Serial/Series Title
NACA Technical Notes
417
NACA Technical Memorandums
380
NACA Technical Reports
359
NACA Aircraft Circulars
104
NACA Special Reports
61
NACA Wartime Reports
15
NACA Advanced Confidential Reports
11
NACA Annual Reports
10
NACA Memorandum Reports
3
Technical note (United States. National Advisory Committee for Aeronautics)
2
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1,346 Matching Results
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The Farman Night Bombers 211 and 212 (French): Four-Engine High-Wing Monoplanes
Circular presenting a description of the Farman night bombers 211 and 212, which are four-engine high-wing monoplanes that are equipped with different engines. Details of the wing structure, fuselage, tail surface and controls, landing gear, power plant, characteristics, performance, drawings, and photographs are provided.
Date:
July 1932
Creator:
unknown
System:
The UNT Digital Library
Fokker F.XX Commercial Airplane (Dutch): A High-Wing Cantilever Monoplane
Circular describing the Fokker F.XX, which is a three-engine high-wing cantilever monoplane with retractable landing gear and tail wheel. Details of the wing, fuselage, cockpit, cabin, covering and cowling, control surfaces, landing gear, power plant, fuel and oil systems, characteristics, drawings, and photographs are provided.
Date:
February 1934
Creator:
unknown
System:
The UNT Digital Library
Polish P Type Single-Seat Fighters: All-Metal Gull-Type Wing Monoplanes
Circular describing the Polish P.I and P.VIII airplanes, which are both all-metal gull-type wing monoplanes that differ in the type of engine used, their wing area, and their landing gears. Details of the components, design, differences, characteristics, load distribution, performance, drawings, and photographs are provided.
Date:
March 1931
Creator:
unknown
System:
The UNT Digital Library
Airplane Flight in the Stratosphere
This brief survey of the problems encountered in high-altitude flight deals in particular with the need for high lift coefficient in the wings, large aspect ratios in the wings, and also the problem of hermetically sealing the cabin.
Date:
February 1932
Creator:
de Caria, Ugo
System:
The UNT Digital Library
Static Longitudinal Stability Of "Ente" Airplanes
The stability conditions of Ente (duck) airplanes are investigated in this report. In developing the formulas, which afford an approximate solution, the unimportant effect of the height of the C.G. and the moment of the residual resistance are neglected. The effect of downwash from the forward horizontal empennage on the wing are also disregarded.
Date:
March 1931
Creator:
Kiel, Heinrich Georg
System:
The UNT Digital Library
The Vortex Theory and Its Significance in Aviation
This report will present ideas closely related to the vortex conception and illustrate them in the simplest possible terms. In addition to these general considerations, this report will attempt to show the application of the vortex theory in connection with the wing theory.
Date:
July 1930
Creator:
Betz, A.
System:
The UNT Digital Library
Riveting in Metal Airplane Construction Part 1 : Riveting Methods and Equipment in German Metal Airplane Construction
"Although all constructors in Germany use duralumin quite frequently, and prefer cold riveting exclusively for permanent (nondetachable) connections of individual structural components, their methods and equipment are very diversified. The differences are due to a great extent to the diversity of structural types and to the special shapes of the individual subassemblies. The results is that different manufacturers have developed totally different riveting methods, as well as entirely different working methods" (p. 1).
Date:
December 1930
Creator:
Pleines, Wilhelm
System:
The UNT Digital Library
Göttingen Six-Component Scale Measurements on a Junkers A 35 Airplane Model
The suggestion for the measurements collected in this report was prompted by the results of spinning experiments. For the theoretical spinning investigations there was a lack of data on lateral force, yawing, and rolling moment of airplanes.
Date:
October 1930
Creator:
Blenk, Hermann
System:
The UNT Digital Library
Problems Concerning the Stability and Maneuverability of Airplanes
"The stability of an airplane can be easily determined by wind-tunnel tests, especially by simple tests with models mounted wind-vane fashion. However, each stability curve plotted by this method is valid only for a certain setting of the corresponding control surface, i.e., it characterizes the stability of the airplane with the control stick in a given position. The problems thus defined are studied from the point of view of longitudinal and transverse stability. Directional stability is not included in this study" (p. 1).
Date:
March 1932
Creator:
Biche, Jean
System:
The UNT Digital Library
The Transference of Heat From a Hot Plate to an Air Stream
The object of the present study was to define experimentally the field of temperature and velocity in a heated flat plate when exposed to an air stream whose direction is parallel to it, then calculate therefrom the heat transference and the friction past the flat plate, and lastly, compare the test data with the mathematical theory. To ensure comparable results, we were to actually obtain or else approximate: a) two-dimensional flow; b) constant plate temperature in the direction of the stream. To approximate the flow in two dimensions, we chose a relatively wide plate and measured the velocity and temperature in the median plane.
