Resource Type
Serial/Series Title
NACA Research Memorandums
469
Atomic Energy Commission Reports
367
NACA Technical Notes
338
United States Department of Energy Grand Junction Office Reports
254
GJBX
198
NACA Technical Memorandums
152
United States Geological Survey Reports
149
NACA Wartime Reports
107
Argonne National Laboratory Reports
95
University of California Radiation Laboratory Reports
90
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2,495 Matching Results
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Preliminary Wind-Tunnel Investigation of the Effect of Area Suction on the Laminar Boundary Layer Over an NACA 64A010 Airfoil
Memorandum presenting a preliminary investigation made in the two-dimensional low-turbulence tunnel on an NACA 64A010 airfoil with permeable surfaces to obtain an indication of the stabilizing effect of area suction on the laminar boundary layer. Although the airfoil surface had many waves and irregularities of contour, the data corroborated qualitatively the theoretically predicted stabilizing effect of area suction on a smooth flat plate.
Date:
April 26, 1948
Creator:
Braslow, Albert L.; Visconti, Fioravante & Burrows, Dale L.
Object Type:
Report
System:
The UNT Digital Library
Flight Investigation of Boundary-Layer Transition and Profile Drag of an Experimental Low-Drag Wing Installed on a Figher-Type Airplane
Report presenting a boundary-layer-transition and profile-drag investigation conducted on an experimental low-drag wing installed on a P-47 airplane designated the XP-47F. Measurements were made at a section outside the propeller slipstream with smooth and with standard camouflage surfaces and on the upper surface of a section in the propeller slipstream with the surface smoothed. Results regarding the right wing section outside the slipstream and left wing section in the propeller slipstream are provided.
Date:
April 1945
Creator:
Zalovcik, John A. & Skoog, Richard B.
Object Type:
Report
System:
The UNT Digital Library
Investigation of a 1/22-Scale of the Republic F-105 Airplane in the Langley 8-Foot Transonic Tunnel: Static Longitudinal Stability and Control and Performance Characteristics at Transonic Speeds
Report presenting an investigation of the aerodynamic characteristics of various configurations of the Republic F-105 in the transonic tunnel at Mach numbers from 0.60 to 1.13. Results in this report include the static longitudinal stability and control characteristics, the effect of various configuration modifications on lift-drag ratio, the effect of subsonic and supersonic inlets and external stores, and the effect of area-distribution modifications on performance.
Date:
April 26, 1956
Creator:
Luoma, Arvo A.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Transonic Flutter Investigation of Models of T-Tall of Blackburn NA-39 Airplane
Report discussing a transonic flutter investigation of models of the T-tail of the Blackburn NA-39 airplane. The investigation was made at a variety of Mach numbers at simulated altitudes extending to below sea level. The Mach numbers at which asymmetric flutter and symmetric oscillations occur are presented.
Date:
April 15, 1958
Creator:
Jones, George W., Jr. & Boswinkle, Robert W., Jr.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Various Heat Exchangers for Liquid-Metal Nuclear Turbojet Over Range of Flight and Operating Conditions
Memorandum presenting an analysis of a large number of liquid-metal-to-air heat-exchanger cores for the nuclear-powered liquid-metal turbojet cycle to determine which types yield the best overall net thrust per total engine weight. The performances of all exchangers considered were initially evaluated at a median condition. The performance of the best of each of the four types was compared with that of a shell-and-tube exchanger with the air flowing through the tubes, operating at the same condition.
Date:
April 28, 1958
Creator:
Ragsdale, Robert G.
Object Type:
Report
System:
The UNT Digital Library
Analytical determination of local surface heat-transfer coefficients for cooled turbine blades from measured metal temperatures
From Summary: "Procedures for applying these analytical methods to experimentally measured blade-metal temperatures are presented. Data are presented for the leading and trailing edge of a symmetrical water-cooled blade to illustrate the validity of the methods for those portions of the blade. In addition to the application to turbine blades, the methods can be applied to any heat-transfer apparatus having a profile that can be approximated by the shape discussed."
Date:
April 10, 1950
Creator:
Brown, W. Byron & Esgar, Jack B.
Object Type:
Report
System:
The UNT Digital Library
Interference Effects of Fuselage-Stored Missiles on Inlet Duct Model of an Interceptor-Type Aircraft at Mach Numbers 1.5 to 1.9
Memorandum presenting the effect of missile armament on the performance of an interceptor-type aircraft model at Mach numbers 1.5, 1.7, and 1.9 and at angles of attack up to 19 degrees. The aircraft model was characterized by triangular-shaped normal-shock inlets located at wing roots. Results regarding force measurements, effect of armament on inlet-duct performance, fuselage boundary-layer survey, and total-pressure contours at inlet throat and diffuser exit are provided.
