Serial/Series Title
NACA Technical Notes
123
NACA Wartime Reports
92
NACA Research Memorandums
69
Atomic Energy Commission Reports
41
NACA Advanced Restricted Reports
33
NACA Technical Reports
25
NACA Memorandum Reports
22
NACA Advanced Confidential Reports
21
NACA Technical Memorandums
20
NACA Restricted Bulletins
13
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405 Matching Results
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Jet Diffusion in Proximity of a Wall
"When auxiliary jet engines are installed on airframes; as well as in some new designs, the jet engines are mounted in such a way that the jet stream exhausts in close proximity to the fuselage. This report deals with the behavior of the jet in close proximity to a two-dimensional surface. The experiments were made to find out whether the axially symmetric stream tends to approach the flat surface" (p. 1).
Date:
May 1949
Creator:
Küchemann, D.
System:
The UNT Digital Library
Oxidation Characteristics of Molybdenum Disulfide and Effect of Such Oxidation on Its Role as a Solid-Film Lubricant
Note presenting an investigation conducted to determine the oxidation characteristics of molybdenum disulfide and to determine the effect of such oxidation on its role as a solid-film lubricant. A coating of molybdenum disulfide serving as a high-temperature solid-film lubricant maintained low coefficient-of-friction values during its oxidation as long as an effective subfilm of the molybdenum disulfide remained.
Date:
May 1949
Creator:
Godfrey, Douglas & Nelson, Erva C.
System:
The UNT Digital Library
Systematic Investigations of the Effects of Plan Form and Gap between the Fixed Surface and Control Surface on Simple Flapped Wings
"Four component measurements of 12 wings of symmetric profile having flaps with chord ratios t(sub R)/t(sub L) = 0.3 and t(sub R)/t(sub L) = 0.2 are treated in this report. As a result of the investigations, the effects of plan form and gap between fixed surface and control surface have been clarified. Lift, drag, pitching moment, and hinge moment were measured in the control-surface deflection range: -23 deg < or = beta < or = 23 deg and the range of angle of attack: -20 deg < or = alpha < or = 20 deg" (p. 1).
Date:
May 1949
Creator:
Göthert & Röber
System:
The UNT Digital Library
Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Trapezoidal Wing)
The present report, which forms the first of six articles on experiments with airfoils of aspect ratio from 1 to 3 and various planforms, deals with the three- and six-component measurements made on the trapezoidal wing series in the 2.15 x 3-meter wind tunnel of the DVL at the request of the Henschel Aircraft Company.
Date:
May 1949
Creator:
Lange & Wacke
System:
The UNT Digital Library
Trace Elements Reconnaissance in Indiana, Illinois, Missouri, Arkansas, and Kentucky
Report discussing examination of various trace elements by the U.S. Geological Survey in Indiana, Illinois, Missouri, Arkansas, and Kentucky during October and November, 1946.
Date:
May 1949
Creator:
Stratton, Edward V. & Nelson, John M.
System:
The UNT Digital Library
Wind-Tunnel Tests on Various Types of Dive Brakes Mounted in Proximity of the Leading Edge of the Wing
"The present report is concerned with a series of tests on a model airplane fitted with four types of dive flaps of various shapes, positions, and incidence located near the leading edge of the wing (from 5 to 20 percent of the wing chord). Tests were also made on a stub airfoil fitted with a ventral dive (located at 8 percent of the wing chord). The hinge moments of the dive flaps were measured" (p. 1).
Date:
May 1949
Creator:
Lattanzi, Bernardino & Bellante, Erno
System:
The UNT Digital Library
Determination of Uranium by Fluorescence
Abstract: "The uranium content of badly contaminated uranium solutions may be determined quickly using visual comparison methods to an accuracy of [...]. This accuracy may be considerably improved by employing the fluorimeter herein described. Interfering ions and their removal using liquid-liquid extractions are considered."
Date:
May 28, 1948
Creator:
Grimes, W. R. & Clark, F. E.
System:
The UNT Digital Library
Ditching Tests of a 1/24-Scale Model of the Lockheed XR60-1 Airplane, TED No. NACA 235
"The ditching characteristics of the Lockheed XR60-1 airplane were determined by tests of a 1/24-scale dynamic model in calm water at the Langley tank no. 2 monorail. Various landing attitudes, flap settings, speeds, and conditions of damager were investigated. The ditching behavior was evaluated from recordings of decelerations, length of runs, and motions of the model" (p. 1).
