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Progress Report on AEC Contract on Research and Development Program on Scintillation Crystals: Period 1 January 1956 to 1 April 1956
Description:
From Abstract: "This report covers the preliminary literature survey and the screening of activated cesium iodide and several alkali halides to qualitatively determine their luminerscence. The report also includes a proposal of the future work and a proposed budget for the 1957 fiscal year."
Date:
April 25, 1956
Creator:
Beadle, Robert
Preliminary Analysis of a Nuclear Powered Supersonic Airplane Using Ramjet Engines
Description:
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.
Hydrogen for Turbojet and Ramjet Powered Flight
Description:
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
High Altitude Performance Investigation of J65-B-3 Turbojet Engine With Both JP-4 and Gaseous Hydrogen Fuels
Description:
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.
Effect of Combustion Gas Properties on Turbojet-Engine Performance With Hydrogen as Fuel
Description:
Memorandum presenting an analysis comparing engine performance determined by use of a method involving adjustment of engine cycle calculations using JP-4 fuel with performance obtained using hydrogen as a fuel.
Date:
April 10, 1956
Creator:
English, Robert E.
Transonic Flutter Investigation of Models of the Sweptback Wing of a Fighter Airplane
Description:
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.
Experimental Performance of a 5000-Pound-Thrust Rocket Chamber Using a 20-Percent-Fluorine - 80-Percent-Oxygen Mixture With RP-1
Description:
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.
Combustion of gaseous hydrogen at low pressures in a 35 degree sector of a 28-inch-diameter ramjet combustor
Description:
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.
Analysis of Flight-Determined and Predicted Effects of Flexibility on the Steady-State Wing Loads of the B-52 Airplane
Description:
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.
Effects of Components and Various Modifications on the Drag and the Static Stability and Control Characteristics of a 42 Deg Swept-Wing Fighter-Airplane Model at Mach Numbers of 1.60 to 2.50
Description:
Wind tunnel testing of swept wing fighter aircraft model for determining drag and static longitudinal and lateral stability and control characteristics. Results regarding performance, longitudinal stability, lateral stability, and strakes are provided.
Date:
April 15, 1959
Creator:
Church, James D.
Compatibility of Metals with Liquid Fluorine at High Pressures and Flow Velocities
Description:
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.
Full-Scale Wind-Tunnel Tests of a North American FJ-3 Airplane with a Spoiler-Slot-Deflector Lateral Control System
Description:
Report discussing an investigation to determine the low-speed aerodynamic characteristics of a North American FJ-3 airplane with a segmented spoiler-slot-deflector lateral control system installed ahead of convention ailerons and operated as individual units and as combined segments. The longitudinal characteristics of the plane, the spoiler-slot-deflector effectiveness, and spoiler-deflector hinge-moment data are all described.
Date:
April 9, 1956
Creator:
Scallion, William I.
Pressure Distributions at Mach Numbers of 1.6 and 1.9 of a Conically Cambered Wing of Triangular Plan Form With and Without Pylon-Mounted Engine Nacelles
Description:
Memorandum presenting the results of an experimental investigation to determine the pressure-distribution characteristics of a conically cambered wing with and without pylon-mounted engine nacelles for Mach numbers of 1.6 and 1.9. The pressure data obtained during this investigation indicate that the low-pressure region existing on the upper surface over the forward part of the wing was spread over a larger proportion of the local chord than would be the case for an uncambered wing.
Date:
April 20, 1956
Creator:
Phelps, E. Ray
A Wind-Tunnel Investigation of the Effects of Conical Camber for an Airplane Configuration Having a Triangular Wing of Aspect Ratio 2.2
Description:
Memorandum presenting the results of an investigation directed at determining the effectiveness of various amounts and spanwise extents of conical camber on the aerodynamic characteristics of a wing-body-tail combination employing a triangular wing of aspect ratio 2.2. Five cambered wings were tested, all of which were designed for a Mach number of 1.0. Results regarding drag characteristics and lift and moment characteristics are provided.
Date:
April 30, 1957
Creator:
Phelps, E. Ray & Boyd, John W.
Wind-Tunnel Investigation at High Subsonic Speeds of the Effects on Static Stability Characteristics of Various Modifications to a Swept-Wing Fighter-Type Airplane Model
Description:
Memorandum presenting an investigation at high subsonic speeds of a model of a twin-engine swept-wing fighter-type airplane. The model was tested with several different tail configurations and with several wing and engine inlet modifications. Results regarding pitching-moment characteristics, lift and drag characteristics, and lateral derivatives are provided.
Date:
April 30, 1957
Creator:
Goodson, Kenneth W.
