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NACA Research Memorandums
180
Atomic Energy Commission Reports
52
NACA Technical Reports
27
University of California Radiation Laboratory Reports
26
Hanford Works Reports
22
HW (Series)
19
Oak Ridge National Laboratory Reports
19
UCRL (Series)
14
BNL (Series)
13
Brookhaven National Laboratory Reports
13
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Abstracts Pertaining to Seaplanes
Report discussing about 400 references pertaining to the hydrodynamic design of seaplanes have been compiled, and the information is presented in the form of abstracts classified under six main headings.
Date:
July 24, 1947
Creator:
Bidwell, Jerold M. & King, Douglas A.
Object Type:
Report
System:
The UNT Digital Library
Additional free-flight tests of the rolling effectiveness of several wing-spoiler arrangements at high subsonic, transonic, and supersonic speeds
From Introduction: "The purpose of the present paper is to present results obtained recently relating to the characteristics of a full-span sharp-edge spoiler with an 0.02-chord projection above the wing surface at several chordwise positions and also to the relative effectiveness of the sharp-edge spoiler and a wedge-type spoiler located at the 80-percent-chord line."
Date:
November 24, 1948
Creator:
Strass, H. Kurt
Object Type:
Report
System:
The UNT Digital Library
Additional results of an investigation at transonic speeds to determine the effects of a heated propulsive jet on the drag characteristics of a series of related afterbodies
From Introduction: "Presented in this report are the basic data obtained from investigation. The data are presented with limited analysis in order to expedite their availability to those concerned with jet-exit-afterbody design."
Date:
September 24, 1956
Creator:
Henry, Beverly Z., Jr. & Cahn, Maurice S.
Object Type:
Report
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.
Object Type:
Report
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
Memorandum presenting an investigation in the Unitary Plan wind tunnel 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 in the presence of the model. Results also included a determination of aileron-spoiler effectiveness, aileron hinge moments, and the effects of wing modifications on model aerodynamic characteristics. The results are presented with minimum analysis.
Date:
June 24, 1958
Creator:
Oehman, Waldo I. & Turner, Kenneth L.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a canard and an outboard-tail airplane model at a Mach number of 2.01
From Introduction: "In order to obtain some insight into the relative merits of canard and outboard-tail control systems at supersonic speeds, a preliminary investigation of a generalized canard and outboard-tail model has been conducted in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 and the results are presented herein."
Date:
March 24, 1958
Creator:
Spearman, M. Leroy & Robinson, Ross B.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a Wing With Quarter-Chord Line Swept Back 45 Degrees, Aspect Ratio 4, Taper Ratio 0.6, and NACA 65A006 Airfoil Section: Transonic-Bump Method
Report discussing a particular wing-body combination that is part of a larger investigation to determine the lift, drag, pitching moment, and root bending moments for various configurations. Information about the aerodynamic characteristics at the tail plane is also provided.
Date:
February 24, 1949
Creator:
Weil, Joseph & Goodson, Kenneth W.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of a wing with quarter-chord line swept back 60 degrees, aspect ratio 2, taper ratio 0.6, and NACA 65A006 airfoil section : transonic bump method
From Introduction: "This paper presents the results of the investigation of the wing-alone and wing-fuselage configurations employing a wing with the quarter-chord line swept back 60^o, aspect ratio 2, taper ratio 0.6, and an NACA 65A006 airfoil section parallel to the free stream."
Date:
February 24, 1950
Creator:
Myers, Boyd C., II & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic characteristics of several jet-spoiler controls on a 45 degree sweptback wing at Mach numbers of 1.61 and 2.01
Report presenting an investigation in the supersonic pressure tunnel at two Mach numbers to determine the aerodynamic characteristics of several jet-spoiler controls on a wing having a 45 degree sweepback of the quarter-chord line, an aspect ratio of 3.5, a taper ratio of 0.3, and an NACA 65A005 airfoil section. Testing indicated that the jet-spoiler effectiveness increased with increasing angle of attack and correlated well with the momentum of jet flow.