Date:
May 28, 1948
Creator:
Fisher, Lloyd J. & Cederborg, Gibson A.
System:
The UNT Digital Library
Effect of Temperature and Reactivity Changes in Operation of the Los Alamos Plutonium Reactor
The operation of the Fast Reactor is considered in terms of normal equilibrium conditions and normal shut-down. The proposed loading, control rod adjustment and subsequent "floating" operation are discussed. Safety devices and interlocks are described. Temperature and reactivity changes are examined with respect to various system failures, phase changes, and "flashing" of the reactor. Slow changes due to faulty slug cooling are also considered. The calculations were initially based upon 10 kw operation. Performance tests of the mercury system now indicate that 20-kw operation may be feasible.
Date:
May 28, 1948
Creator:
Hall, David B. & Hall, Jane H.
System:
The UNT Digital Library
Free-flight investigation of 16-inch diameter supersonic ram-jet unit
Report presenting an investigation of a series of 16-inch-diameter ramjet engine in free flight in order to determine the performance of ramjet units in flight at supersonic speeds and to study methods for improving the performance. Results regarding the telemeter data recorded by ground stations, static pressures, variation of altitude with time after release, variation of flight velocities, and fuel-air ratio are provided. Partial failure of the measuring equipment prevented a complete evaluation of engine performance.
Date:
May 28, 1948
Creator:
Kinghorn, George F. & Disher, John H.
System:
The UNT Digital Library
High-speed wind-tunnel tests of a 1/78-scale model of the Lockheed YP-80A airplane
Report presenting an investigation to determine the high-speed performance and static longitudinal stability and control characteristics of a model of the Lockheed YP-80A airplane. High-speed aerodynamic characteristics are presented for speeds up to Mach number 0.96. Results regarding the scale effects, longitudinal stability, and longitudinal-control effectiveness are provided.
Date:
May 28, 1948
Creator:
Olson, Robert N. & Lawrence, Leslie F.
System:
The UNT Digital Library
Ice protection of turbojet engines by inertia separation of water 1: alternate-duct system
Aerodynamic and icing investigations of internal water-inertia separation inlets designed to prevent automatically entrance of large quantities of water into a turbojet engine in icing conditions was conducted on a one-half scale model. A simplified analytical approach to the design of internal water-inertia separation inlets is included. Results show that in order to be effective in preventing screen and guide-vane icing for an inlet of this type, a ram-pressure recovery of 75 percent was attained at design inlet-velocity ratio in an icing condition. For nonicing operation, ram-pressure recovery is comparable to direct-ram inlet.
Date:
May 28, 1948
Creator:
von Glahn, Uwe
System:
The UNT Digital Library
Investigation of the diborane - hydrogen peroxide propellant combination
Report presenting the results of two runs made with liquid diborane and hydrogen peroxide in a small-scale rocket engine. The first run was very erratic and modifications were made to the testing apparatus and procedures for the second run. In the second run, the combustion started immediately and continued smoothly for 12 seconds of operation.
Date:
May 28, 1948
Creator:
Rowe, William H.; Ordin, Paul M. & Diehl, John M.
System:
The UNT Digital Library
Aerodynamic Characteristics of Several NACA Airfoil Sections at Seven Reynolds Numbers From 0.7 X 10(Exp 6) to 9.0 X 10(Exp 6)
Report presenting an investigation of the two-dimensional aerodynamic characteristics of several NACA airfoil sections at four Reynolds numbers. Results regarding the minimum drag, maximum lift, lift-curve slope, and angle of zero lift and pitching moment are provided.
Date:
May 27, 1948
Creator:
Loftin, Laurence K., Jr. & Poteat, M. Irene
System:
The UNT Digital Library
An exploratory investigation of the relative merits of split and chord-extension flaps on a 45 degrees swept-back wing
Report presenting a wind-tunnel investigation to explore the merits of split and chord-extension flaps on a 45 degree sweptback wing. Testing occurred at low speed on a semispan model equipped with split flaps of 60 and 90-percent span and a full-span chord-extension flap. Results regarding split flaps, chord-extension flap, and resultant lift coefficients after balancing pitching-moment coefficients are provided.
