.
Date:
June 27, 1958
Creator:
Dawson, John R.
System:
The UNT Digital Library
A Preliminary Investigation of the Performance of a Short Length Turbojet Combustor Using Vaporized Hydrocarbon Fuels
"Two short turbojet combustors designed for use with vaporized hydrocarbon fuels were tested in a one-quarter annular duct. The experimental combustors consisted of many small "swirl-can" combustor elements manifolded together. This design approach allowed the secondary mixing zone to be considerably reduced over that of conventional combustors" (p. 1).
Date:
January 7, 1958
Creator:
Jones, R. E. & Pawlik, E. V.
System:
The UNT Digital Library
Tracking Performance of a Swept-Wing Fighter With a Director-Type Radar Fire-Control System and Scope Presentation
Memorandum presenting flight tests conducted with an F-86D airplane equipped with a director-type radar fire-control system with scope presentation of the attack display. The effects of two attack-computer parameters and one attack-display parameter on the tracking performance in the manual mode of operation were investigated. Results regarding fixed-sight tracking and tracking with scope presentation are provided.
Date:
January 20, 1958
Creator:
Turner, Horward L.; Rathert, George A., Jr. & Heinle, Donovan R.
System:
The UNT Digital Library
A Flight Study of the Effects of Noise Filtering in the Attack Display on the Pilot's Tracking Performance
Memorandum presenting flight tests conducted with a director-type radar fire-control system, with scope presentation of the steering information, to determine the effects of attack-display smoothing on the pilot's tracking and steering effectiveness in tail-chase and lead-collision beam attacks. Results regarding tail-chase attacks and lead-collision beam attacks are provided.
Date:
September 10, 1958
Creator:
Turner, Howard L. & Heinle, Donovan R.
System:
The UNT Digital Library
Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
Memorandum presenting a transonic flutter investigation of models of the wing of a current fighter airplane. The models were dynamically and elastically scaled in accordance with criteria which include a flutter safety margin. Results regarding the presentation of data, interpretation of results, wings without leading-edge chord-extensions, and wings with leading-edge chord-extensions are provided.
Date:
April 15, 1958
Creator:
Smith, Samuel L., III & Boswinkle, Robert W., Jr.
System:
The UNT Digital Library
Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor
Report presenting testing of gaseous hydrogen fuel burned in a connected-pipe combustor with a cross section equal to 35 degrees sector of a 28-inch diameter. Eleven shrouded fuel-injector configurations were used to obtain combustion data at specified high-altitude ramjet combustor conditions. Results regarding shroud air blockage, mixing tabs, higher equivalence-ratio burning, injector size, flameholder durability, burner length, combustion efficiency, and temperature profile are provided.
Date:
April 22, 1958
Creator:
Kerslake, William R.
System:
The UNT Digital Library
Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane
Memorandum presenting an investigation of the steady-state wing loads conducted on a Boeing B-52 airplane over a range of Mach numbers and altitudes. Results regarding flight tests and air-load calculations are provided.
Date:
April 23, 1958
Creator:
Kuhl, Albert E.; Rogers, John T. & Little, Mary V.
System:
The UNT Digital Library
Investigation of Flutter Characteristics of Three Low-Aspect-Ratio All-Movable Half-Span Control Surfaces at Mach Numbers From 1.49 to 2.87
Memorandum presenting results of a supersonic flutter investigation of three low-aspect-ratio control surfaces. Two controls were all-movable but the third had a fixed cutout. Results regarding the experiments and calculations are provided.
Date:
May 2, 1958
Creator:
Morgan, Homer G.; Figge, Irving E. & Presnell, John G., Jr.
System:
The UNT Digital Library
Some Effects of Flow Spoilers and of Aerodynamic Balance on the Oscillating Hinge Moments for a Swept Fin-Rudder Combination in a Transonic Wind Tunnel
Memorandum presenting force-oscillation tests made in the 8-foot transonic pressure tunnel to investigate some effects of an overhang-type aerodynamic balance and of a flow spoiler on the dynamic hinge-moment characteristics of a full-span flap-type rudder on a 5-percent-thick, swept vertical fin of low aspect ratio. Test results how that the aerodynamic damping moment on the plain rudder becomes unstable near a Mach number of 0.975 and remains unstable to the maximum speed of the tests.
Date:
May 28, 1958
Creator:
Herr, Robert W.; Gibson, Frederick W. & Osborne, Robert S.
System:
The UNT Digital Library
Free-Spinning-Tunnel Investigation of a 1/28-Scale Model of the North American FJ-4 Airplane
Report on an investigation to determine the erect and inverted spin and recovery characteristics of a model of the North American FJ-4 airplane. The testing found that either a flat-type of steep-type spin may be obtained when the airplane is spinning erect. The optimum recovery technique from inverted spins was full rudder reversal with simultaneous movement of the ailerons to full with the stick maintained full forward.
Date:
January 13, 1958
Creator:
Healy, Frederick M.
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
A Wind-Tunnel Investigation of the Wing Loads Due to Deflected Inboard Ailerons on a 45 Degree Sweptback Wing at Transonic Speeds
Memorandum presenting the effects of deflected inboard ailerons on the wing loads of a 45 degree sweptback wing-body combination in the 16-foot transonic tunnel. The model had a wing with an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections. Results regarding the chordwise pressure distributions, effect of ailerons on wing section loadings, effect of aileron on wing loading, and effects of a deflected aileron on opposite-wing loading are provided.
