You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1930-1939
 Year: 1930
 Collection: National Advisory Committee for Aeronautics Collection
The 1929 Rhon soaring-flight contest

The 1929 Rhon soaring-flight contest

Date: April 1930
Creator: Lippisch, Alexander
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
An accurate method of measuring the moments of inertia of airplanes

An accurate method of measuring the moments of inertia of airplanes

Date: October 1930
Creator: Miller, M P
Description: 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.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of airfoils VI : continuation of reports nos. 93, 124, 182, 244, and 286

Aerodynamic characteristics of airfoils VI : continuation of reports nos. 93, 124, 182, 244, and 286

Date: January 1, 1930
Creator: unknown
Description: This collection of data on airfoils has been made from the published reports of a number of the leading aerodynamic laboratories of this country and Europe. The information which was originally expressed according to the different customs of the several laboratories is here presented in a uniform series of charts and tables suitable for use of designing engineers and for purposes of general reference. The authority for the results here presented is given as the name of the laboratory at which the experiments were conducted, with the size of the model, wind velocity, and year of test.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of twenty-four airfoils at high speeds

Aerodynamic characteristics of twenty-four airfoils at high speeds

Date: January 1, 1930
Creator: Brigg, L. J. & Dryden, H. L.
Description: The aerodynamic characteristics of 24 airfoils are given for speeds of 0.5, 0.65, 0.8, 0.95, and 1.08 times the speed of sound, as measured in an open-jet air stream 2 inches in diameter, using models of 1-inch chord. The 24 airfoils belong to four general groups. The first is the standard R. A. F. family in general use by the Army and Navy for propeller design, the members of the family differing only in thickness. This family is represented by nine members ranging in thickness from 0.04 to 0.20 inch. The second group consists of five members of the Clark Y family, the members of the family again differing only in thickness. The third group, comprising six members, is a second R. A. F. Family in which the position of the maximum ordinate is varied. Combined with two members of the first R.A.F. family, this group represents a variation of maximum ordinate position from 30 to 60 percent of the chord in two camber ratios, 0.08 and 0.16. The fourth group consists of three geometrical forms, a flat plate, a wedge, and a segment of a right circular cylinder. In addition one section used in the reed metal propeller was ...
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic theory and test of strut forms. Part I

Aerodynamic theory and test of strut forms. Part I

Date: January 1, 1930
Creator: Smith, R H
Description: This report presents the first part of a two part study made under this title. In this part the symmetrical inviscid flow about an empirical strut of high service merit is found by both the Rankine and the Joukowsky methods. The results can be made to agree as closely as wished. Theoretical stream surfaces as well as surfaces of constant speed and pressure in the fluid about the strut are found. The surface pressure computed from the two theories agrees well with the measured pressure on the fore part of the model but not so well on the after part. From the theoretical flow speed the surface friction is computed by an empirical formula. The drag integrated from the friction and measured pressure closely equals the whole measured drag. As the pressure drag and the whole drag are accurately determined, the friction formula also appears trustworthy for such fair shapes. (author).
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic theory and tests of strut forms. Part II

Aerodynamic theory and tests of strut forms. Part II

Date: January 1, 1930
Creator: Smith, R H
Description: This report presents the second of two studies under the same title. In this part five theoretical struts are developed from distributed sources and sinks and constructed for pressure and resistance tests in a wind tunnel. The surface pressures for symmetrical inviscid flow are computed for each strut from theory and compared with those found by experiment. The theoretical and experimental pressures are found to agree quantitatively near the bow, only qualitatively over the suction range, the experimental suctions being uniformly a little low, and not at all near the stern. This study is the strut sequel to Fuhrmann's research on airship forms, the one being a study in two dimensions, the other in three. A comparison of results indicates that the agreement between theory and experiment is somewhat better for bodies of revolution than for cylinders when both are shaped for slight resistance. The consistent deficiency of the experimental suctions which is found in the case of struts was not found in the case of airships, for which the experimental suctions were sometimes above sometimes below their theoretical values.
Contributing Partner: UNT Libraries Government Documents Department
Air forces and air-force moments at large angles of attack and how they are affected by the shape of the wing

Air forces and air-force moments at large angles of attack and how they are affected by the shape of the wing

