Resource Type
Partner
Collection
Technical Report Archive and Image Library
190
National Advisory Committee for Aeronautics Collection
173
Texas State Publications
11
Harris and Eliza Kempner
2
Boy and Girl Scout Annual Reports
1
Docs In The News
1
Federal Communications Reports
1
Rescuing Texas History, 2017
1
Stillwater History Museum at the Sheerar, Stillwater, Oklahoma
1
Texas Cultures Online
1
1 More
Serial/Series Title
NACA Technical Notes
63
NACA Technical Memorandums
41
NACA Technical Reports
35
NACA Special Reports
23
NACA Wartime Reports
10
United States Bureau of Mines Reports
9
Monthly Report of the Attorney General of the State of Texas
8
NACA Advanced Confidential Reports
7
U.S. Geological Survey bulletin
5
United States Geological Survey Reports
5
22 More
Results:
1 - 24 of
208
next
An approximate spin design criterion for monoplanes
"A quantitative criterion of merit has been needed to assist airplane designers to incorporate satisfactory spinning characteristics into new designs. An approximate empirical criterion, based on the projected side area and the mass distribution of the airplane, has been formulated in a recent British report. In the present paper, the British results have been analyzed and applied to American designs. A simpler design criterion based solely on the type and the dimensions of the tail, has been developed: it is useful in a rapid estimation of whether a new design is likely to comply with the minimum requirements for safety in spinning" (p. 1).
Date:
June 1939
Creator:
Seidman, Oscar & Donlan, Charles J.
System:
The UNT Digital Library
The Unsteady Lift of a Finite Wing
Note discussing the lift of a finite wing including the calculations and constants for each step of the lift. This information is compared against the lift of an infinite wing. From Summary: "Unsteady lift function for wings of finite aspect ratio have been calculated by approximate methods involving corrections of the aerodynamic inertia and of the angle of the infinite wing. The starting lift of the finite wing is found to be only slightly less than that of the infinite wing; whereas the final lift may be considerably less. The calculations indicate that the distribution of lift near the start is similar to the final distribution."
Date:
January 1939
Creator:
Jones, Robert T.
System:
The UNT Digital Library
Pressure drop in tank and float vent tubes on diving airplanes
Report presenting an experiment regarding tank and float venting conditions that exist on diving airplanes undergoing rapid changes in altitude. The results indicated that large pressure differences build up between the outside and inside of tanks and floats on diving airplanes unless the correct size of venting tube is used.
Date:
January 1939
Creator:
Waldron, C. D.
System:
The UNT Digital Library
Nomenclature for Aeronautics
The nomenclature for aeronautics presented in this Report No. 474 is a revision of the last previous report on this subject (i.e., Report no. 240.) This report is published for the purpose of encouraging greater uniformity and precision in the use of terms relating to aeronautics, both in official documents of the Government and in commercial publications. Terms in general use in other branches of engineering have been included only where they have some special significance in aeronautics, or form an integral part of its terminology.
Date:
1939
Creator:
unknown
System:
The UNT Digital Library
Corrugated Metal Diaphragms for Aircraft Pressure-Measuring Instruments
Note presenting a description of a large number of corrugated diaphragms of beryllium copper, phosphor bronze, and Z-nickel with geometrically similar outlines but various diameters and thicknesses were formed by hydraulic pressing. The apparatus and technique used in the manufacture, testing, and heat treatment are described. Results regarding pressure-deflection curves, load limit, effect of center reinforcing, snap-action diaphragms, deflection traverse, thickness variations, and concentrated central loads are provided.
Date:
November 1939
Creator:
Wildhack, W. A. & Goerke, V. H.
System:
The UNT Digital Library
Reservoir Characteristics of the Eunice Oil Field, Lea County, New Mexico
Report issued by the U.S. Bureau of Mines on the oil and gas production of the Eunice oil field in southeastern New Mexico. Properties of the oil field, and analysis of the oil and gas produced are presented. This report includes tables, maps, illustrations, and photographs.
Date:
July 1939
Creator:
Anderson, C. C.; Hinson, H. H. & Schroeder, H. J.
System:
The UNT Digital Library
The Iron and Steel Industries of Europe
Report describing the iron and steel industries in Europe, including the availability of raw material sand the economic set-up of each nation covered.
Date:
1939
Creator:
Wright, Charles Will
System:
The UNT Digital Library
Determination of the Profile Drag of an Airplane Wing in Flight at High Reynolds Numbers
Report presenting flight tests to determine the profile-drag coefficients of a portion of the original wing surface of an all-metal airplane and a portion of the wing made aerodynamically smooth and more nearly fair than the original section. Tests were also carried out to determine the point of transition from laminar to turbulent boundary layer and to determine the velocity distribution along the upper surface of the wing.
