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NACA Research Memorandums
121
Atomic Energy Commission Reports
44
Hanford Works Reports
16
University of California Radiation Laboratory Reports
15
Oak Ridge National Laboratory Reports
12
NACA Technical Reports
9
ORNL (Series)
8
HW (Series)
7
AEC research and development report
5
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Maximum-Lift Investigation at Mach Numbers From 0.05 to 1.20 of a Wing With Leading Edge Swept Back 42 Degrees
Report presenting an investigation at subsonic and transonic speeds to determine the aerodynamic characteristics of three geometrically similar wings with 42 degree sweepback of the leading edge, aspect ratio 4, taper ratio 0.625, and NACA 64(sub)1-112 airfoils. The lift, drag, and pitching-moment characteristics are provided.
Date:
February 14, 1950
Creator:
Turner, Thomas R.
Object Type:
Report
System:
The UNT Digital Library
Pressure Distributions on the Blade Sections of the NACA 10-(3)(049)-033 Propeller Under Operating Conditions
A report in a series of five that present unanalyzed pressure data obtained in tests of five full-scale propellers with NACA 16-series blade sections. Pressure distributions on the blade sections were measured under operating conditions to determine the aerodynamic characteristics of each blade section. This particular report presents information for nine radial stations of the NACA 10-(3)(049)-033 propeller.
Date:
February 14, 1950
Creator:
Gray, W. H. & Hunt, Robert M.
Object Type:
Report
System:
The UNT Digital Library
Stability and control characteristics at low speed of a 1/4-scale Bell X-5 airplane model: Longitudinal stability and control
Report presenting an investigation of the low-speed longitudinal stability and control characteristics of a scale model of a Bell X-5 airplane design with various leading-edge slat and trailing-edge flap arrangements. A marked increase in stability with increasing sweep angle at low lift coefficients was noted. Results regarding the basic longitudinal characteristics, leading-edge slats, trailing-edge flaps, and longitudinal control are provided.
Date:
March 14, 1950
Creator:
Kemp, William B., Jr.; Becht, Robert E. & Few, Albert G., Jr.
Object Type:
Report
System:
The UNT Digital Library
Static Longitudinal Stability of a Tandem-Coupled Bomber-Fighter Airplane Configuration Proposed by All American Airways, Inc.
"At the request of the Air Materiel Command an investigation was made in the Langley free-flight tunnel to determine the static longitudinal stability and control characteristics of models coupled together in a tandem configuration proposed by All American Airways, Inc. Force tests were made using 1/20-scale models of B-29 end F-80 airplanes to determine the effects of coupling the fighter to the tail of the bomber. The results of the investigation showed that for the bomber alone the aerodynamic center was 0.21 mean aerodynamic chord behind the center of gravity (stable) but that for the tandem configuration the aerodynamic center was 0.09 mean aerodynamic chord forward of the center of gravity, of the combination (unstable)" (p. 1).
Date:
March 14, 1950
Creator:
Hewes, Donald E.
Object Type:
Report
System:
The UNT Digital Library
Spectrophotometry of Neptunium in Perchloric Acid Solutions
Report discussing a study testing features of the absorption spectra of different oxidation states of neptunium and perchloric acid concentration's effects on the spectra. Data regarding a disproportionation reaction present in neptunium(V) solutions in concentrated acid is included.
Date:
April 14, 1950
Creator:
Sjoblom, R. K. & Hindman, J. C.
Object Type:
Report
System:
The UNT Digital Library
Urine Assay Procedure at the Mound Laboratory : Final Report
The following report analyzes experiments on urinary samples of personnel who were exposed to radioactive materials. This report describes the procedure employed for this assay, and data to show its performance and reasons for its present course are presented.