Date: July 1, 1930
Creator: Fuchs, Richard & Schmidt, Wilhelm
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Alterations and tests of the "Farnboro" engine indicator

Alterations and tests of the "Farnboro" engine indicator

Date: September 1, 1930
Creator: Collins, John H , Jr
Description: The 'Farnboro' electric indicator was tested as received from the manufacturers, and modifications made to the instrument to improve its operation. The original design of disk valve was altered so as to reduce the mass, travel, and seat area. Changes were made to the recording mechanism, which included a new method of locating the top center position on the record. The effect of friction on the motion of the pointer while taking motoring and power cards was eliminated by providing a means of putting pressure lines on the record. The modified indicator gives a complete record of the average cyclic variation in pressure per crank degree for any set of engine operating conditions which can be held constant for the period of time required to build up the composite card. The value of the record for accurate quantitative measurement is still questioned, although the maximum indicated pressure recorded on the motoring and power cards checks the readings of the balanced diaphragm type of maximum cylinder pressure indicator.
Contributing Partner: UNT Libraries Government Documents Department
Analytical determination of the load on a trailing edge flap

Analytical determination of the load on a trailing edge flap

Date: October 1, 1930
Creator: Pinkerton, Robert M
Description: This report presents a theoretical analysis of the lift on a trailing edge flap. An analytical expression has been derived which enables the computation of the flap load coefficient. The theoretical results seem to show a fair agreement with the meager experimental results which are available.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (15th).administrative report including Technical Reports nos. 309 to 336

Annual report of the National Advisory Committee for Aeronautics (15th).administrative report including Technical Reports nos. 309 to 336

Date: January 1, 1930
Creator: unknown
Description: Report includes the National Advisory Committee for Aeronautics letter of submittal to the President, Congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Contributing Partner: UNT Libraries Government Documents Department
The "Avro Trainer" airplane (British) : a training biplane

The "Avro Trainer" airplane (British) : a training biplane

Date: June 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Balanced and servo control surfaces

Balanced and servo control surfaces

Date: May 1, 1930
Creator: unknown
Description: Many reports on various control systems are available, but the results cannot be generally applied since the effect of particular changes of surface-form and mounting are subject to variations depending upon airfoil section and influences of airplane layout. This report presents a simple analysis of several control systems in more general use. Elevators, ailerons, and rudders are all discussed.
Contributing Partner: UNT Libraries Government Documents Department
A balanced diaphragm type of maximum cylinder pressure indicator

A balanced diaphragm type of maximum cylinder pressure indicator

Date: December 1, 1930
Creator: Spanogle, J A & Collins, John H , Jr
Description: A balanced diaphragm type of maximum cylinder pressure indicator was designed to give results consistent with engine operating conditions. The apparatus consists of a pressure element, a source of controlled high pressure and a neon lamp circuit. The pressure element, which is very compact, permits location of the diaphragm within 1/8 inch of the combustion chamber walls without water cooling. The neon lamp circuit used for indicating contact between the diaphragm and support facilitates the use of the apparatus with multicylinder engines.
Contributing Partner: UNT Libraries Government Documents Department
The Behm acoustic sounder for airplanes with reference to its accuracy

The Behm acoustic sounder for airplanes with reference to its accuracy

Date: October 1, 1930
Creator: Schreiber, Ernest
Description: Relative altimetry is of great importance for increasing the safety in aerial transportation, because it makes possible safe flying at night, by poor visibility, and when landing. Among the instruments of this type is the Behm sounder, which operates on an acoustic principle. Acoustic altimetry in general and the Behn sounder, in particular, are covered in this report.
Contributing Partner: UNT Libraries Government Documents Department
Bending Tests of Metal Monocoque Fuselage Construction

Bending Tests of Metal Monocoque Fuselage Construction

Date: November 1930
Creator: Mossman, Ralph W. & Robinson, Russell G.
Description: Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Contributing Partner: UNT Libraries Government Documents Department
The boundary layer as a means of controlling the flow of liquids and gases

