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 Collection: National Advisory Committee for Aeronautics Collection
Avia pursuit airplane B.H. 21

Avia pursuit airplane B.H. 21

Date: November 1, 1926
Creator: Serryer, J
Description: Built by the 'Czecho-Slovakian' aircraft factory, AVIA, the B.H. 21, has a top speed of 250 MPH, and carries 120 kg of gasoline and 20 kg of oil, giving it a radius of action of 600-650 km. It is equipped with a Hispano-Suiza engine capable of 300 HP.
Contributing Partner: UNT Libraries Government Documents Department
Lockheed "Vega" airplane : a commercial cabin monoplane

Lockheed "Vega" airplane : a commercial cabin monoplane

Date: November 1, 1927
Creator: unknown
Description: The Vega is a high wing monoplane suitable for commercial purposes. It can seat 6 passengers or 100 cubic feet of cargo.
Contributing Partner: UNT Libraries Government Documents Department
The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

The Westland "Widgeon III" "Cirrus II: or "Genet II" engine

Date: August 1, 1927
Creator: unknown
Description: The Widgeon III is a parasol type monoplane. One of it's strongest features was the high degree of visibility available to the pilot.
Contributing Partner: UNT Libraries Government Documents Department
The Mureaux "Brunet 3C2" pursuit airplane

The Mureaux "Brunet 3C2" pursuit airplane

Date: May 1, 1927
Creator: Serryer, J
Description: Designed by Engineer Brunet, the 3C2 is an all metal monoplane with two engines and provision for six machine guns and 12 10 Kg. bombs.
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
Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Effect of ice formations on section drag of swept NACA 63A-009 airfoil with partical-span leading-edge slat for various modes of thermal ice protection

Date: March 15, 1954
Creator: Von Glahn, Uwe H & Gray, Vernon H
Description: Studies were made to determine the effect of ice formations on the section drag of a 6.9-foot-chord 36 degree swept NACA 63A-009 airfoil with partial-span leading-edge slat. In general, the icing of a thin swept airfoil will result in greater aerodynamic penalties than for a thick unswept airfoil. Glaze-ice formations at the leading edge of the airfoil caused large increases in section drag even at liquid-water content of 0.39 gram per cubic meter. The use of an ice-free parting strip in the stagnation region caused a negligible change in drag compared with a completely unheated airfoil. Cyclic de-icing when properly applied caused the drag to decrease almost to the bare-airfoil drag value.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Investigation of turbines for driving supersonic compressors II : performance of first configuration with 2.2 percent reduction in nozzle flow area / Warner L. Stewart, Harold J. Schum, Robert Y. Wong

Date: July 22, 1952
Creator: Stewart, Warner L; Schum, Harold J & Wong, Robert Y
Description: The experimental performance of a modified turbine for driving a supersonic compressor is presented and compared with the performance of the original configuration to illustrate the effect of small changes in the ratio of nozzle-throat area to rotor-throat area. Performance is based on the performance of turbines designed to operate with both blade rows close to choking. On the basis of the results of this investigation, the ratio of areas is concluded to become especially critical in the design of turbines such as those designed to drive high-speed, high-specific weight-flow compressors where the turbine nozzles and rotor are both very close to choking.
Contributing Partner: UNT Libraries Government Documents Department
The physical effects of detonation in a closed cylindrical chamber

The physical effects of detonation in a closed cylindrical chamber

Date: January 1, 1935
Creator: Draper, C S
Description: Detonation in the internal-combustion engine is studied as a physical process. It is shown that detonation is accompanied by pressure waves within the cylinder charge. Sound theory is applied to the calculation of resonant pressure-wave frequencies. Apparatus is described for direct measurement of pressure-wave frequencies. Frequencies determined from two engines of different cylinder sizes are shown to agree with the values calculated from sound theory. An outline of the theoretically possible modes of vibration in a right circular cylinder with flat ends is included. An appendix by John P. Elting gives a method of calculating pressure in the sound wave following detonation.
Contributing Partner: UNT Libraries Government Documents Department
General airplane performance

General airplane performance

Date: January 1, 1939
Creator: Rockfeller, W C
Description: Equations have been developed for the analysis of the performance of the ideal airplane, leading to an approximate physical interpretation of the performance problem. The basic sea-level airplane parameters have been generalized to altitude parameters and a new parameter has been introduced and physically interpreted. The performance analysis for actual airplanes has been obtained in terms of the equivalent ideal airplane in order that the charts developed for use in practical calculations will for the most part apply to any type of engine-propeller combination and system of control, the only additional material required consisting of the actual engine and propeller curves for propulsion unit. Finally, a more exact method for the calculation of the climb characteristics for the constant-speed controllable propeller is presented in the appendix.
Contributing Partner: UNT Libraries Government Documents Department
Elastic instability of members having sections common in aircraft construction