Date:
April 14, 1950
Creator:
Spoerl, E. S.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of a Supersonic Aircraft Configuration Having a Tapered Wing With Circular-Arc Sections and 40 Degree Sweepback: Static Lateral Stability Characteristics at Mach Numbers of 1.40 and 1.59
"An investigation has been conducted in the Langley 4- by 4-foot supersonic tunnel to determine the static lateral stability characteristics of a supersonic aircraft configuration at Mach numbers of 1.40 and 1.59. The model had a 40 degree sweptback wing with 10-percent-thick circular-arc sections normal to the quarter-chord line. The results of the investigation indicated high directional stability that decreased with increasing Mach number and positive effective dihedral that was essentially invariant with lift coefficient and Mach number" (p. 1).
Date:
June 14, 1950
Creator:
Spearman, M. Leroy
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Investigation of a 0.6-Scale Model of Hughes MX-904 Tail Surface at Supersonic Speeds: Several Combinations of the Tail With Each of Two Foreshortened Body Segments
"An investigation has been made in the Langley 9- by 12-inch super-sonic blowdown tunnel at Mach numbers of 1.62 and 1.96 of a partial-span body with one tail surface, designed for use on the Hughes Falcon (MX-904) missile. The present paper extends the work reported in NACA-RM-SL50E10. Force and moment data including elevator hinge moment were obtained for the conditions of the tail in the presence of a small segment of the fore-shortened body, in the presence of a semi-span body and attached to a semi-span body, and for the condition of the foreshortened semi-span body alone" (p. 1).
Date:
July 14, 1950
Creator:
Guy, Lawrence D. & Conner, D. William
Object Type:
Report
System:
The UNT Digital Library
Experimental and Analytical Study of Balanced-Diaphragm Fuel Distributors for Gas-Turbine Engines
"A method of distributing fuel equally to a plurality of spray nozzles in a gas-turbine engine by means of balanced-diaphragm fuel distributors is presented. The experimental performance of three of eight possible distributor arrangements are discussed. An analysis of all eight arrangements is included. Criterions are given for choosing a fuel-distributor arrangement to meet specific fuel-system requirements of fuel-distribution accuracy, spray-nozzle pressure variations, and fuel-system pressures" (p. 1).
Date:
August 14, 1950
Creator:
Straight, David M. & Gold, Harold
Object Type:
Report
System:
The UNT Digital Library
Measurements of the effect of trailing-edge thickness on the zero-lift drag of thin low-aspect-ratio wings
Report presenting an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models with tapered 4-percent-thick wings for a range of Mach numbers. Wings with an aspect ratio of 3.11 and trailing-edge thickness of 0, 1/3 maximum thickness, 2/3 maximum thickness, and 3/3 maximum thickness were tested.
Date:
August 14, 1950
Creator:
Morrow, John D.
Object Type:
Report
System:
The UNT Digital Library
Penetration of Liquid Jets into a High-Velocity Air Stream
Data are presented showing the penetration characteristics of liquid jets directed approximately perpendicular to a high-velocity air stream for jet-nozzle-throat diameters from 0.0135 to 0.0625 inch, air stream densities from 0.0805 to 0.1365 pound per cubic foot, liquid jet velocities from 168.1 to 229.0 feet per second and a liquid jet density of approximately 62 pounds per cubic foot. The data were analyzed and a correlation was developed that permitted the determination of the penetration length of the liquid jet for any operation condition within the range of variables investigated.
Date:
August 14, 1950
Creator:
Chelko, Louis J.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Downwash, Sidewash, and Mach Number Distribution Behind a Rectangular Wing at a Mach Number of 2.41
"An investigation of the nature of the flow field behind a rectangular wing of circular arc cross section has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured by means of a weathercocking vane. Theoretical calculations have been made to obtain the variation of both downwash and sidewash with angle of attack by using the superposition method of Lagerstrom, Graham, and Grosslight" (p. 1).
