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in creator/contributor: "Langley Aeronautical Laboratory"  
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Model Supports and Their Effects on the Results of Wind Tunnel Tests

Description: "The airflow about a model while being tested is often sufficiently affected by the model support to lead to erroneous conclusions unless appropriate corrections are used. In this paper some new material on the subject is presented, together with a review of the airfoil support corrections used in several other laboratories" (p. 1).
Date: February 1923
Creator: Bacon, David L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The N.A.C.A. Recording Tachometer and Angle of Attack Recorder

Description: This note contains photos and descriptions of airplane flight apparatus for use in conjunction with a recording galvanometer. In measuring the angle of attack a variable resistance is used, being controlled by a vane in the airstream. Thus it is only necessary to measure the change of resistance.
Date: August 1923
Creator: Reid, H. J. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An impulse electric motor for driving recording instruments

Description: The chief purpose in undertaking the development of this synchronous motor was the creation of a very small, compact power source, capable of driving the film drums of the recording aircraft instruments designed by the staff of the National Advisory Committee for Aeronautics.
Date: September 1923
Creator: Joachim, W. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Time Lag and Interval of Discharge With a Spring Actuated Fuel Injection Pump

Description: Discussed here is research on a spring activated fuel pump for solid or airless injection with small, high speed internal combustion engines. The pump characteristics under investigation were the interval of fuel injection in terms of degrees of crank travel and in absolute time, the lag between the time the injection pump plunger begins its stroke and the appearance of the jet at the orifice, and the manner in which the fuel spray builds up to a maximum when the fuel valve is opened, and then … more
Date: September 1923
Creator: Matthews, Robertson & Gardiner, A. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Notes on the N.A.C.A. Control Force Recorder

Description: Emphasized here is the desirability of using recording instruments in the investigation of the characteristics of airplanes with particular reference to the National Advisory Committee for Aeronautics (NACA) control force recorder. Given here are photographs, records, and a description of the instrument developed by NACA for investigations on different types of aircraft. Described here is an instrument for recording control forces.
Date: July 1923
Creator: Reid, H. J. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Influences in the Selection of a Cycle for Small High Speed Engines Running on Solid or Airless Injection With Compression Ignition

Description: Note presenting an investigation undertaken to answer the question of what cycle of heat phases should be selected for small high speed engines running on solid or airless injection with compression ignition, and what the relative proportions of the heat phases should be.
Date: July 1923
Creator: Matthews, Robertson
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Pressure Distribution Over the Horizontal Tail Surfaces of an Airplane 3

Description: This report contains the results of an investigation of the distribution of pressure over the tail surfaces of a full-sized airplane during accelerated flight for the purpose of determining the magnitude of the tail and fuselage stresses in maneuvering. As the pressures in accelerated flight change in value with great rapidity, it was found that the liquid manometer used in the first part of this investigation would not be at all suitable under these conditions; so it was necessary to design an… more
Date: 1923
Creator: Norton, F. H. & Brown, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distribution Over the Rudder and Fin of an Airplane in Flight

Description: "This investigation was carried out by the National Advisory Committee for Aeronautics at the Langley Memorial Aeronautical Laboratory for the purpose of determining the loads which occur on the vertical tail surfaces in flight. The method consisted in measuring the pressures simultaneously at 28 points on the rudder and fin by means of a recording multiple manometer. The results show that the maximum load encountered in stunting was 7 pounds per square foot on the rudder and fin, and it is pro… more
Date: 1923
Creator: Norton, F. H. & Brown, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution over thick airfoils - model tests

Description: From Summary: "This investigation was undertaken to study the distribution of loading over thick wings of various types. The unloading on the wing was determined by taking the pressure at a number of holes on both the upper and lower surfaces of a model wing in the wind tunnel. The results from these tests show, first, that the distribution of pressure over a thick wing of uniform section is very little different from that over a thin wing; second, that wings tapering either in chord or thickne… more
Date: 1923
Creator: Norton, F. H. & Bacon, D. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Aerodynamic Properties of Thick Airfoils 2

Description: "This investigation is an extension of NACA report no. 75 for the purpose of studying the effect of various modifications in a given wing section, including changes in thickness, height of lower camber, taper in thickness, and taper in plan form with special reference to the development of thick, efficient airfoils. The method consisted in testing the wings in the NACA 5-foot wind tunnel at speeds up to 50 meters (164 feet) per second while they were being supported on a new type of wire balanc… more
Date: 1923%
Creator: Norton, F. H. & Bacon, D. L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Pressure Distribution Over the Horizontal Tail Surfaces of an Airplane

Description: "This work was undertaken to determine as completely as possible the distribution of pressure over the horizontal tail surfaces of an airplane, and to analyze the relation of this pressure to the structural loads and the longitudinal stability. The investigation is divided into three parts, of which this the first. The first part of the investigation is for the purpose of determining the pressure distribution over two horizontal tail surfaces in uniform free flight; the second part to conduct t… more
Date: 1923
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Practical Stability and Controllability of Airplanes

Description: "The effect of the characteristics of an airplane on balance, stability, and controllability, based on free flight tests, is discussed particularly in respect to the longitudinal motion. It is shown that the amount of longitudinal stability can be varied by changing the position of the center of gravity or by varying the aspect ratio of the tail plane, and that the stability for any particular air speed can be varied by changing the camber of the tail plane. It is found that complete longitudin… more
Date: 1923
Creator: Norton, F. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A study of taking off and landing an airplane

Description: "This report covers the results of an investigation carried on at the Langley Memorial Aeronautical Laboratory of the National Advisory Committee for Aeronautics for the purpose of discussing the various methods of effecting the take-off and the landing of an airplane, and to make a direct analysis of the control movements, the accelerations, and air speeds during these the maneuvers. The recording instruments developed at the laboratory were used in this test and the records obtained by them w… more
Date: 1923
Creator: Carroll, T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Study of Airplane Maneuvers With Special Reference to Angular Velocities

Description: "This investigation was undertaken by the National Advisory Committee for Aeronautics for the purpose of increasing our knowledge on the behavior of the airplane during various maneuvers and to obtain values of the maximum angular velocities and accelerations in flight. The method consisted in flying a JN4H airplane through various maneuvers while records were being taken of the control position, the air speed, the angular velocity and the acceleration along the Z axis. The results showed that … more
Date: 1923
Creator: Reid, H. J. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Control in Circling Flight

Description: "This investigation was undertaken for the purpose of developing instruments that would record the forces and positions of all three controls, and to obtain data on the behavior of an airplane in turns. All the work was done on a standard rigged JN4H (airplane no. 2 of National Advisory Committee for Aeronautics, report no. 70). It was found that the airplane was longitudinally unstable and nose heavy; that it was laterally unstable, probably due to too little dihedral; and that it was directio… more
Date: 1923
Creator: Norton, F. H. & Allen, E. T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Controllability and Maneuverability of Airplanes

Description: This investigation was conducted for the purpose of studying the behavior of the JN4H airplane in free flight under the action of its controls and from this to arrive at satisfactory definitions and coefficients for controllability and maneuverability. The method consisted in recording the angular velocity about the three axes, together with the air speed, control positions, and acceleration.
Date: 1923
Creator: Norton, F. H. & Brown, W. G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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