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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1928
 Collection: Technical Report Archive and Image Library
The 1926 German seaplane contest

The 1926 German seaplane contest

Date: March 1928
Creator: Seewald, F; Blenk, H & Liebers, F
Description: The report discusses the problem of rating the various seaplane designs from the 1926 seaplane contest. The whole process of rating consists in measuring the climbing speed, flying weight and carrying capacity of a seaplane and then using these data as the basis of a construction problem.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of thin empirical profiles and their application to the tail surfaces and ailerons of airplanes

Aerodynamic characteristics of thin empirical profiles and their application to the tail surfaces and ailerons of airplanes

Date: December 1, 1928
Creator: Toussaint, A & Carafoli, E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air force and moment for N-20 wing with certain cut-outs

Air force and moment for N-20 wing with certain cut-outs

Date: January 1, 1928
Creator: Smith, R H
Description: The airplane designer often finds it necessary, in meeting the requirements of visibility, to remove area or to otherwise locally distort the plan or section of an airplane wing. This report, prepared for the Bureau of Aeronautics January 15, 1925, contains the experimental results of tests on six 5 by 30 inch N-20 wing models, cut out or distorted in different ways, which were conducted in the 8 by 8 foot wind tunnel of the Navy Aerodynamical Laboratory in Washington in 1924. The measured and derived results are given without correction for vl/v for wall effect and for standard air density, p=0.00237 slug per cubic foot.
Contributing Partner: UNT Libraries Government Documents Department
Air force tests of sperry messenger model with six sets of wings

Air force tests of sperry messenger model with six sets of wings

Date: January 1, 1928
Creator: Shoemaker, James M
Description: The purpose of this test was to compare six well-known airfoils, the R.A.F 15, U.S.A. 5, U.S.A. 27, U.S.A. 35-B, Clark Y, and Gottingen 387, fitted to the Sperry Messenger model, at full scale Reynolds number as obtained in the variable density wind tunnel of the National Advisory Committee for Aeronautics; and to determine the scale effect on the model equipped with all the details of the actual airplane. The results show a large decrease in minimum drag coefficient upon increasing the Reynolds number from about one-twentieth scale to full scale. Maximum lift coefficient was increased with increasing scale for all the airfoils except the Gottingen 387, for which it was slightly decreased. A comparison is made between the results of these tests and those obtained from tests made in this tunnel on airfoils alone. (author).
Contributing Partner: UNT Libraries Government Documents Department
Airplane strength calculations and static tests in Russia : an attempt at standardization

Airplane strength calculations and static tests in Russia : an attempt at standardization

Date: September 1, 1928
Creator: unknown
Description: We are here giving a summary of the rules established by the Theoretical Section of the Central Aerodynamic Institute of Moscow for the different calculation cases of an airplane. It appears the engineers of the Aerodynamic Institute considered only thick or medium profiles. For these profiles they have attempted to increase the safety when the center of pressure moves appreciably toward the trailing edge.
Contributing Partner: UNT Libraries Government Documents Department
Annual report of the National Advisory Committee for Aeronautics (13th).administrative report including Technical Reports nos. 257 to 282

Annual report of the National Advisory Committee for Aeronautics (13th).administrative report including Technical Reports nos. 257 to 282

Date: January 1, 1928
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 Armstrong Whitworth "Starling" (British) : (single seat fighter)

The Armstrong Whitworth "Starling" (British) : (single seat fighter)

Date: September 1, 1928
Creator: unknown
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An automatic speed control for wind tunnels

An automatic speed control for wind tunnels

Date: February 1, 1928
Creator: Zahm, A F
Description: Described here is an automatic control that has been used in several forms in wind tunnels at the Washington Navy Yard. The form now in use with the 8-foot tunnel at the Navy Yard is considered here. Details of the design and operation of the automatic control system are given. Leads from a Pitot tube are joined to an inverted cup manometer located above a rheostat. When the sliding weight of this instrument is set to a given notch, say for 40 m.p.h, the beam tip vibrates between two electric contacts that feed the little motor. Thus, when the wind is too strong or too weak, the motor automatically throws the rheostat slide forward and backward. If it failed to function well, the operator would notice the effect on his meniscus, and would operate the hand control by merely pressing the switch.
Contributing Partner: UNT Libraries Government Documents Department
Aviation fuels : with especial reference to "white spirit."