Date:
June 24, 1958
Creator:
Lord, Douglas R.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Characteristics of Two Series of Lifting Bodies at Mach Number 6.86
From Introduction: "This paper presents the results of an investigation conducted in the Langley 11-inch hypersonic tunnel to evaluate methods of increasing maximum lift-drag ratio."
Date:
May 24, 1954
Creator:
Ridyard, Herbert W.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Loads on an External Store Adjacent to a 60 Degree Delta Wing at Mach Numbers From 0.75 to 1.96
Report presenting an investigation to determine separately the aerodynamic characteristics of a Douglas Aircraft Company store and a semispan delta-wing-fuselage configuration in the presence of one another. The store was located at the 50-percent-semispan station with the store nose both ahead of and behind the wing leading edge for two longitudinal and three vertical positions.
Date:
April 24, 1956
Creator:
Hadaway, William M.
Object Type:
Report
System:
The UNT Digital Library
Air-Flow Behavior Over the Wing of an XP-51 Airplane as Indicated by Wing-Surface Tufts at Subcritical and Supercritical Speeds
Report presenting the air-flow behavior over the wing of an XP-51 airplane including photographs of tufts attached to the wing surface and chordwise pressure distributions. A comparison of tuft studies from flight results are compared with results from wind-tunnel testing. Three types of flow were observed: steady flow, unsteady flow, and break-away flow are provided.
Date:
April 24, 1947
Creator:
Beeler, De E.
Object Type:
Report
System:
The UNT Digital Library
An analog study of the relative importance of various factors affecting roll coupling
From Introduction: "In this study wide variations in many of the pertinent aerodynamic were investigated at subsonic and supersonic speeds. The effects of large changes in principal axis inclination and mass distribution are also included. The primary purpose of this paper is to summarize the information obtained from the analog calculations and to compare the results with the trends predicted from a slightly modified version of reference 2."
Date:
April 24, 1956
Creator:
Weil, Joseph & Day, Richard E.
Object Type:
Report
System:
The UNT Digital Library
Analysis of a Nuclear Incident in a Redox Dissolver
Since the start of E-metal processing in December, 1958, critical mass control in the Redox dissolvers has been provided by a combination of administrative controls, revised dissolver charging procedures, and new dissolving processes and operation control procedures. These were all based on a maximum allowable charge of E-Metal to the dissolvers which was equivalent to 45 percent of the minimum critical mass.
Date:
August 24, 1959
Creator:
Neely, V. I.
Object Type:
Report
System:
The UNT Digital Library
Analysis of Effects of Inlet Pressure Losses on Performance of Axial-Flow Type Turbojet Engine
From Introduction: "An analytical evaluation of the effects of inlet losses on the net thrust and the fuel economy of an axial-flow-compressor type turbojet engine with a two-stage turbine is presented herein. The analysis is based on engine performance characteristics that were determined from experiments in the NACA Cleveland altitude wind tunnel (references 1 and 2). The experimental investigation did not include tests in which inlet losses were systematically varied, but the effects of these losses can be accurately estimated from the experimentally determined performance characteristics of the engine."
Date:
November 24, 1948
Creator:
Sanders, Newell D. & Palasics, John
Object Type:
Report
System:
The UNT Digital Library
Analysis of Fluorine Addition to the Vanguard First Stage
Memorandum presenting an analysis of the effect of adding fluorine to the Vanguard first-stage oxidant. An increase in specific impulse of 5.74 percent may be obtained with 30 percent fluorine. Charts are provided regarding the vehicle performance increases for a zero-drag vertical trajectory.
Date:
January 24, 1957
Creator:
Tomazic, William A.; Schmidt, Harold W. & Tischler, Adelbert O.