The boundary layer as a means of controlling the flow of liquids and gases

Date: March 1, 1930
Creator: Schrenk, Oskar
Description: According to one of the main propositions of the boundary layer theory the scarcely noticeable boundary layer may, under certain conditions, have a decisive influence on the form of the external flow by causing it to separate from the wing surface. These phenomena are known to be caused by a kind of stagnation of the boundary layer at the point of separation. The present report deals with similar phenomena. It is important to note that usually the cause (external interference) directly affects only the layer close to the wall, while its indirect effect extends to a large portion of the external flow.
Contributing Partner: UNT Libraries Government Documents Department
The Breguet 270 General-Purpose Military Airplane (French) : A Two-Seat All-Steel Sesquiplane

The Breguet 270 General-Purpose Military Airplane (French) : A Two-Seat All-Steel Sesquiplane

Date: September 1, 1930
Creator: De Marolles, R J
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Calculation of Pressure Distribution on Airship Hulls

Calculation of Pressure Distribution on Airship Hulls

Date: July 1, 1930
Creator: Von Karman, Theodor
Description: These calculations were based on the shape of the ZR III, with the following simplifications: cars, fins, and rudders removed; all cross sections replaced by equivalent circular cross sections. Under these assumptions the pressure distribution was calculated for the following cases: symmetrical case, or flow parallel to the axis; unsymmetrical case, or flow at an angle to the axis. In both cases the simple potential flow first forms the basis for the determination of the pressure distribution.
Contributing Partner: UNT Libraries Government Documents Department
Calculation of tapered monoplane wings

Calculation of tapered monoplane wings

Date: August 1, 1930
Creator: Amstutz, E
Description: The tapered wing shape increases the lift in the middle of the wing and thus reduces the bending moment of the lifting forces in the plane of symmetry. Since this portion of the wing is the thickest, the stresses of the wing material are reduced and desirable space is provided for stowing the loads in the wing. This statically excellent form of construction, however, has aerodynamic disadvantages which must be carefully weighed, if failures are to be avoided. This treatise is devoted to the consideration of these problems.
Contributing Partner: UNT Libraries Government Documents Department
Calibration and lag of a Friez type cup anemometer

Calibration and lag of a Friez type cup anemometer

Date: June 1, 1930
Creator: Pinkerton, Robert M
Description: Tests on a Friez type cup anemometer have been made in the variable density wind tunnel of the Langley Memorial Aeronautical Laboratory to calibrate the instrument and to determine its suitability for velocity measurements of wind gusts. The instrument was calibrated against a Pitot-static tube placed directly above the anemometer at air densities corresponding to sea level, and to an altitude of approximately 6000 feet. Air-speed acceleration tests were made to determine the lag in the instrument reading. The calibration results indicate that there should be an altitude correction. It is concluded that the cup anemometer is too sluggish for velocity measurements of wind gusts.
Contributing Partner: UNT Libraries Government Documents Department
The Caproni "90 P.B." military airplane (Italian) : a giant biplane of 6000 horsepower

The Caproni "90 P.B." military airplane (Italian) : a giant biplane of 6000 horsepower

Date: July 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The Cierva "Autogiro" Mark III (British) : Armstrong-Siddeley "Genet Major" Engine

The Cierva "Autogiro" Mark III (British) : Armstrong-Siddeley "Genet Major" Engine

Date: June 1, 1930
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Coefficients of flow of standard nozzles

Coefficients of flow of standard nozzles

Date: January 1, 1930
Creator: Mueller, H & Peters, H
Description: We first undertook experiments with air, devoted principally to the investigation of the disturbances due to the differences in the nature of the flow to the nozzle. The difficulty of measuring the air, however, caused us to experiment with water. Due to the possibility of measuring the capacity of the container, this method was much more accurate than measuring with Pitot tobes.
Contributing Partner: UNT Libraries Government Documents Department
Collection of wind-tunnel data on commonly used wing sections

Collection of wind-tunnel data on commonly used wing sections

Date: January 1930
Creator: Louden, F. A.
Description: This report groups in a uniform manner the aerodynamic properties of commonly used wing sections as determined from tests in various wind tunnels. The data have been collected from reports of a number of laboratories. Where necessary, transformation has been made to the absolute system of coefficients and tunnel wall interference corrections have been applied. Tables and graphs present the data in the various forms useful to the engineer in the selection of a wing section.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST