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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1927
 Collection: National Advisory Committee for Aeronautics Collection
Aero dopes and varnishes

Aero dopes and varnishes

Date: July 1, 1927
Creator: Britton, H T S
Description: Before proceeding to discuss the preparation of dope solutions, it will be necessary to consider some of the essential properties which should be possessed of a dope film, deposited in and on the surface of an aero fabric. The first is that it should tighten the material and second it should withstand weathering.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic characteristics of airfoils IV : continuation of reports nos. 93, 124, and 182

Aerodynamic characteristics of airfoils IV : continuation of reports nos. 93, 124, and 182

Date: January 1, 1927
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 the 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
The aerodynamic characteristics of seven frequently used wing sections at full Reynolds number

The aerodynamic characteristics of seven frequently used wing sections at full Reynolds number

Date: January 1, 1927
Creator: Munk, Max M
Description: This report contains the aerodynamic properties of the wing sections U.S.A. 5, U.S.A. 27, U.S.A. 35 A, U.S.A. 35 B, Clark Y, R.A.F. 15, and Gottingen 387, as determined at various Reynolds numbers up to an approximately full scale value in the variable density wind tunnel of the National Advisory Committee for Aeronautics. It is shown that the characteristics of the wings investigated are affected greatly and in a somewhat erratic manner by variation of the Reynolds number. In general there is a small increase in maximum lift and an appreciable decrease in drag at all lifts.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic laboratory at Cuatro Vientos

Aerodynamic laboratory at Cuatro Vientos

Date: June 1, 1927
Creator: Caracciolo, Moreno
Description: This report presents a description of the design of the Cuatro Vientes wind tunnel.
Contributing Partner: UNT Libraries Government Documents Department
Air cooling : an experimental method of evaluating the cooling effect of air streams on air-cooled cylinders

Air cooling : an experimental method of evaluating the cooling effect of air streams on air-cooled cylinders

Date: May 1, 1927
Creator: Alcock, J F
Description: In this report is described an experimental method which the writer has evolved for dealing with air-cooled engines, and some of the data obtained by its means. Methods of temperature measurement and cooling are provided.
Contributing Partner: UNT Libraries Government Documents Department
The air forces on a systematic series of biplane and triplane cellule models

The air forces on a systematic series of biplane and triplane cellule models

Date: January 1, 1927
Creator: Munk, Max M
Description: The air forces on a systematic series of biplane and triplane cellule models are the subject of this report. The test consist in the determination of the lift, drag, and moment of each individual airfoil in each cellule, mostly with the same wing section. The magnitude of the gap and of the stagger is systematically varied; not, however, the decalage, which is zero throughout the tests. Certain check tests with a second wing section make the tests more complete and conclusions more convincing. The results give evidence that the present army and navy specifications for the relative lifts of biplanes are good. They furnish material for improving such specifications for the relative lifts of triplanes. A larger number of factors can now be prescribed to take care of different cases.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil lift with changing angle of attack

Airfoil lift with changing angle of attack

Date: September 1, 1927
Creator: Reid, Elliott G
Description: Tests have been made in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics to determine the effects of pitching oscillations upon the lift of an airfoil. It has been found that the lift of an airfoil, while pitching, is usually less than that which would exist at the same angle of attack in the stationary condition, although exceptions may occur when the lift is small or if the angle of attack is being rapidly reduced. It is also shown that the behavior of a pitching airfoil may be qualitatively explained on the basis of accepted aerodynamic theory.
Contributing Partner: UNT Libraries Government Documents Department
Annual report for the National Advisory Committee for Aeronautics (12th).administrative report including Technical Reports nos. 233 to 256

Annual report for the National Advisory Committee for Aeronautics (12th).administrative report including Technical Reports nos. 233 to 256

Date: January 1, 1927
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
Approximation method for determining the static stability of a monoplane glider

Approximation method for determining the static stability of a monoplane glider

Date: November 1, 1927
Creator: Lippisch, A
Description: The calculations in this paper afford an approximate solution of the static stability. A derivation of the formulas for moment coefficient of a wing, moment coefficient of elevator, and the total moment of the combined wing and elevator and the moment coefficient with reference to the center of gravity are provided.
Contributing Partner: UNT Libraries Government Documents Department
Approximations for column effect in airplane wing spars

Approximations for column effect in airplane wing spars

Date: January 1, 1927
Creator: Warner, Edward P
Description: The significance attaching to "column effect" in airplane wing spars has been increasingly realized with the passage of time, but exact computations of the corrections to bending moment curves resulting from the existence of end loads are frequently omitted because of the additional labor involved in an analysis by rigorously correct methods. The present report represents an attempt to provide for approximate column effect corrections that can be graphically or otherwise expressed so as to be applied with a minimum of labor. Curves are plotted giving approximate values of the correction factors for single and two bay trusses of varying proportions and with various relationships between axial and lateral loads. It is further shown from an analysis of those curves that rough but useful approximations can be obtained from Perry's formula for corrected bending moment, with the assumed distance between points of inflection arbitrarily modified in accordance with rules given in the report. The discussion of general rules of variation of bending stress with axial load is accompanied by a study of the best distribution of the points of support along a spar for various conditions of loading.
Contributing Partner: UNT Libraries Government Documents Department
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