Elastic instability of members having sections common in aircraft construction

Date: January 1, 1932
Creator: Trayer, George W & March, H W
Description: Two fundamental problems of elastic stability are discussed in this report. In part one formulas are given for calculating the critical stress at which a thin, outstanding flange of a compression member will either wrinkle into several waves or form into a single half wave and twist the member about its longitudinal axis. A mathematical study of the problem, which together with experimental work has led to these formulas, is given in an appendix. Results of test substantiating the recommended formulas are also presented. In part two the lateral buckling of beams is discussed. The results of a number of mathematical studies of this phenomenon have been published prior to this writing, but very little experimentally determined information relating to the problem has been available heretofore. Experimental verification of the mathematical deductions is supplied.
Contributing Partner: UNT Libraries Government Documents Department
Air propellers in yaw

Air propellers in yaw

Date: January 1, 1937
Creator: Lesley, E P; Worley, George F & Moy, Stanley
Description: Report presents the results of tests conducted at Stanford University of a 3-foot model propeller at four pitch settings and at 0 degree, 10 degrees, 20 degrees, and 30 degrees yaw. In addition to the usual propeller coefficients, cross-wind and vertical forces and yawing, pitching, and rolling moments were determined about axes having their origin at the intersection of the blade axis and the axis of rotation. The tests showed that the maximum efficiency was reduced only slightly for angles of yaw up to 10 degrees but that at 30 degrees yaw the loss in efficiency was about 10 percent. In all cases the cross-wind force was found to be greater than the cross-wind component of the axial thrust. With a yawed propeller an appreciable thrust was found for v/nd for zero thrust at zero yaw. Yawing a propeller was found to induce a pitching moment that increased in magnitude with yaw.
Contributing Partner: UNT Libraries Government Documents Department
Application of practical hydrodynamics to airship design

Application of practical hydrodynamics to airship design

Date: January 1, 1933
Creator: Upson, Ralph H & Klikoff, W A
Description: The purpose of the first two parts of this report is to present in concise format all the formulas required for computation of the hydrodynamic forces, so that they can be easily computed for either straight or curvilinear flight. Improved approximations are also introduced having a high degree of accuracy throughout the entire range of practical proportions. The remaining two parts of the report are devoted respectively to stability and skin friction, as functions of the same hydrodynamic forces.
Contributing Partner: UNT Libraries Government Documents Department
A proof of the theorem regarding the distribution of lift over the span for minimum induced drag

A proof of the theorem regarding the distribution of lift over the span for minimum induced drag

Date: January 1, 1931
Creator: Durand, W F
Description: The proof of the theorem that the elliptical distribution of lift over the span is that which will give rise to the minimum induced drag has been given in a variety of ways, generally speaking too difficult to be readily followed by the graduate of the average good technical school of the present day. In the form of proof this report makes an effort to bring the matter more readily within the grasp of this class of readers.
Contributing Partner: UNT Libraries Government Documents Department
Aircraft woods: their properties, selection, and characteristics

Aircraft woods: their properties, selection, and characteristics

Date: January 1, 1931
Creator: Markwardt, L J
Description: Strength values of various woods for aircraft design for a 15 per cent moisture condition of material and a 3-second duration of stress are presented, and also a discussion of the various factors affecting the values. The toughness-test method of selecting wood is discussed, and a table of acceptance values for several species is given.
Contributing Partner: UNT Libraries Government Documents Department
A method of calculating the ultimate strength of continuous beams

A method of calculating the ultimate strength of continuous beams

Date: January 1, 1931
Creator: Newlin, J A & Trayer, George W
Description: The purpose of this study was to investigate the strength of continuous beams after the elastic limit has been passed. As a result, a method of calculation, which is applicable to maximum load conditions, has been developed. The method is simpler than the methods now in use and it applies properly to conditions where the present methods fail to apply.
Contributing Partner: UNT Libraries Government Documents Department
Stability of thin-walled tubes under torsion

Stability of thin-walled tubes under torsion

Date: January 1, 1935
Creator: Donnell, L H
Description: In this report a theoretical solution is developed for the torsion on a round thin-walled tube for which the walls become unstable. The results of this theory are given by a few simple formulas and curves which cover all cases. The differential equations of equilibrium are derived in a simpler form than previously found, it being shown that many items can be neglected.
Contributing Partner: UNT Libraries Government Documents Department
An extended theory of thin airfoils and its application to the biplane problem