Date:
April 24, 1957
Creator:
Piercy, Thomas G. & Davis, Owen H.
Object Type:
Report
System:
The UNT Digital Library
Survey of Supersonic Inlets for High Mach Number Applications
Report discussing various inlet design philosophies based on the results of testing at Mach numbers up to 5. The most ideal inlet design was found to be one with combined external-plus-internal compression due to problems noted with both external-only and internal-only inlets.
Date:
April 1, 1958
Creator:
Connors, James F. & Allen, John L.
Object Type:
Report
System:
The UNT Digital Library
Wind-Tunnel Measurements at Subsonic Speeds of the Static and Dynamic-Rotary Stability Derivatives of a Triangular-Wing Airplane Model Having a Triangular Vertical Tail
Report presenting the results of oscillation tests to measure the dynamic-rotary stability derivatives of an airplane model at high subsonic speeds. Measurements taken included the damping in pitch, damping in yaw, damping in roll, and the yawing moment due to rolling velocity.
Date:
April 25, 1955
Creator:
Beam, Benjamin H.; Reed, Verlin D. & Lopez, Armando E.
Object Type:
Report
System:
The UNT Digital Library
Method for Estimating Pitching-Moment Interference of Wing-Body Combinations at Supersonic Speed
Report presenting an investigation into the effects of interference at supersonic speeds on the aerodynamic properties of wing-body combinations to determine the pitching moments. The correlation points of various wing-body shapes are provided and suggestions for modifications are made.
Date:
April 17, 1952
Creator:
Kaattari, George E.; Nielsen, Jack Norman & Pitts, William C.
Object Type:
Report
System:
The UNT Digital Library
Recent European Developments in Helicopters
Descriptions are given of two captured helicopters, one driven by electric power, the other by a gasoline engine. An account is given of flight tests of the gasoline powered vehicle. After 15 successful flight tests, the gasoline powered vehicle crashed due to the insufficient thrust. Also discussed here are the applications of helicopters for military observations, for meteorological work, and for carrying radio antennas.
Date:
April 1921
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Testing Airplane Fabrics
"The following considerations determine the strength of airplane fabrics: 1. maximum air forces acting on the surfaces (including local stresses); 2. tensions produced in the fabrics, in the directions of both warp and filling; 3. factor of safety required. The question of the permissible depression of the fabric as affecting the aerodynamic requirements in regard to the maintenance of shape of the section, the tenacity and extensibility of the layer of dope, its strength and its permeability to water is almost as important" (p. 1).
Date:
April 1924
Creator:
Pröll, A.
Object Type:
Report
System:
The UNT Digital Library
The Induction Factor Used for Computing the Rolling Moment Due to the Ailerons
In the following note, prepared for the National Advisory Committee for Aeronautics, this induction factor is determined from the result of a model test, and compared with a formula recently developed by the author. The two results are found to be in substantial agreement.
Date:
April 1924
Creator:
Munk, Max M.
Object Type:
Report
System:
The UNT Digital Library
Longitudinal oscillation of an airplane Part 1: problem and method
Report presenting some theoretical calculations for determining the problems of accelerated and disturbed motion, phenomena in an accidental or intentional disturbance through the deflection of the rudder or elevator, or any other change in the conditions of flight.
Date:
April 1924
Creator:
Fuchs, R. & Hopf, L.
Object Type:
Report
System:
The UNT Digital Library
Torsional Strength of Nickel Steel and Duralumin Tubing as Affected by the Ratio of Diameter to Gage Thickness
"This investigation was made at the request of the Bureau of Aeronautics. Since the ordinary torsion formula is based on elastic resistance to deformation, it is inaccurate for determination of ultimate stresses in thin wall tubing subjected to torsional loads. It has been found that the torsional modulus of rupture varies with the ratio of diameter to gage thickness and the object of these tests was to determine the extent of these variations for subject materials. This is somewhat of a prorogation of work done by the Army Air Service at McCook Field" (p. 1).
Date:
April 1924
Creator:
Otey, N. S.
Object Type:
Report
System:
The UNT Digital Library
Comparing the Performance of Geometrically Similar Airplanes
"This note has been prepared for the National Advisory Committee for Aeronautics. It deals with the model rules relating to aeronautical problems, and shows how the characteristics of one airplane can be determined from those of another airplane of different weight or size, and of similar type. If certain rules for the ratios of the dimensions, the weights and the horsepower are followed, a small low-powered airplane can be used for obtaining information as to performance, stability, controllability and maneuverability of a larger prototype, and contrariwise" (p. 1).