Object Type:
Report
System:
The UNT Digital Library
Analysis of fluorine addition to the vanguard first stage
From Introduction: "This report presents data pertinent to the problem of boosting rocket performance by adding up to 30 percent liquid fluorine to the liquid oxygen of an existing oxygen-hydrocarbon rocket engine."
Date:
January 24, 1957
Creator:
Tomazic, William A.; Schmidt, Harold W. & Tischler, Adelbert O.
Object Type:
Report
System:
The UNT Digital Library
Analysis of the effects of wing interference on the tail contributions to the rolling derivatives
From Introduction: "This report presents calculations of the angularity of the air stream with respect to the vertical tail for a rolling airplane, the interference effects of the wing being taken into account. A discussion of the factors which enter into the calculations is given and equations for applying the side-wash results to the determination of the tail contributions to the rolling-stability derivatives are included. The results are compared with some available experimental data."
Date:
January 24, 1951
Creator:
Michael, William H., Jr.
Object Type:
Report
System:
The UNT Digital Library
Annual Technical Progress Report, AEC Unclassified Programs: Fiscal Year 1968
Annual report with the objectives of evaluating, producing, and maintaining an up-to-date set of basic nuclear data; producing and evaluating multigroup constants; and improving of present day methods of neutronic calculations as related to microscopic and macroscopic nuclear data, for unclassified research sponsored by the U.S. Atomic Energy Commission during FY 1968.
Date:
May 24, 1969
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
An apparatus for measuring rates of discharge of a fuel-injection system
From Introduction: "An apparatus that gives a quick and an accurate measurement of the rate of discharge has been has been designed by the NACA and is described in this report."
Date:
March 24, 1941
Creator:
Dutee, Francis J.
Object Type:
Report
System:
The UNT Digital Library
An apparatus for varying effective dihedral in flight with application to a study of tolerable dihedral on a conventional fighter airplane
From Summary: "An apparatus for varying effective dihedral in flight by means of servo actuation of the ailerons in response to sideslip angle is described. The results of brief flight tests of the apparatus on a conventional fighter airplane are presented and discussed. The results of an investigation employing the apparatus to determine the tolerable (safe for normal fighter operation) range of effective dihedral on the test airplane are presented."
Date:
August 24, 1949
Creator:
Kauffman, William M.; Liddell, Charles J., Jr.; Smith, Allan & Van Dyke, Rudolph D., Jr.
Object Type:
Report
System:
The UNT Digital Library
Application of one part of Von Karman's two-dimensional transonic similarity law to drag data of NACA 65-series wings
Report presenting the use of Von Karman's two-dimensional transonic similarity law as applied to drag data of three different thickness wings with NACA 65-series sections and aspect ratios of 7.6 over a range of Mach numbers. The correlation was found to be satisfactory, with results better in the subsonic range than in the supersonic range.
Date:
August 24, 1948
Creator:
Amer, Kenneth B.
Object Type:
Report
System:
The UNT Digital Library
Application of Spring Tabs to Elevator Controls
Equations are presented for calculating the stick-force characteristics obtained with a spring-tab type of elevator control. The main problems encountered in the design of a satisfactory elevator spring tab are to provide stick forces in the desired range, to maintain the force per g sufficiently constant throughout the speed range, to avoid undesirable "feel" of the control in ground handling or in flight at low airspeeds, and to prevent flutter. Examples are presented to show the design features of spring tabs required to solve these problems for airplanes of various sizes.
Date:
November 24, 1944
Creator:
Phillips, William H.
Object Type:
Report
System:
The UNT Digital Library
Application of supersonic vortex-flow theory to the design of supersonic impulse compressor- or turbine-blade sections
From Introduction: "The purpose of this paper is to present an analytical method for the design of two-dimensional related selection of a blade for particular rotor conditions may be made quickly and easily and its performance deduced from tests of representative sections in cascade."
Date:
April 24, 1952
Creator:
Boxer, Emanuel; Sterrett, James R. & Wlodarski, John
Object Type:
Report
System:
The UNT Digital Library