An extended theory of thin airfoils and its application to the biplane problem

Date: January 1, 1931
Creator: Millikan, Clark B
Description: The report presents a new treatment, due essentially to von Karman, of the problem of the thin airfoil. The standard formulae for the angle of zero lift and zero moment are first developed and the analysis is then extended to give the effect of disturbing or interference velocities, corresponding to an arbitrary potential flow, which are superimposed on a normal rectilinear flow over the airfoil. An approximate method is presented for obtaining the velocities induced by a 2-dimensional airfoil at a point some distance away. In certain cases this method has considerable advantage over the simple "lifting line" procedure usually adopted. The interference effects for a 2-dimensional biplane are considered in the light of the previous analysis. The results of the earlier sections are then applied to the general problem of the interference effects for a 3-dimensional biplane, and formulae and charts are given which permit the characteristics of the individual wings of an arbitrary biplane without sweepback or dihedral to be calculated. In the final section the conclusions drawn from the application of the theory to a considerable number of special cases are discussed, and curves are given illustrating certain of these conclusions and serving as examples to indicate ...
Contributing Partner: UNT Libraries Government Documents Department
Macchi M. 39 Seaplane: Single-Seat Racer with an 800 HP. Fiat "A-S2" Engine

Macchi M. 39 Seaplane: Single-Seat Racer with an 800 HP. Fiat "A-S2" Engine

Date: March 1, 1927
Creator: unknown
Description: The M. 39 was designed by Castoldi to compete in the Schneider Cup Race of 1926 (Norfolk, VA). It is a monoplane with engine mounted in the fuselage, resting on two wing and hull mounted floats.
Contributing Partner: UNT Libraries Government Documents Department
Investigation of the Behavior of Thin-Walled Panels with Cutouts

Investigation of the Behavior of Thin-Walled Panels with Cutouts

Date: September 1, 1946
Creator: Podorozhny, A. A.
Description: The present paper deals with the computation and methods of reinforcement of stiffened panels with cutouts under bending loads such as are applied to the sides of a fuselage. A comparison is maade between the computed and test results. Results are presented of tests on panels with cutouts under tensile and compressive loads.
Contributing Partner: UNT Libraries Government Documents Department
Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Investigations of Compression Shocks and Boundary Layers in Gases Moving at High Speed

Date: January 1, 1947
Creator: Ackeret, J.; Feldmann, F. & Rott, N.
Description: The mutual influences of compression shocks and friction boundary layers were investigated by means of high speed wind tunnels.Schlieren optics provided a clear picture of the flow phenomena and were used for determining the location of the compression shocks, measurement of shock angles, and also for Mach angles. Pressure measurement and humidity measurements were also taken into consideration.Results along with a mathematical model are described.
Contributing Partner: UNT Libraries Government Documents Department
On the Instability of Methods for the Integration of Ordinary Differential Equations

On the Instability of Methods for the Integration of Ordinary Differential Equations

Date: April 1, 1956
Creator: Rutishauser, Heinz
Description: Examples and a criterion for stability of integration methods is provided. The criterion is applied to well-known integration formulas.
Contributing Partner: UNT Libraries Government Documents Department
The Calculation of Compressible Flows with Local Regions of Supersonic Velocity

The Calculation of Compressible Flows with Local Regions of Supersonic Velocity

Date: March 1, 1947
Creator: Goethert, B. & Kawalki, K. H.
Description: This report addresses a method for the approximate calculation of compressible flows about profiles with local regions of supersonic velocity. The flow around a slender profile is treated as an example.
Contributing Partner: UNT Libraries Government Documents Department
Free Convection Under the Conditions of the Internal Problem

Free Convection Under the Conditions of the Internal Problem

Date: April 1, 1958
Creator: Ostroumov, G. A.
Description: Convection is called free is the stresses (including the normal pressure) to which the fluid is subjected at its boundaries do not perform mechanical work, that is, if all the boundaries of the fluid are stationary. The case where this is not true is termed forced convection. It corresponds to the action on the fluid of some mechanical suction pumping the fluid.
Contributing Partner: UNT Libraries Government Documents Department
Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers

Drag Reduction by Suction of the Boundary Layer Separated Behind Shock Wave Formation at High Mach Numbers

Date: July 1, 1947
Creator: Regenscheit, B.
Description: With an approach of the velocity of flight of a ship to the velocity of sound, there occurs a considerable increase of the drag. The reason for this must be found in the boundary layer separation caused by formation of shock waves. It will be endeavored to reduce the drag increase by suction of the boundary layer. Experimental results showed that drag increase may be considerably reduced by this method. It was, also, observed that, by suction, the position of shock waves can be altered to a considerable extent.
Contributing Partner: UNT Libraries Government Documents Department