Date:
April 1924
Creator:
Munk, Max M. & Warner, Edward P.
Object Type:
Report
System:
The UNT Digital Library
Some effects of rainfall on flight of airplanes and on instrument indications
"Several possible effects of heavy rain on the aerodynamic performance of an airplane and of heavy rain and associated atmospheric phenomena on the indications of flight instruments are briefly considered. It is concluded that the effects of heavy rain on the performance of an airplane are not so great as to force the airplane down from moderate altitudes. Serious malfunctioning of the air-speed indicator may occur, however, as a result of flooding of the pitot-static head and subsequent accumulation of water in the air-speed pressure line" (p. 1).
Date:
April 1941
Creator:
Rhode, Richard V.
Object Type:
Report
System:
The UNT Digital Library
Effect of Aging on Mechanical Properties of Aluminum-Alloy Rivets
"Curves and tabular data present the results of strength tests made during and after 2 1/2 years of aging on rivets and rivet wire of 3/16-inch nominal diameter. The specimens were of aluminum alloy: 24S, 17S, and A17S of the duralumin type and 53S of the magnesium-silicide type" (p. 1).
Date:
April 1941
Creator:
Roop, Frederick C.
Object Type:
Report
System:
The UNT Digital Library
Some Flight Data for the Chance Vought Regulus 2 Missile
Report discussing tests of a model of the Chance Vought Regulus II missile to determine the lift, static stability, dynamic stability, trim, duct information, and drag for a range of Mach numbers.
Date:
April 23, 1956
Creator:
Wineman, Andrew R.
Object Type:
Report
System:
The UNT Digital Library
Rocket-Powered-Model Investigation of the Effects of Aeroelasticity on the Rolling Effectiveness of an 8.06-Percent-Scale McDonnell F3H-1 Airplane Wing at Mach Numbers From 0.5 to 1.4
Report discussing an investigation to determine the effects of aeroelasticity on the rolling effectiveness of a model of a McDonnell F3H-1 airplane wing. The plane was found to be subject to aeroelastic losses that varied with Mach number and altitude.
Date:
April 12, 1954
Creator:
English, Roland D.
Object Type:
Report
System:
The UNT Digital Library
A Review of NACA Research Through 1954 on Boron Compounds as Fuels for Jet Aircraft (Project Zip)
Report discussing a project to determine a high-energy fuel suitable for turbojet-powered aircraft. Components of the project include thermal and combustion properties, experiments with combustors using boron compounds, evaluation of boron fuels in full-scale turbojets with and without afterburners, and boron fuel use in ramjet flights. The most promising fuel found in the report is pentaborane.
Date:
April 12, 1957
Creator:
Olson, Walter T.; Breitwieser, Roland & Gibbons, Louis C.
Object Type:
Report
System:
The UNT Digital Library
Effect of Fuel Injectors and Liner Design on Performance of an Annular Turbojet Combustor With Vapor Fuel
Memorandum presenting a direct-connect duct investigation conducted with a one-quarter segment of a 25.5 inch diameter annular combustor which had been previously developed for liquid fuel injection. The combustor was modified by changing the fuel injectors and the liner design for vapor fuel injection. Results regarding accuracy and reproducibility, combustion efficiency, combustor-outlet temperature profiles, and pressure losses are provided.
Date:
April 6, 1953
Creator:
Norgren, Carl T. & Childs, J. Howard
Object Type:
Report
System:
The UNT Digital Library
Effect of Control Trailing-Edge Thickness or Aspect Ratio on the Oscillating Hinge-Moment and Flutter Characteristics of a Flaptype Control at Transonic Speeds
Control trailing-edge thickness and aspect ratio effect on oscillating hinge-moment and flutter characteristics of flap-type controls. Results regarding damping moments and flutter characteristics and spring moments are provided.
Date:
April 23, 1958
Creator:
Moseley, William C., Jr. & Thompson, Robert F.
Object Type:
Report
System:
The UNT Digital Library
Liquid Hydrogen as a Jet Fuel for High-Altitude Aircraft
Memorandum presenting a review of some of the analytical and experimental studies of the use of liquid hydrogen as a jet-engine fuel and which show the possible extension of aircraft performance that will follow adequate research and development effort on the problem of its use.
Date:
April 15, 1955
Creator:
Silverstein, Abe & Hall, Eldon W.
Object Type:
Report
System:
The UNT Digital Library