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Airplane Performance as Influenced by the Use of a Supercharged Engine
"The question of the influence of a supercharged engine on airplane performance is treated here in a first approximation, but one that gives an exact idea of the advantage of supercharging. Considered here is an airplane that climbs first with an ordinary engine, not supercharged, and afterwards climbs with a supercharged engine. The aim is to find the difference of the ceilings reached in the two cases" (p. 1).
Date:
May 1920
Creator:
de Bothezat, George
System:
The UNT Digital Library
Notes on the Theory of the Accelerometer
Report discusses several types of accelerometers and how they function. Methods for reducing error and determining the source of the error, including the best placement for the device, are included.
Date:
May 1920
Creator:
Warner, E. P.
System:
The UNT Digital Library
The Problem of the Helicopter
Report discussing some of the issues regarding the design and operation of helicopters and the theoretical basis behind them. Some particular issues covered include propeller blade design, helicopters in forced descent, horizontal travel, and stability and control.
Date:
May 1920
Creator:
Warner, E. P.
System:
The UNT Digital Library
Relation of Rib Spacing to Stress in Wing Planes
The stress relations to the fabric and the rib consequent upon a change of spacing between ribs in a wing plane are discussed. Considering the wing plane as a static structure, and ignoring the question of aerodynamic efficiency, it appears that the unit stress in the rib and fabric will remain constant for constant p if the linear dimensions of both rib and fabric are increased alike, viz., if wing and fabric remain geometrically similar. Since the bulge and the structural dimensions remain geometrically similar, the whole distended plane remains so, and hence should have the same pressure distribution and efficiency.
Date:
May 1920
Creator:
Zahm, A. F.
System:
The UNT Digital Library
Airplane Superchargers
Discussed here are the principles and operation of aircraft engine superchargers used to maintain and increase engine power as aircraft encounter decreases in the density of air as altitude rises. Details are given on the design and operation of the centrifugal compressors. A method is given for calculating the amount of power needed to drive a compressor. The effects of the use of a compressor on fuel system operation and design are discussed. Several specific superchargers that were in operation are described.
Date:
May 1921
Creator:
Noack, W. G.
System:
The UNT Digital Library
On a New Type of Wind Tunnel
Discussed here is a new type of wind tunnel, its advantages, the difficulties attendant upon its use, and the special methods required for its operation. The main difference between the new type of wind tunnel and the ones now in operation is the use of a different fluid. The idea is to diminish the effect of viscosity.
Date:
May 1921
Creator:
Munk, Max
System:
The UNT Digital Library
N.A.C.A. control position recorder
Report discussing a new instrument is described which is capable of simultaneously recording the position of the three controls of an airplane. The records are taken photographically on a standard N.A.C.A. film drum and the instrument can be quickly installed in any airplane.
Date:
May 1922
Creator:
Norton, F. H.
System:
The UNT Digital Library
Notes on Propeller Design 4: General Proceeding in Design
The choice of the numbers of revolutions and of the diameter, the distribution of thrust, and the values of the constants in the aerodynamical equations of the propeller are discussed.
Date:
May 1922
Creator:
Munk, Max M.
System:
The UNT Digital Library
Notes on Propeller Design III: The Aerodynamical Equations of the Propeller Blade Elements
The air flow and the air force created by all elements of the propeller blades lying in a ring located between two concentric circles around the propeller axis are independent of what happens in other rings.
Date:
May 1922
Creator:
Munk, Max M.
System:
The UNT Digital Library
Notes on the Design of Latticed Columns Subject to Lateral Loads
"No rational column formula has yet been developed which gives results which are sufficiently precise for the design of airplane members, and consequently it is necessary to fall back upon experimental testing. In order to derive the maximum benefit from experiments, however, it is necessary that the experiments be guided by theory. It is the object here to modify existing formulae that may be obtained with a minimum number of tests" (p. 1).
Date:
May 1922
Creator:
McCarthy, Charles J.
System:
The UNT Digital Library
Sylphon diaphragms : a method for predicting their performance for purposes of instrument design
Here, the purpose is to show that the characteristic performance of a syphon diaphragm can be predicted from a knowledge of its stiffness and of its dimensions. The proof is based on a mathematical analysis of this type of diaphragm, together with enough experimental data to prove the validity of the assumptions and the sufficiency of the analysis. Equations are developed for the performance of syphons under various conditions of loading, both for concentrated loads and for hydrostatic pressure.
Date:
May 1922
Creator:
Eaton, H. N. & Keulegan, G. H.
System:
The UNT Digital Library
Adaptation of aeronautical engines to high altitude flying
Report discussing Issues and techniques relative to the adaptation of aircraft engines to high altitude flight. Covered here are the limits of engine output, modifications and characteristics of high altitude engines, the influence of air density on the proportions of fuel mixtures, methods of varying the proportions of fuel mixtures, the automatic prevention of fuel waste, and the design and application of air pressure regulators to high altitude flying. Summary: 1. Limits of engine output. 2. High altitude engines. 3. Influence of air density on proportions of mixture. 4. Methods of varying proportions of mixture. 5. Automatic prevention of fuel waste. 6. Design and application of air pressure regulators to high altitude flying.
Date:
May 1923
Creator:
Kutzbach, K.
System:
The UNT Digital Library
Experiments With a Built-In or Fuselage Radiator
"The experiments discussed here were performed to determine whether radiators having similar cooling properties offer less resistance when incorporated into the fuselage, than when the hitherto customary arrangement is employed, with the radiator in the free air current more or less independent of the fuselage. The experiments indicated that the quantity of air flowing through the radiator is greatest when the fuselage and the radiator are separate. However, separate radiators cause more air resistance" (p. 1).
