Resource Type
Serial/Series Title
NACA Technical Notes
417
NACA Technical Memorandums
380
NACA Technical Reports
359
United States Bureau of Mines Reports
175
NACA Aircraft Circulars
104
United States Geological Survey Reports
98
NACA Special Reports
61
Report of investigations (United States. Bureau of Mines)
36
U.S. Geological Survey bulletin
35
Geological Survey bulletin
27
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The 5- by 7-meter wind tunnel of the DVL
The report contains a description of the DVL wind tunnel. According to the cones fixed, an elliptical stream with axes 5 by 7 meters and length 9 meters, or a stream 6 by 8 meters in cross section and 11 meters in length is available. The top speed with the smaller cone is 65 meters per second. The testing equipment consists of an automatic six-component balance and a test rig for propellers and engines up to 650 horsepower.
Date:
March 1936
Creator:
Kramer, M.
Object Type:
Report
System:
The UNT Digital Library
The 6-Foot-4-Inch Wind Tunnel at the Washington Navy Yard
Report discussing the 6-foot-4-inch wind tunnel and its auxiliary equipment has proven itself capable of continuous and reliable output of data. The real value of the tunnel will increase as experience is gained in checking the observed tunnel performance against full-scale performance. Such has been the case of the 8- by 8-foot tunnel, and for that reason the comparison in the calibration tests have been presented.
Date:
August 1935
Creator:
Desmond, G. L. & McCrary, J. A.
Object Type:
Report
System:
The UNT Digital Library
The 7 by 10 Foot Wind Tunnel of the National Advisory Committee for Aeronautics
This report presents a description of the 7 by 10 foot wind tunnel and associated apparatus of the National Advisory Committee for Aeronautics. Included also are calibration test results and characteristic test data of both static force tests and autorotation tests made in the tunnel.
Date:
October 22, 1931
Creator:
Harris, Thomas A.
Object Type:
Report
System:
The UNT Digital Library
The 1929 Rhon soaring-flight contest
The limitation of the 1929 contest to performance gliders necessitated the establishment of a formula which would make it possible to distinguish between performance gliders and school and training gliders. The sinking speed was therefore adopted as the basis for such a distinction, and the requirement was made that the sinking speed of a performance glider should not exceed 0.8 m/s. The rest of the report details the different entries with regard to design and performance.
Date:
April 1930
Creator:
Lippisch, Alexander
Object Type:
Report
System:
The UNT Digital Library
The 1933 Contest for the Deutsch De La Meurthe Trophy
Report discussing the regulations and airplanes participating in the 1933 contest competing for the Deutsch de la Meurthe trophy.
Date:
October 1933
Creator:
Léglise, Pierre; Hirschauer, L. & Saladin, Raymond
Object Type:
Report
System:
The UNT Digital Library
The 1934 Contest for the Deutsch De La Meurthe Trophy
This report presents a description of the rules, history and new technical innovations in the Deutsch de la Meurthe Cup race of 1934.
Date:
February 1935
Creator:
Léglise, Pierre
Object Type:
Report
System:
The UNT Digital Library
N.A.C.A. Stall-Warning Device
With some airplanes the approach to the stall is accompanied by changes in the behavior, such as tail buffeting or changes in the control characteristics of the airplane so that the pilot obtains a warning of the impending stall. Vith other airplanes it is possible to approach the stall without any perceptible warning other than the reading of the air-speed meter, in which case the danger of inadvertent stalling is considerably greater. Although it is not within the scope of this paper to discuss stalling characteristics, it is desired to point out that in general the danger of inadvertent stalling is greatest with those airplanes that behave worse when the stalling occurs; that is, with airplanes in which the stall starts at the wing tips. A warning of the impending stall is desirable in any case, but is particularly desirable with airplanes of the latter type.
Date:
February 1938
Creator:
Thompson, F. L.
Object Type:
Report
System:
The UNT Digital Library
N.A.C.A. Stall-Warning Indicator
"The stall-warning indicator employs a total-head tube located close to the wing surface in a region wherein local stalling occurs before the main portion of the wing stalls. The artificial production of a localized stalled region is accomplished by means of a sharp leading edge extending a few inches along the span. An abrupt drop in the total pressure relative to a static reference taken at some convenient point occurs at the stall in this region" (p. 1).
Date:
October 1938
Creator:
Thompson, F. L.
Object Type:
Report
System:
The UNT Digital Library
The Aachen Wind-Tunnel Balance
Report discussing a description of the balance in the Aachen wind-tunnel.
Date:
November 1934
Creator:
Wieselsberger, C.
Object Type:
Report
System:
The UNT Digital Library
Accelerated Laboratory Test for Determination of Slacking Characteristics of Coal
Report issued by the U.S. Bureau of Mines on laboratory testing developed to measure the slacking of coals. Testing methods and results are presented. This report includes tables and graphs.
Date:
November 1930
Creator:
Fieldner, Arno Carl; Selvig, W. A. & Frederic, W. H.
Object Type:
Report
System:
The UNT Digital Library
Acceleration, Stress, and Deflection Measurements on the XB-15 Bomber in Gusty Air
From Introduction: "This report presents the results of these tests which cover a total of about 70 flying hours on this airplane."
Date:
June 1939
Creator:
Pearson, Henry A.
Object Type:
Report
System:
The UNT Digital Library
Accelerations in Landing with a Tricycle-Type Landing Gear
"In connection with the application of stable tricycle-type landing gears to transport airplanes, the question arises as to whether certain passengers may not experience relatively great accelerations in an emergency landing. Since the main landing wheels are behind the center of gravity in this type of gear, a hard-braked landing will cause immediate nosing down of the airplane and, when this motion is stopped due to the front wheel striking the ground, there will be some tendency for the rearmost passengers to be thrown out of their seats, The provided rough calculations are designed to show the magnitudes of the various reactions experienced in a severe landing under these circumstances" (p. 1).
Date:
February 1937
Creator:
Jones, Robert T.
Object Type:
Report
System:
The UNT Digital Library
Accident Experience and Cost of Accidents in Washington Coal Mines
Report containing tables detailing cost of mining accidents in Washington state in comparison with other states.
Date:
November 1931
Creator:
Ash, S. H.
Object Type:
Report
System:
The UNT Digital Library
Accounting System and Office-Management Procedure for Medium-Size Metal Mines
Report discussing an accounting system and management of office procedures design for medium-size metal mines, offered by the United States Bureau of Mines, to be more efficient in the mining industry.
Date:
1934
Creator:
Keller, Albert E.
Object Type:
Report
System:
The UNT Digital Library
Accurate Calculation of Multispar Cantilever and Semicantilever Wings With Parallel Webs Under Direct and Indirect Loading
In the present report the computation is actually carried through for the case of parallel spars of equal resistance in bending without direct loading, including plotting of the influence lines; for other cases the method of calculation is explained. The development of large size airplanes can be speeded up by accurate methods of calculation such as this.
Date:
March 1932
Creator:
Sänger, Eugen
Object Type:
Report
System:
The UNT Digital Library
An Accurate Method of Measuring the Moments of Inertia of Airplanes
From Summary: "This note contains a description of an improved apparatus and procedure used by the NACA for determining the moments of inertia of airplanes. The method used, based on the pendulum theory, is similar to that previously used, but a recent investigation of its accuracy has resulted in the improvements described herein. The error, when using the new apparatus and procedure, has been found to be of the order of 1 per cent."
Date:
October 1930
Creator:
Miller, M. P.
Object Type:
Report
System:
The UNT Digital Library
Activation of hydrocarbons and the octane number
This report presents an examination of the history of research on engine knocking and the various types of fuels used in the investigations of this phenomenon. According to this report, the spontaneous ignition of hydrocarbons doped with oxygen follows the logarithmic law within a certain temperature range, but not above 920 degrees K. Having extended the scope of investigations to prove hydrocarbons, the curves of the mixtures burned by air should then be established by progressive replacement of pure iso-octane with heptane. Pentane was also examined in this report.