Aviation fuels : with especial reference to "white spirit."

Date: February 1, 1928
Creator: Dumanois, P
Description: Gasoline, the fuel now used, is an extremely volatile and inflammable liquid capable of forming explosive mixtures, the cause of many catastrophes in aviation. It is therefore of special interest to investigate the possibility of using fuels which, while being less volatile than gasoline, would nevertheless enable this engine to function satisfactorily.
Contributing Partner: UNT Libraries Government Documents Department
The Avro "Avian III" Airplane (British)

The Avro "Avian III" Airplane (British)

Date: April 1, 1928
Creator: unknown
Description: The Avro Avian has a lift capacity of 828 lbs (including pilot). It is equipped with the Mark II A.D.C. Cirrus engine.
Contributing Partner: UNT Libraries Government Documents Department
Bearing strength of wood under steel aircraft bolts and washers and other factors influencing fitting design

Bearing strength of wood under steel aircraft bolts and washers and other factors influencing fitting design

Date: October 1, 1928
Creator: Trayer, G W
Description: The purpose of this report is to correlate, bring up to date, and put under a single cover all the information thought to be essential to an understanding of the formulas.
Contributing Partner: UNT Libraries Government Documents Department
Bleriot combat monoplane 127 (French)

Bleriot combat monoplane 127 (French)

Date: November 1, 1928
Creator: unknown
Description: The 127 is a cantilever monoplane without external bracing. It is designed to accompany and protect bombardment and observation aircraft.
Contributing Partner: UNT Libraries Government Documents Department
Bleriot-Spad 91 Airplane (French) : pursuit single-seater, type "Jockey"

Bleriot-Spad 91 Airplane (French) : pursuit single-seater, type "Jockey"

Date: May 1, 1928
Creator: SOCIETE BLERIOT-AERONAUTIQUE
Description: This aircraft has announced a speed of 270 km per hour at 4000 m. It is of all metal construction.
Contributing Partner: UNT Libraries Government Documents Department
The Boulton and Paul "Sidestrand I" bomber airplane (British)

The Boulton and Paul "Sidestrand I" bomber airplane (British)

Date: April 1, 1928
Creator: unknown
Description: The Sidestrand I is a twin engine bomber that has gone into production for Royal Air Force Squadrons. It seats three, and can carry a load in excess of 3500 lbs.
Contributing Partner: UNT Libraries Government Documents Department
The C.A.M.S. 54 G.R. transatlantic seaplane (French)

The C.A.M.S. 54 G.R. transatlantic seaplane (French)

Date: September 1, 1928
Creator: Ide, John Jay
Description: Tested at the end of March, 1928, the C.A.M.S. 54 G.R. was built for the purpose of crossing the Atlantic from Europe by way of the azores. It has a biplane construction with wings mounted above the hull. It is powered by two new series 500 HP. geared Hispano Suiza V type engines.
Contributing Partner: UNT Libraries Government Documents Department
Calculation of Airplane Performances Without the Aid of Polar Diagrams

Calculation of Airplane Performances Without the Aid of Polar Diagrams

Date: March 1, 1928
Creator: Schrenk, Martin
Description: For good profiles the profile-drag coefficient is almost constant in the whole range which comes into consideration for practical flight. This is manifest in the consideration of the Gottingen airfoil tests and is confirmed by the investigations of the writer (measurements of the profile drag during flight by the Betz method), concerning which a detailed report will soon be published. The following deductions proceed from this fact. The formulas developed on the assumptions of a constant profile-drag coefficient afford an extensive insight into the influences exerted on flight performances by the structure of the airplane.
Contributing Partner: UNT Libraries Government Documents Department
The Caproni monoplanes "Ca 97" Italian

The Caproni monoplanes "Ca 97" Italian

Date: October 1, 1928
Creator: unknown
Description: The Ca 97 is constructed with wings half overhung, a large fuselage, all metal construction, and can be configured with 1 to 3 engines.
Contributing Partner: UNT Libraries Government Documents Department
The cells of giant airplanes

The cells of giant airplanes

Date: September 1, 1928
Creator: Weyl, A R
Description: This report presents a discussion of the Rohrbach type of giant airplane. The problems considered are structural drag, wing loading and divided power plants.
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of five propellers in flight