Date:
May 1923
Creator:
Wieselsberger, C.
System:
The UNT Digital Library
Influence of Ribs on Strength of Spars
Note presenting an investigation to determine what effect joints connected with brackets, nails, and glue has on the strength of aircraft wing spars. Equations used to determine the results of loading tests are provided.
Date:
May 1923
Creator:
Ballenstedt, L.
System:
The UNT Digital Library
The Effect of Wind Tunnel Turbulence Upon the Forces Measured on Models
These tests were undertaken to find the effect of turbulence in the air stream upon the lift and drag forces measured on models in the four-foot wind tunnel at the Massachusetts Institute of Technology. Maximum lifts and minimum drags were measured on Gottingen-387 and R.A.F.-15 airfoils, minimum drag on a streamlined strut, and the static pressure gradients for different conditions of turbulence were investigated. The results show that the scale of the turbulence (as defined in this report) has a marked effect upon the measured forces on models tested in the tunnel as well as on the pressure gradient, and it is recommended that further investigation of the phenomena be made with the aid of smoke and small wind vanes.
Date:
May 1924
Creator:
LePage, W. L. & Nichols, J. T.
System:
The UNT Digital Library
High Altitude Flying
This note investigates the effect of high altitude or low atmospheric pressure upon the operation of an engine and the effect of the low pressure and lack of oxygen and of the very low temperatures upon the pilot and upon the performance of the airplane itself.
Date:
May 1924
Creator:
King, Paul B. & Carroll, Thomas
System:
The UNT Digital Library
A method of determining the dimensions and horsepower of an airship for any given performance
A simple and easily applied method of calculating the dimensions and horsepower necessary for an airship to have any given performance is described and illustrated by examples. The method includes means for estimating the changes in performance or in size when modifications or new features are introduced into a design, involving increase or saving in weights, or changes in resistance or propulsive efficiency.
Date:
May 1924
Creator:
Burgess, C. P.
System:
The UNT Digital Library
Note on the Pressure Distribution Over the Hull of Elongated Airships With Circular Cross Section
"This note, prepared for the National Advisory Committee for Aeronautics, contains the demonstration that the pressure around the circular cross section of an elongated airship, plotted against the diameter of symmetry, can be expected to be represented by a straight line" (p. 1).
Date:
May 1924
Creator:
Munk, Max M.
System:
The UNT Digital Library
The comparison of well-known and new wing sections tested in the variable density wind tunnel
Three groups of airfoils have been tested in the variable density wind tunnel. The first group contains three airfoils. The second group is a systematic series of twenty-seven airfoils. The third group consists of several frequently used wing sections.
Date:
May 1925
Creator:
Higgins, George J.
System:
The UNT Digital Library
The Estimation of Airplane Performance From Wind Tunnel Tests on Conventional Airplane Models
Calculations of the magnitude of the correction factors and the range of their variations for wind tunnel models used in making aircraft performance predictions were made for 23 wind tunnel models. Calculated performances were compared with those actually determined for such airplanes as have been built and put through flight test. Except as otherwise noted, all the models have interplane struts and diagonal struts formed to streamwise shape. Wires were omitted in all cases. All the models were about 18 inches in span and were tested in a 4-foot wind tunnel. Results are given in tabular form.
Date:
May 1925
Creator:
Warner, Edward P. & Ober, Shatswell
System:
The UNT Digital Library
Propeller Design - A Simple System Based on Model Propeller Test Data -III
"This report, the third of a series of four, describes a simple system for designing propellers of a standard form. In this report, the system is based on tests of a family of model propellers of standard Navy form, the data from which have been extended by means of calculations to cover the complete range likely to be found in practice. However, it can be worked out for any family having propellers of one general form" (p. 1).
Date:
May 1926
Creator:
Wieck, Fred E.
System:
The UNT Digital Library
Propeller Design: Extension of Test Data on a Family of Model Propellers by Means of the Modified Blade Element Theory 2
This report is the second of a series of four on propeller design, and describes the method used to extend the data obtained from tests on a family of thirteen model propellers to include all propellers of the same form likely to be met in practice. This necessitates the development of a method of propeller analysis which when used to calculate the powers and efficiencies gives results which check the tests throughout their range.
Date:
May 1926
Creator:
Weick, Fred E.
System:
The UNT Digital Library
Propeller Design: Practical Application of the Blade Element Theory 1
"This report is the first of a series of four on propeller design and contains a description of the blade elements or modified Drzewiecke theory as used in the Bureau of Aeronautics, U.S. Navy Department. Blade interference corrections are used which were taken from R.& M. NO. 639 of the British Advisory Committee for Aeronautics. The airfoil characteristics used were obtained from tests of model propellers, not from tests of model wings" (p. 1).
Date:
May 1926
Creator:
Weick, Fred E.
System:
The UNT Digital Library
A Dangerous Seaplane Landing Condition
"A peculiar phenomena in seaplane landing is observed and reported. The seaplane having executed a normal fast landing at low incidence, a forward movement of the control stick effected an unusual condition in that the seaplane left the water suddenly in an abnormal attitude. The observations describing this phenomena are offered as a warning against possible accident and as a conjectural cause of seaplane landing accidents of a certain kind" (p. 1).
Date:
May 1928
Creator:
Carroll, Thomas
System:
The UNT Digital Library