Date:
September 14, 1950
Creator:
Adamson, David & Boatright, William B.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Downwash, Sidewash, and Mach Number Distribution Behind a Rectangular Wing at a Mach Number of 2.41
"An investigation of the nature of the flow field behind a rectangular circular-arc wing has been conducted in the Langley 9-inch supersonic tunnel. Pitot- and static-pressure surveys covering a region of flow behind the wing have been made together with detailed pitot surveys throughout the region of the wake. In addition, the flow direction has been measured using a weathercocking vane measurements. Theoretical calculations of the variation of both downwash and sidewash with angle of attack using Lagerstrom's superposition method have been made" (p. 1).
Date:
September 14, 1950
Creator:
Adamson, D. & Boatright, William B.
Object Type:
Report
System:
The UNT Digital Library
Effects of sweep on the damping-in-roll characteristics of three sweptback wings having an aspect ratio of 4 at transonic speeds
Report presenting the damping-in-roll characteristics of three wings with an aspect ratio of 4, a taper ratio of 0.6, an NACA 65A006 airfoil section, and three different sweep angles at a range of Mach numbers and angles of attack. The data were obtained in the 7- by 10-foot tunnel transonic bump by utilizing the twisted-wing technique. Results regarding the damping-in-roll parameter, angle of attack, and lift-curve slope are provided.
Date:
December 14, 1950
Creator:
Lockwood, Vernard E.
Object Type:
Report
System:
The UNT Digital Library
Measurements of an Iron and Borated Water Shield in the Lid Tank : Experiment 10
The following report measures a shield mockup in three regions: the first made almost entire of iron; the second, transition, region is made of various thicknesses of B4C; and the third region was borated water. The iron samples used in the experiments were made in the form of rectangular plates and place in the lid tank; however, the plates were not completely flat and created a water gap that was measured in this report.
Date:
December 14, 1950
Creator:
Blizard, E. P. & Clifford, C. E.
Object Type:
Report
System:
The UNT Digital Library
Force and pressure characteristics for a series of nose inlets at Mach numbers from 1.59 to 1.99 3: conical-spike all-external-compression inlet with supersonic cowl lip
Memorandum presenting an investigation conducted in the Lewis 8- by 6-foot supersonic wind tunnel to determine the force and pressure characteristics of an all-external compression inlet with a conical spike and a supersonic cowl lip. Measurements of lift, drag, pitching moment, and internal and external pressures were made at free-stream Mach numbers of 1.59, 1.79, and 1.99 for a range of mass-flow ratios and angles of attack to 10 degrees.
Date:
February 14, 1951
Creator:
Weinstein, Maynard I. & Davids, Joseph
Object Type:
Report
System:
The UNT Digital Library
Preliminary Transient Performance Data for Afterburner Operation of Westinghouse Electronic Power Regulator on XJ34-WE-32 Turbojet Engine in Altitude Wind Tunnel
"At the request of the Bureau of Aeronautics, Department of the Navy, an investigation of the Westinghouse XJ34-WE-32 turbojet engine is being conducted in the NACA Lewis altitude wind tunnel to determine the steady-state and transient operating characteristics of the controlled and uncontrolled engine at various altitudes and ram pressure ratios. As part of this program, transient performance data that illustrate the operation of the engine is obtained in the form of oscillographic traces. Similar data for engine operation in the afterburning range, covering a range of throttle settings from the minimum value giving rated speed (throttle position, 72 degrees) to full afterburning (throttle position, 110 degrees), is presented herein" (p. 1).
Date:
February 14, 1951
Creator:
Vasu, George; Schwent, Glennon V. & Ketchum, James R.
Object Type:
Report
System:
The UNT Digital Library
Supersonic Tunnel Investigation by Means of Inclined-Plate Technique to Determine Performance of Several Nose Inlets Over Mach Number Range of 1.72 to 2.18
Memorandum presenting a study using a suspended flat plate to continuously vary the Mach number in the 18- by 18-inch Mach number 1.91 supersonic tunnel. The technique was applied to the determination of pressure recovery and mass-flow characteristics of four supersonic nose inlets over the Mach number range produced. Results regarding the plate calibration and inlet performance are provided.