Characteristics of five propellers in flight

Date: January 1, 1928
Creator: Crowley, J W , Jr & Mixson, R E
Description: This investigation was made for the purpose of determining the characteristics of five full-scale propellers in flight. The equipment consisted of five propellers in conjunction with a VE-7 airplane and a Wright E-2 engine. The propellers were of the same diameter and aspect ratio. Four of them differed uniformly in thickness and pitch and the fifth propeller was identical with one of the other four with exception of a change of the airfoil section. The propeller efficiencies measured in flight are found to be consistently lower than those obtained in model tests. It is probable that this is mainly a result of the higher tip speeds used in the full-scale tests. The results show also that because of differences in propeller deflections it is difficult to obtain accurate comparisons of propeller characteristics. From this it is concluded that for accurate comparisons it is necessary to know the propeller pitch angles under actual operating conditions. (author).
Contributing Partner: UNT Libraries Government Documents Department
Characteristics of propeller sections tested in the variable density wind tunnel

Characteristics of propeller sections tested in the variable density wind tunnel

Date: January 1, 1928
Creator: Jacobs, Eastman N
Description: Tests were carried out in the variable density wind tunnel of the National Advisory Committee for Aeronautics on six airfoil sections used by the Bureau of Aeronautics as propeller sections. The sections were tested at pressures of 1 and 20 atmospheres corresponding to Reynolds numbers of about 170,000 and 3,500,000. The results obtained, besides providing data for the design of propellers, should be of special interest because of the opportunity afforded for the study of scale effect on a family of airfoil sections having different thickness ratios. (author).
Contributing Partner: UNT Libraries Government Documents Department
Choice of profile for the wings of an airplane. Part I

Choice of profile for the wings of an airplane. Part I

Date: June 1, 1928
Creator: Toussaint, A & Carafoli, E
Description: The choice of the profile for the wings of an airplane is a problem which should be solved by a scientific method based on data obtained by systematic experimentation. The problem, in its present form, may be stated as follows: "To find a profile which has certain required aerodynamic characteristics and which encloses the spars, whose number, dimensions and separating distance are likewise determined by structural considerations." At present, the static test, corresponding to the case of accelerated flight at limited speed, requires the knowledge of the moment of the aerodynamic resultant at the angle of zero lift, and the possibility of controlling the magnitude of the corresponding absolute coefficient within more or less extensive limits.
Contributing Partner: UNT Libraries Government Documents Department
Choice of profile for the wings of an airplane. Part II

Choice of profile for the wings of an airplane. Part II

Date: June 1, 1928
Creator: Carafoli, E & Toussaint, A
Description: This report gives a general method for drawing airplane profiles. This method is useful, but it leads to a somewhat laborious drawing which becomes quite complicated when we take a transformation function having terms of a high degree.
Contributing Partner: UNT Libraries Government Documents Department
Coal-Mine Fatalities in the United States, 1927

Coal-Mine Fatalities in the United States, 1927

Date: 1928
Creator: Adams, William W.
Description: Report compiled by the U.S. Bureau of Mines including statistics on fatalities in coal mines located in the United States as well as data regarding the various operations (e.g., number of miners employed and average production). The information is organized into tables for comparison and the text draws some overall conclusions in the summary.
Contributing Partner: UNT Libraries Government Documents Department
Combustion time in the engine cylinder and its effect on engine performance

Combustion time in the engine cylinder and its effect on engine performance

Date: January 1, 1928
Creator: Marvin, Charles F , Jr
Description: As part of a general program to study combustion in the engine cylinder and to correlate the phenomena of combustion with the observed performance of actual engines, this paper presents a sketchy outline of what may happen in the engine cylinder during the burning of a charge. It also suggests the type of information needed to supply the details of the picture and points out how combustion time and rate affect the performance of the engine. A theoretical concept of a flame front which is assumed to advance radially from the point of ignition is presented, and calculations based on the area and velocity of this flame and the density of the unburned gases are made to determine the mass rate of combustion. From this rate the mass which has been burned and the pressure at any instant during combustion are computed. This process is then reversed in an effort to determine actual rates of combustion and flame velocities from the pressures as recorded on indicator diagrams. The effects of different rates of combustion on engine performance are then discussed and the importance of proper spark advance is emphasized.
Contributing Partner: UNT Libraries Government Documents Department
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