Date:
April 1931
Creator:
Elias, Franz
System:
The UNT Digital Library
Clerget 100 Hp Heavy-Oil Engine
A complete technical description of the Clerget heavy-oil engine is presented along with the general characteristics. The general characteristics are: 9 cylinders, bore 120 mm, stroke 130 mm, four-stroke cycle engine, rated power limited to 100 hp at 1800 rpm; weight 228 kg; propeller with direct drive and air cooling. Moving parts, engine block, and lubrication are all presented.
Date:
January 1931
Creator:
Léglise, Pierre
System:
The UNT Digital Library
Mathematical treatise on the recovery from a flat spin
In this mathematical investigation, made in collaboration with Dr. Wilhelm Schmidt, we interpret the temporary change (due to some disturbance) in the quantities which define the position of the airplane while in a flat spin. We further examine the effect of this change, of the means resorted to to produce the disturbance, and thus reveal the expedients available for recovering from a flat spin.
Date:
November 1930
Creator:
Fuchs, R.
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
System:
The UNT Digital Library
The Mutual Action of Airplane Body and Power Plant
The present report concerns the development of general propeller performance and r.p.m. curves which, combined with the general curve of the power required for level flight, presents a complete picture of the performance. The curve of power required for level flight in this paper is only an approximation for constant profile drag coefficient, meaning that it is not suitable to unconventional wing sections.
Date:
April 1932
Creator:
Schrenk, Martin
System:
The UNT Digital Library
Investigation of the Variations in the Velocity of the Air Flow About a Wing Profile
Memorandum presenting an investigation to determine the variations in the velocity of the air when it was obliged to flow about a wing profile. Special interest was paid to the determination of velocity as compared with that of the undisturbed flow and of the velocity drop in successive planes perpendicular to the flow direction at increasing distances from the wing profile.
Date:
July 1930
Creator:
Repenthin, Walter
System:
The UNT Digital Library
Experiments With Airplane Brakes
This report begins by examining the forces on the brake shoes. For the determination of the load distribution over the shoes it was assumed that the brake linings follow Hooke's law, are neatly fitted and bedded in by wear. The assumption of Hooke's law, that is, the proportionality between compression of the lining and the absorption of force, is fulfilled to a certain extent for the loading, as becomes apparent from the load tests described further on. But there is a material discrepancy at unloading.
Date:
September 1931
Creator:
Michael, Franz
System:
The UNT Digital Library
Elmira Soaring Contest, 1930
This report details the Elmira, New York soaring contest of 1930 and provides up-current maps, experiences in piloting, distance flights, and a few details on glider design.
Date:
March 1931
Creator:
Hirth, Wolfram K. E.; Schempp, Martin H. & Herrick, Jack
System:
The UNT Digital Library
Combating Airplane Fires
This report provides a summary of the important steps to be taken in combating airplane fires. Some considerations and ways of preventing fires from developing are provided.
Date:
January 1930
Creator:
Brunat, Henri
System:
The UNT Digital Library
Effect of Viscosity in Speed Measurements With Double-Throat Venturi Tubes
In order to clarify the viscosity effect some experiments were made in the Gottigen low-pressure tunnel with the Bruhn double-throat Venturi tube. This type of tunnel makes it possible to vary the pressure and thereby the density within wide limits and consequently, to examine the viscosity effect. This, however, did not impair the results because pressure and temperature were determined at different periods.
Date:
August 1931
Creator:
Peters, H.
System:
The UNT Digital Library
Aerodynamic Investigation of a Cup Anemometer
Results of an investigation wherein the change of the normal force coefficient with Reynolds Number was obtained statically for a 15.5-centimeter hemispherical cup.
Date:
July 1934
Creator:
Hubbard, John D. & Brescoll, George P.
System:
The UNT Digital Library
Bending Tests of Metal Monocoque Fuselage Construction
Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Date:
November 1930
Creator:
Mossman, Ralph W. & Robinson, Russell G.
System:
The UNT Digital Library
Spartan "Cruiser" Commercial Airplane (British): A Six-Seat Low-Wing Cantilever Monoplane
Circular describing the Spartan "Cruiser", which is a six-seat low-wing cantilever commercial monoplane with three engines. Details of the construction, fuselage, wing, tail unit, power plant, fuel system, lubrication system, landing gear, controls, cabin arrangement, characteristics, performance, drawings, and photographs are provided.
Date:
August 1932
Creator:
unknown
System:
The UNT Digital Library
The Short "Scion Senior" Commercial Airplane (British): A Four-Engine High-Wing Cantilever Monoplane
Circular presenting a description of the Scion Senior, which is a high-wing cantilever monoplane of metal construction with four Pobjoy Niagara engines.
Date:
February 1936
Creator:
unknown
System:
The UNT Digital Library
The Caproni "90 P.B." Military Airplane (Italian): A Giant Biplane of 6000 Horsepower
Circular presenting a description of the Caproni 90 P.B., which is the largest airplane in existence at the time of the report. Details of the weight, construction, wings, controls, fuselage, tail, landing gear, flying qualities, and photographs are provided.
Date:
July 1930
Creator:
unknown
System:
The UNT Digital Library