Date:
May 27, 1948
Creator:
Hopkins, Edward J.
System:
The UNT Digital Library
Summary of the Research Progress Meeting
Technical report includes three reports of research progress: 1)Neutron scattering by A. Bratenahl; 2) Nuclear Cross Sections, Norman Knable.
Date:
May 27, 1948
Creator:
Wakerling, R. K.
System:
The UNT Digital Library
Physico-chemical Studies of U-Compounds in Solution : Progress Report, February 1945
This progress report discusses progress on oxidation-reduction studies, including polarography, as well as the Uranium-complex formation including electrical transport and spectro-photometric work. This report covers the work done in the period of February of 1945.
Date:
May 26, 1948
Creator:
Tishkoff, G. H. & Fanta, Paul E.
System:
The UNT Digital Library
Theoretical performance of some rocket propellants containing hydrogen, nitrogen, and oxygen
From Summary: "Theoretical performance data including nozzle-exit temperature, specific impulse, volume specific impulse and composition, temperature, and mean molecular weight of reaction products based on frozen equilibrium and isentropic expansion are presented for 13 propellant combinations at reaction pressure of 300 pounds per square inch absolute and expansion ratio of 20.4. On basis of maximum specific impulse alone, five fuels had the following order for any given oxidant: liquid hydrogen, hydrazine, liquid ammonia, and either hydrazine hydrate or hydroxylamine. Three oxidants with a given fuel had the following order: liquid ozone, liquid oxygen, and 100-percent hydrogen peroxide."
Date:
May 26, 1948
Creator:
Miller, Riley O. & Ordin, Paul M.
System:
The UNT Digital Library
Preliminary Investigation at a Mach Number of 1.9 and a Reynolds Number of 2,200,000 of Three Ailerons Applicable to the Bell XS-2 Airplane Design
Report presenting testing of a 42.7 degree sweptback tapered wing with three types of ailerons tested at a Mach number of 1.9 and a Reynolds number of 2,200,000; the wing geometry was similar to that of an XS-2 airplane. The purpose of the investigation was to determine the effectiveness of ailerons at these specified flight characteristics. Results regarding the aerodynamic characteristics of the wing are also provided.
Date:
May 25, 1948
Creator:
Sivells, James C. & Conner, D. William
System:
The UNT Digital Library
Preliminary Report on the Hydrolytic Behavior of Cerium (IV)
The following report analyzes the hydrolytic behavior of cerium and compares them with the actinides of uranium and plutonium.
Date:
May 25, 1948
Creator:
Kraus, K. A.; Holmberg, R. W. & Nelson, F.
System:
The UNT Digital Library
The Ratio of Amino Acid Nitrogen to Creatinine in the Urine as a Sensitive Test for Uranium Poisoning
Report discussing experiments that were performed to determine whether amino acids in urine could be used as a test of subtle uranium poisoning.
Date:
May 25, 1948
Creator:
Berke, Harry & Rothstein, A.
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Low-Speed Stability and Control Characteristics of a Model With a Sweptback Vee Tail and a Sweptback Wing
Report presenting testing in the 300 mph tunnel of a model with a sweptback vee tail and a sweptback wing to determine its low-speed stability and control characteristics. The results are compared to testing with the same tail panel with zero dihedral on the same wing-fuselage combination. The longitudinal stability characteristics, downwash at the tail, longitudinal control characteristics, lateral stability characteristics, and rudder control characteristics are provided.
Date:
May 25, 1948
Creator:
Polhamus, Edward C.
System:
The UNT Digital Library
Current Status of Longitudinal Stability
The problems of static and dynamic longitudinal stability both at high speeds and at low speeds are discussed and data are presented which indicate recent progress made in the solution of these problems.
Date:
May 24, 1948
Creator:
Donlan, Charles J.
System:
The UNT Digital Library
Current Status of Longitudinal Stability
Report presenting an investigation of the problems of static and dynamic longitudinal stability both at high speeds and low speeds as well as information about progress that has been made to solve these problems. The incorporation of large amounts of sweepback on both the wing and horizontal tail can improve the rate of trim changes and stability. Longitudinal stability has been attained for configurations with a sweep angle of 45 degrees with stall-control devices, but experimental proof is needed for these devices.
Date:
May 24, 1948
Creator:
Donlan, Charles J.
System:
The UNT Digital Library