Date:
October 1939
Creator:
Peschard, Marcel
Object Type:
Report
System:
The UNT Digital Library
Additional Test Data on Static Longitudinal Stability
From Summary: "The purpose of this investigation was to explore the influence of weights of the controls on the stability with elevator released. The available test data were extended to stability with elevator locked. In this connection the study of the propeller effect seemed of vital importance."
Date:
August 1934
Creator:
Hübner, Walter
Object Type:
Report
System:
The UNT Digital Library
Adhesion of Ice in Its Relation to the De-Icing of Airplanes
From Summary: "The various possible means of preventing ice adhesion on airplane surfaces are critically reviewed. Results are presented of tests of the adhesives forces between ice and various solid and liquid forces. It is concluded that the de-icing of airplane wings by heat from engine exhaust shows sufficient promise to warrant full-scale tests. For propellers, at least, and possibly for certain small areas such as windshields, radio masts, etc. the use of de-icing or adhesion-preventing liquids will provide the best means of protection."
Date:
August 1939
Creator:
Rothrick, A. M. & Selden, R. F.
Object Type:
Report
System:
The UNT Digital Library
Advantages of Oxide Films as Bases for Aluminum Pigmented Surface Coatings for Aluminum Alloys
Report discussing both laboratory and weather-exposure corrosion tests showed conclusively that the protection afforded by aluminum pigmented spar varnish coatings applied to previously anodized aluminum surfaces was greatly superior to that afforded by the same coatings applied to surfaces which had simply been cleaned free from grease and not anodized.
Date:
November 1931
Creator:
Buzzard, R. W. & Mutchler, W. H.
Object Type:
Report
System:
The UNT Digital Library
An Aerodynamic Analysis of the Autogiro Rotor With a Comparison Between Calculated and Experimental Results
This report presents an extension of the autogiro theory of Glauert and Lock in which the influence of a pitch varying with the blade radius is evaluated and methods of approximating the effect of blade tip losses and the influence of reversed velocities on the retreating blades are developed. A comparison of calculated and experimental results showed that most of the rotor characteristics could be calculated with reasonable accuracy, and that the type of induced flow assumed has a secondary effect upon the net rotor forces, although the flapping motion is influenced appreciably. An approximate evaluation of the effect of parasite drag on the rotor blades established the importance of including this factor in the analysis.
Date:
January 17, 1934
Creator:
Wheatley, John B.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Analysis of the Gyroplane Rotating-Wing System
"An aerodynamic analysis of the gyroplane rotating-wing system is presented herein. This system consists of a freely rotating rotor in which opposite blades are rigidly connected and allowed to rotate or feather freely about their span axis. Equations have been derived for the lift, the lift-drag ratio, the angle of attack, the feathering angles, and the rolling and pitching moments of a gyroplane rotor in terms of its basic parameters" (p. 1).
Date:
March 1934
Creator:
Wheatley, John B.
Object Type:
Report
System:
The UNT Digital Library
The Aerodynamic Aspect of Wing-Fuselage Fillets
Report discussing model tests prove the feasibility of enhancing the aerodynamic qualities of wing-fuselage fillets by appropriate design of fuselage and wing roots. Abrupt changes from maximum fuselage height to wing chord must be avoided and every longitudinal section of fuselage and wing roots must be so faired and arranged as to preserve the original lift distribution of the continuous wing. Adapting the fuselage to the curvilinear circulation of the wing affords further improvement. The polars of such arrangements are almost the same as those of the "wing alone," thus voiding the superiority of the high-wing type airplane known with conventional design.
Date:
February 1935
Creator:
Muttray, H.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of a 4-Engine Monoplane Showing Comparison of Air-Cooled and Liquid-Cooled Engine Installations
From Introduction: "An investigation has been conducted in the N.A.C.A. full-scale wind tunnel to determine the aerodynamic characteristics of a 1/4-scale model of a 4-engine monoplane when equipped with comparable air-cooled engine and liquid-cooled engine installations. The air-cooled engine installation consisted of nacelles equipped with N..A.C.A. cowlings and oil coolers located in the leading edge of the wing."
Date:
July 1939
Creator:
Silverstein, Abe & Wilson, Herbert A., Jr.
Object Type:
Report
System:
The UNT Digital Library