Date:
February 14, 1951
Creator:
Fox, Jerome L.
Object Type:
Report
System:
The UNT Digital Library
V. Multiplying Lattices of the Hollow Type
A two-group approximation of the fission ratios and Pu production in an infinite hollow matrix is developed
Date:
February 14, 1951
Creator:
Brown, Harold
Object Type:
Report
System:
The UNT Digital Library
Description and Investigation of a Dynamic Model of the XH-17 Two-Blade Jet Driven Helicopter
Report presenting a description and results of an investigation of a model of the XH-17 two-blade, jet-powered helicopter. Tests were made with a standard configuration and with several modifications, including varying the size of blade counterweights, changing the control stiffness and chordwise bending stiffness of the blades, and varying the pylon and undercarriage damping and spring constants. Results regarding flutter testing, ground-vibration tests, and three-per-revolution rotor-blade unsymmetric bending oscillations are provided.
Date:
March 14, 1951
Creator:
Brooks, George W. & Sylvester, Maurice A.
Object Type:
Report
System:
The UNT Digital Library
Time Histories of the Aerodynamic Loads on the Vertical and Horizontal Tail Surfaces of a Jet-Powered Bomber Airplane During Sideslip Maneuvers at Approximately 20,000 Feet
Report presenting time histories of the aerodynamic loads on the vertical and horizontal tail surfaces of a jet-powered bomber airplane (B-45A) in sideslip maneuvers. Information about maximum measured rudder and fin loads, maximum total vertical-tail load, horizontal-tail-load dissymmetry, maximum elevator loads, and elevator-load dissymmetry is provided.
Date:
March 14, 1951
Creator:
Cooney, T. V. & McGowan, William A.
Object Type:
Report
System:
The UNT Digital Library
Wing-on and wing-off longitudinal characteristics of an airplane configuration having an thin unswept tapered wing of aspect ratio 3, as obtained from rocket-propelled models at Mach numbers from 0.8 to 1.4
Report presenting flight tests at Mach numbers from 0.8 to 1.4 on three rocket-propelled general research models of airplane configurations. Two models had thin unswept tapered wings of aspect ratio 3 and hexagonal airfoil sections, two wings had different structural stiffness characteristics, and the third model had no wing. Results regarding the static and dynamic longitudinal stability, control, trim, and drag characteristics are provided.
Date:
March 14, 1951
Creator:
Gillis, Clarence L. & Vitale, A. James
Object Type:
Report
System:
The UNT Digital Library
Heat transfer to bodies in a high-speed rarified-gas stream
Report presents the results of an investigation to determine the equilibrium temperature and heat-transfer coefficients for transverse cylinders in a high-speed stream of rarefied gas measured over a range of Knudsen numbers (ratio of molecular-mean-free path to cylinder diameter) from 0.025 to 11.8 and for Mach numbers from 2.0 to 3.3. The range of free-stream Reynolds numbers was from 0.28 to 203. The models tested were 0.0010-, 0.0050-, 0.030-, 0.051-, 0.080-, and 0.126-inch -diameter cylinders held normal to the stream.
Date:
May 14, 1951
Creator:
Stalder, Jackson R.; Goodwin, Glen & Creager, Marcus O.
Object Type:
Report
System:
The UNT Digital Library
Note on flutter of a 60 degree delta wing encountered at low-supersonic speeds during the flight of a rocket-propelled model
From Summary: "An analysis of the flight time history of a rocket-propelled model of a 60 degree delta-wing airplane configuration, fired for the purpose of obtaining zero-lift drag data, indicated wing flutter and subsequent failure at low-supersonic Mach numbers. This flutter occurred during the unpowered decelerating portion of the flight. The behavior of the model during flight is discussed and the mass and stiffness characteristics of a duplicate wing are presented."
Date:
May 14, 1951
Creator:
Lauten, William T., Jr. & Mitcham, Grady L.
Object Type:
Report
System:
The UNT Digital Library