Analytical Studies of the Response to Longitudinal Control of Three Airplane Configurations in Landing Approaches
Description:
Memorandum presenting a theoretical investigation to determine the reasons for poor airplane response to longitudinal control. Some effects of airplane configuration on the response, primarily for short time periods, were also determined. Results regarding a comparison of three airplanes, the effect of changes on airplane B, and the effect of changes on airplane C are provided.
Date:
April 9, 1953
Creator:
Bihrle, William, Jr. & Stone, Ralph W., Jr.
Boundary-Layer-Transition and Heat-Transfer Measurements from Flight Tests of Blunt and Sharp 50 Degree Cones at Mach Numbers from 1.7 to 4.7
Description:
Boundary-layer-transition and heat-transfer measurements were obtained from flight tests of blunt and sharp cones having apex angles of 50 deg. The test Mach number range was from 1.7 to 4.7, corresponding to free-stream Reynolds numbers, based on cone base diameter, of 18. 3 x 10(exp 6) and 32.1 x 10(exp 6), respectively. Transition on both models occurred at a local Reynolds number of 1 x 10(exp 6) to 2 X 10(exp 6) based on distance from the stagnation point. Transition Reynolds numbers base…
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Date:
April 18, 1957
Creator:
Chauvin, Leo T. & Speegle, Katherine C.
Preliminary Free-Jet Performance of XRJ43-MA-3 Ram-Jet Engine at a Mach Number of 2.70
Description:
Report discussing an investigation to determine the free-jet performance characteristics of the XRJ43-MA-3 20B3 ram-jet engine at a Mach number of 2.70 at several angles of attack, inlet temperatures, and fuel-air ratios. Information about the inlet supercritical mass-flow ratio, diffuser-outlet Mach number contours, and effect of angle of attack and inlet temperature on engine performance is provided.
Date:
April 15, 1955
Creator:
Welna, Henry J. & Campbell, Carl E.
A Flight Evaluation and Analysis of the Effect of Icing Conditions on the ZPG-2 Airship
Description:
"A series of test flights was conducted by the U. S. Navy over a 3- year period to evaluate the effects of icing on the operation of the ZPG-2 airship. In supercooled. clouds, ice formed only on the forward edges of small protuberances and wires and presented no serious hazard to operation. Ice accretions of the glaze type which occurred in conditions described as freezing drizzle adversely affected various components to a somewhat greater extent" (p. 1).
Date:
April 1958
Creator:
Lewis, William & Perkins, Porter J., Jr.
Effectiveness of Thermal-Pneumatic Airfoil-Ice-Protection System
Description:
From Summary: "Icing and drag investigations were conducted in the NACA Lewis icing research tunnel employing a combination thermal-pneumatic de-icer mounted on a 42-inch-chord NACA 0018 airfoil. The de-icer consisted of a 3-inch-wide electrically heated strip symmetrically located about the leading edge with inflatable tubes on the upper and lower airfoil surfaces aft of the heated area. The entire de-icer extended to approximately 25 percent of chord. A maximum power density of 9.25 watts per…
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Date:
April 13, 1951
Creator:
Gowan, William H., Jr. & Mulholland, Donald R.
Perforated Sheets as a Porous Material for Distributed Suction and Injection
Description:
Note presenting measurements made of the resistance to air flow of a series of perforated metal sheets with open areas ranging from less than 1 percent up to 41 percent. The results showed that the permeability of a perforated sheet is governed principally by its open-area ratio. The number of holes per square inch, the sheet thickness, and the shape of the individual holes had little or no effect on permeability.
Date:
April 1956
Creator:
Dannenberg, Robert E.; Gambucci, Bruno J. & Weiberg, James A.
Flight Investigation to Evaluate the Roll-Rate Stabilization System of the Naval Ordnance Test Station SIDEWINDER Missile at Mach Numbers From 0.9 to 2.3
Description:
Report presenting a flight investigation using a rocket-powered model to evaluate the roll-rate stabilization of the Naval Ordnance Test Station SIDEWINDER missile, which uses aerodynamic damping by gyro-actuated rollerons. Dynamic roll instability was found to occur in flight.
Date:
April 29, 1954
Creator:
Brown, Clarence A., Jr. & Nason, Martin L.
A Method for Determining Cloud-Droplet Impingement on Swept Wings
Description:
From Summary: "The general effect of wing sweep on cloud-droplet trajectories about swept wings of high aspect ratio moving at subsonic speeds is discussed. A method of computing droplet trajectories about yawed cylinders and swept wings is presented, and illustrative droplet trajectories are computed. A method of extending two-dimensional calculations of droplet impingement on nonswept wings to swept wings is presented."
Date:
April 1953
Creator:
Dorsch, Robert G. & Brun, Rinaldo J.
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