Date:
1939
Creator:
Bicknell, Joseph
System:
The UNT Digital Library
Tests in the gust tunnel of a model of the XBM-1 airplane
Report presenting testing of a dynamically scaled model of a Navy XBM-1 biplane in the gust tunnel to provide data for use in determining the structure of atmospheric gusts from measurements of the motions of the full-scale airplane in rough air. Records for two flights for several gradients were evaluated to give histories of events during passage through the gust.
Date:
October 1939
Creator:
Donely, Philip & Shufflebarger, C. C.
System:
The UNT Digital Library
Airfoil Theory at Supersonic Speed
From Summary: "A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl airfoil theory of 1918-1919 for incompressible flow. In addition to the profile and induced drags, account must be taken at supersonic flow of still another drag, namely, the wave drag, which is independent of the wing aspect ratio. Both wave and induced drags are proportional to the square of the lift and depend on the Mach number, that is, the ratio of flight to sound speed. In general, in the case of supersonic flow, the drag-lift ratio is considerably less favorable than is the case for incompressible flow."
Date:
June 1939
Creator:
Schlichting, H.
System:
The UNT Digital Library
Preliminary Report on the Characteristics of the N.A.C.A. 4400R Series Airfoils
Report presenting tests made in the variable-density wind tunnel of airfoils of the NACA 4400 series modified by reflex at the trailing edge designed to reduce the pitching moment to the value of -0.03. The modified airfoils are designated the NACA 4400R series.
Date:
March 1939
Creator:
Sherman, Albert
System:
The UNT Digital Library
Preliminary Report on Laminar-Flow Airfoils and New Methods Adopted for Airfoil and Boundary-Layer Investigations
"Recent developments in airfoil-testing methods and fundamental air-flow investigations, as applied to airfoils, are discussed. Preliminary test results, obtained under conditions relatively free from stream turbulence and other disturbances, are presented. Suitable airfoils and airfoil-design principles were developed to take advantage of the unusually extensive laminar boundary layers that may be maintained under the improved testing conditions" (p. 1).
Date:
June 1939
Creator:
Jacobs, Eastman N.
System:
The UNT Digital Library
Effects of Propellers and of Vibration on the Extent of Laminar Flow on the NACA 27-212 Airfoil
Report presenting an investigation of the effects of propellers and of vibration on the extent of laminar flow on the NACA 27-212 airfoil by testing the airfoil in conjunction with a tractor and a pusher propeller and with a mechanical vibrator. The results show that neither the pusher propeller nor vibration with amplitudes up to 0.094 inch and with a frequency of 1650 cycles per minute had any consequential effect on the extent of laminar flow but that the tractor propeller had a very pronounced effect.
Date:
October 1939
Creator:
Hood, Manley J. & Gaydos, M. Edward
System:
The UNT Digital Library
Metal-Mining Practice
Report issued by the U.S. Bureau of Mines over practices of metal mining. As stated in the introduction, "this bulletin summarizes mining practices of a large number of metal mines in the United states and foreign countries. The adaptation of mining methods best suited to the various natural conditions in mines is discussed, and comparative costs are presented" (p. 1). This report includes tables, illustrations, and photographs.
Date:
1939
Creator:
Jackson, Charles Freeman & Hedges, Joseph Harold
System:
The UNT Digital Library
The Effect of Streamlining the Aterbody of an N.A.C.A. Cowling
Report presenting an investigation of the drag and power cost associated with the changing of the nose of a nacelle from a streamline shape to a conventional cowling shape. Full-scale propellers and nacelles were used. The results of the tests showed that the streamline afterbody drag approached that of an airship form and that the added drag due to the open-nose cowling was only a quarter of the drag increase obtained with the other afterbody.
Date:
December 1939
Creator:
Stickle, George W.; Crigler, John L. & Naiman, Irven
System:
The UNT Digital Library
Ground-cooling and flight tests of an airplane equipped with a nose-blower engine cowling
Report presenting flight and ground-cooling tests with a Northrop A-17A attack airplane to determine the merits of a nose-blower engine cowling designed and built at the NACA laboratory. The main objective was to determine the cooling characteristics of the nose blower, especially for ground and low-speed operation. Results regarding the cooling properties, engine pressure drop, and maximum speed and drag are provided.
Date:
October 1939
Creator:
Turner, L. I., Jr.