Date:
July 21, 1958
Creator:
Heath, Atwood R., Jr. & Igoe, Ann W.
System:
The UNT Digital Library
Performance at Mach Numbers 3.07, 1.89, and 0 of Inlets Designed for Inlet-Engine Matching Up to Mach 3
Report presenting performance of a two-dimensional external-compression inlet designed for various methods of inlet-engine matching up to Mach 3 at Mach 1.89 and Mach 0. Results regarding shock geometry, two-shock ramps, isentropic ramps, profiles, and cowl drag for the various Mach number tests are provided.
Date:
May 20, 1958
Creator:
Gertsma, L. W. & Beheim, M. A.
System:
The UNT Digital Library
Investigation of Aerodynamic Characteristics of an Airplane Configuration Having Tail Surfaces Outboard of the Wing Tips at Mach Numbers of 2.30, 2.97, and 3.51
Memorandum presenting an investigation to determine the drag, static longitudinal and lateral stability, and longitudinal trim characteristics of an airplane configuration with tail surfaces outboard of the wing tips. Included in the basic data are some effects of Reynolds number, engine pack, and wing twist combined with toe-out of the vertical tails.
Date:
June 23, 1958
Creator:
Church, James D.; Hayes, William C., Jr. & Sleeman, William C., Jr.
System:
The UNT Digital Library
Investigation of Lithium Hydride and Magnesium as High-Temperature Internal Coolants With Several Skin Materials
Memorandum presenting an investigation of hemispherical nose shapes of titanium, stainless steel coated with aluminum oxide, and uncoated stainless steel with lithium hydride and magnesium as internal coolants. Results regarding titanium models, stainless-steel models (uncoated), stainless-steel models coated with aluminum oxide, solution effects on the decomposition temperature of lithium hydride, effect of lithium hydride and magnesium on temperature measurements, and efficiency of models cooled with lithium hydride are provided.
Date:
May 28, 1958
Creator:
Modisette, Jerry L.
System:
The UNT Digital Library
Effects of Modifications to a Control Surface on a 6-Percent-Thick Unswept Wing on the Transonic Control-Surface Flutter Derivatives
Transonic flutter derivatives for unswept wing control surface configurations determined by pressure cell measurements. The control surfaces were mounted on a wing with an aspect ratio of 3, a taper ratio of 0.6, and a wing-thickness ratio of 0.06. Results regarding aerodynamic balance, vortex generators, splitter-plate configurations, and wedges are provided.
Date:
May 2, 1958
Creator:
Wyss, John A.; Sorenson, Robert M. & Gambucci, Bruno J.
System:
The UNT Digital Library
Compatibility of Metals with Liquid Fluorine at High Pressures and Flow Velocities
Report presenting testing of specimens of various metals in selected geometric configurations exposed to liquid fluorine under controlled conditions of flow and pressure. None of the samples eroded, decomposed, or exhibited any measurable physical or chemical changes.
Date:
April 17, 1958
Creator:
Schmidt, Harold W.
System:
The UNT Digital Library
A Feasibility Study of the Flare-Cylinder Configuration as a Reentry Body Shape for an Intermediate Range Ballistic Missile
"A study has been made of a flare-cylinder configuration to investigate its feasibility as a reentry body of an intermediate range ballistic missile. Factors considered were heating, weight, stability, and impact velocity. A series of trajectories covering the possible range of weight-drag ratios were computed for simple truncated nose shapes of varying pointedness, and hence varying weight-drag ratios" (p. 1).
Date:
May 28, 1958
Creator:
Hall, James R. & Garland, Benjamine J.
System:
The UNT Digital Library
Transonic Flutter Investigation of Models of the All-Movable Horizontal Tail of a Fighter Airplane
Memorandum presenting a transonic flutter investigation of models of the all-movable horizontal tail of a fighter airplane in the transonic blowdown tunnel. The models were dynamically and elastically scaled by criteria which provide a flutter safety margin. Results regarding some general comments, simulated airplane tests, effects of pitch stiffness with rearward pitch axis, and effect of pitch-axis location are provided.
Date:
January 24, 1958
Creator:
Sellers, Thomas B.
System:
The UNT Digital Library
Investigation of Control Effectiveness and Stability Characteristics of a Model of a Low-Wing Missile With Interdigitated Tail Surfaces at Mach Numbers of 2.29, 2.97, and 3.51
"A brief investigation of the longitudinal stability and control effectiveness at supersonic speeds of a model of a low-wing missile with interdigitated tail surfaces was made in the Langley Unitary Plan wind tunnel. The data were obtained at Mach numbers M of 2.29, 2.97, and 3.51 for Reynolds number (based on the mean geometric chord of the wing) of 1.15 x 10(exp 6), 1.14 x 10(exp 6), and 1.11 x 10(exp 6), respectively. Data were obtained for three settings of the longitudinal control surfaces: with deflection of all surfaces, with deflection of the lower surfaces only, and with all surfaces undeflected" (p. 1).
Date:
July 14, 1958
Creator:
Presnell, John G., Jr.
System:
The UNT Digital Library
Effects of Boattail Area Contouring and Simulated Turbojet Exhaust on the Loading and Fuselage-Tail Component Drag of a Twin-Engine Fighter-Type Airplane Model
Effects of boattail area contouring and simulated turbojet exhaust on loading and fuselage-tail component drag of twin-engine fighter-type airplane model.
Date:
July 14, 1958
Creator:
Foss, Willard E., Jr.; Runckel, Jack F. & Lee, Edwin E., Jr.
System:
The UNT Digital Library