System:
The UNT Digital Library
Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing
Report presenting an investigation in the 20-foot wind tunnel to determine the drag, propulsive and net efficiencies, and cooling characteristics of several scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18-percent-thick, 5-by-15-foot airfoil. Two 3-blade propellers with differing diameters were tested in conjunction with a 12-inch-diameter nacelle in three positions in front of the wing and with a 16-inch-diameter nacelle in six positions in front of the wing. Lift, drag, cooling-air flow, and propeller characteristics were determined for each arrangement.
Date:
September 1939
Creator:
McHugh, James G.
System:
The UNT Digital Library
Theory of Automatic Control of Airplanes
"Methods of automatically controlling the airplane are reviewed. Equations for the controlled motion including inertia effects of the control are developed and methods of investigating the stability of the resulting fifth and higher order equations are presented. The equations for longitudinal and lateral motion with both ideal and non-ideal controls are developed in dimensionless form in terms of control parameters based on simple dynamic tests of the isolated control unit" (p. 1).
Date:
April 1939
Creator:
Weiss, Herbert K.
System:
The UNT Digital Library
Intermittent-flow coefficients of a poppet valve
"Flow coefficients were determined for the inlet valve of a modern air-cooled cylinder during operation of the valve. The cylinder head with valves was mounted on a large tank that could be evacuated. Operating the valve with a rotating cam allowed air to flow through the valve into the evacuated tank. The change of pressure in the tank was a measure of the amount of air flowing though the valve in a given number of cycles. The flow coefficients were determined from the pressure across the valve, the quantity of air flowing, and the valve-lift curve" (p. 1).
Date:
April 1939
Creator:
Waldron, C. D.
System:
The UNT Digital Library
Wind-Tunnel Tests of Several Forms of Fixed Wing Slot in Combination With a Slotted Flap on an N.A.C.A. 23012 Airfoil
Note presenting tests of several forms of fixed wing slot in a large-chord NACA 23012 airfoil in the closed-throat 7- by 10-foot wind tunnel. The airfoil extended completely across the test section so that two-dimensional flow was approximated. The data are presented in the form of tables of important aerodynamic characteristics for each slot tested and as curves of section lift, profile-drag, and pitching-moment coefficients.
Date:
April 1939
Creator:
Bamber, M. J.
System:
The UNT Digital Library
A flight investigation of the distribution of ice-inhibiting fluids on a propeller blade
Report presenting an investigation of the flow of ice-inhibiting fluids over the blade surfaces of a 12.5-foot-daimeter propeller in flight by discharging dyed fluids at various stations along the leading edges of the blades. The effects on the distribution of varying the fluid composition, the blade-surface roughness, and the orifice design were also observed.
Date:
September 1939
Creator:
Rodert, Lewis A.
System:
The UNT Digital Library
Wind-Tunnel Investigation of an N.A.C.A. 23021 Airfoil With Two Arrangements of a 40-Percent-Chord Slotted Flap
Note presenting an investigation in the 7- by 10-foot wind tunnel of an NACA 23021 airfoil with two arrangements of a 40-percent-chord slotted flap. The effect of slot shape, flap position, and flap deflection on the section aerodynamic characteristics was determined. Results regarding coefficients, precision, plain airfoils, and slotted-flap arrangements are provided.
Date:
September 1939
Creator:
Duschik, Frank
System:
The UNT Digital Library
Combined Beam-Column Stresses of Aluminum-Alloy Channel Sections
The results of a research program to obtain design data on the strength of open-channel aluminum-alloy sections subjected to combined column and beam action. The results of the tests of about 70 specimens were graphed for stresses due to axial load and stresses due to bending loading as functions of length to radius of gyration of the specimens. From these graphs a design chart was derived that is suitable for ready use.
Date:
September 1939
Creator:
Gottlieb, R.; Thompson, T. M. & Witt, E. C.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Effect of Yawing on Lateral-Stability Characteristics 2: Rectangular N.A.C.A. 23012 Wing with a Circular Fuselage and a Fin
Note presenting testing of an N.A.C.A. 23012 rectangular wing with rounded tips in combination with a fuselage of circular cross section at several angles of yaw in the NACA 7- by 10-foot wind tunnel. The model was tested as a high-wing, a midwing, and a low-wing monoplane; for each wing location, tests were made with two amounts of dihedral and with partial-span split flaps. Results regarding the wing and fuselage, fin and fuselage, and wing, fuselage, and fin are provided.
Date:
September 1939
Creator:
Bamber, M. J. & House, R. O.
System:
The UNT Digital Library