National Advisory Committee for Aeronautics (NACA) - 150 Matching Results

Search Results

prev Results: 97 - 120 next
open access

A method of flight measurement of spins

Description: A method is described involving the use of recording turn meters and accelerometers and a sensitive altimeter, by means of which all of the physical quantities necessary for the complete determination of the flight path, motion, attitude, forces, and couples of a fully developed spin can be obtained in flight. Data are given for several spins of two training type airplanes which indicate that the accuracy of the results obtained with the method is satisfactory.
Date: October 7, 1930
Creator: Soulé, Hartley A. & Scudder, Nathan F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Methods for the Identification of Aircraft Tubing of Plain Carbon Steel and Chromium-Molybdenum Steel

Description: The survey of the possibilities for distinguishing between plain carbon and chromium-molybdenum steel tubing included the Herbert pendulum hardness, magnetic, sparks, and chemical tests. The Herbert pendulum test has the disadvantages of all hardness tests in being limited to factory use and being applicable only to scale-free, normalized material. The small difference in the range of hardness values between plain carbon and chromium-molybdenum steels is likewise a disadvantage.
Date: October 1930
Creator: Mutchler, W. H. & Buzzard, R. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A new chart for estimating the absolute ceiling of an airplane

Description: This report is concerned with the derivation of a chart for estimating the absolute ceiling of an airplane. This chart may be used in conjunction with the usual curves of power required and power available as an accurate substitute for extended calculation, or it may be used in the estimation of absolute ceiling when power curves are not available.
Date: July 1930
Creator: Diehl, Walter S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of a high-speed compression-ignition engine using multiple orifice fuel injection nozzles

Description: This report presents test results obtained at the Langley Memorial Aeronautical Laboratory of the National Advisory Committee for Aeronautics during an investigation to determine the relative performance of a single-cylinder, high-speed, compression-ignition engine when using fuel injection valve nozzles with different numbers, sizes, and directions of round orifices. A spring-loaded, automatic injection valve was used, centrally located at the top of a vertical disk-type combustion chamber for… more
Date: June 1930
Creator: Spanogle, J. A. & Foster, H. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A Possible Method for Preventing the Autorotation of Airplane Wings

Description: "At the suggestion of Professor Betz, the following device was tested with the object of reducing the autorotational speed of airplane wings. The model of a normal wing with the Gottigen profile 420, 1 meter span and 0.2 meter chord was provided with a pair of symmetrical slots on the suction side, connected with each other inside the wing. The arrangement of the testing equipment and models are given and the effect of the slots can be seen in the experimental curves that are included" (p. 1).
Date: June 1930
Creator: Schrenk, Oskar
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Practical Tests With The "Auto Control Slot" Part 1: Lecture

Description: "The effect of a slotted wing depends essentially on the fact that a secondary flow branches off from the main flow and passes to the suction side of the profile. It is thus possible to delay the separation greatly and increase the lift. The practical aspect of the slotted wing is less known in Germany, especially the results obtained during the last three years since the introduction of the 'auto control slot'" (p. 1).
Date: November 1930
Creator: Lachmann, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Practical Tests With The "Auto Control Slot" Part 2: Discussion

Description: "For some time the D.V.L. has been investigating the question of applicability of Handley Page slotted wings to German airplanes. Comparitive gliding tests were made with open and closed slots on an Albatros L 75 airplane equipped with the Handley Page "auto control slots." This investigation served to determine the effect of the auto control slot on the properties and performances of airplanes at large angles of attack. The most important problems were whether the angle of glide at small angle… more
Date: November 1930
Creator: Lachmann, G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Present Status of Aircraft Instruments

Description: This report gives a brief description of the present state of development and of the performance characteristics of instruments included in the following group: speed instruments, altitude instruments, navigation instruments, power-plant instruments, oxygen instruments, instruments for aerial photography, fog-flying instruments, general problems, summary of instrument and research problems. The items considered under performance include sensitivity, scale errors, effects of temperature and pres… more
Date: October 9, 1930
Creator: Subcommittee on Instruments
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution on the tail surfaces of a PW-9 pursuit airplane in flight

Description: Presented here are pressure distribution data obtained from the tail surfaces of a PW-9 in a number of flight maneuvers. The results given are part of those obtained in an extensive investigation of the pressure distribution over all of the lifting and control surfaces of this airplane. The results are given in tabular and curve form and are discussed briefly with respect to their comparison with existing tail surface design specifications. It is recommended that tail load design loadings shoul… more
Date: April 1930
Creator: Rhode, Richard V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution over a Douglas wing tip on a biplane in flight

Description: "This note presents the results obtained in pressure distribution tests on the right upper wing panel and tip of a Douglas M-3 airplane in flight. These tests are a part of a more extensive investigation of the effect of changes in tip shape on the load distribution, the tip reported herein being the first of a series of tip shapes being tested. The results are given in tables and curves in such form that the load distribution for any conditions may be determined easily. Tests were made at Lang… more
Date: August 1930
Creator: Rhode, Richard V. & Lundquist, Eugene E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution over a symmetrical airfoil section with trailing edge flap

Description: "Measurements were made to determine the distribution of pressure over one section of an R. A. F. 30 (symmetrical) airfoil with trailing edge flaps. In order to study the effect of scale measurements were made with air densities of approximately 1 and 20 atmospheres. Isometric diagrams of pressure distribution are given to show the effect of change in incidence, flap displacement, and scale upon the distribution. Plots of normal force coefficient versus angle of attack for different flap displa… more
Date: April 2, 1930
Creator: Jacobs, Eastman N. & Pinkerton, Robert M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Distribution Over a Thick, Tapered and Twisted Monoplane Wing Model-N.A.C.A. 81-J

Description: "This reports presents the results of pressure distribution tests on a thick, tapered and twisted monoplane wing model. The investigation was conducted for the purpose of obtaining data on the aerodynamic characteristics of the new wing and to provide additional information suitable for use in the design of tapered cantilever wings. The tests included angles of attack up to 90 degrees. The span loading over the wing was approximately of elliptical shape, which gave rise to relatively small bend… more
Date: May 21, 1930
Creator: Wenzinger, Carl J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure distribution over the fuselage of a PW-9 pursuit airplane in flight

Description: "This report presents the results obtained from pressure distribution tests on the fuselage of a PW-9 pursuit airplane in a number of conditions of flight. The investigation was made to determine the contribution of the fuselage to the total lift in conditions considered critical for the wing structure, and also to determine whether the fuselage loads acting simultaneously with the maximum tail loads were of such a character as to be of concern with respect to the structural design of other par… more
Date: August 1, 1930
Creator: Rhode, Richard V. & Lundquist, Eugene E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Pressure Distribution Over the Wings and Tail Surfaces of a PW-9 Pursuit Airplane in Flight

Description: This report presents the results of an investigation to determine (1) the magnitude and distribution of aerodynamic loads over the wings and tail surfaces of a pursuit-type airplane in the maneuvers likely to impose critical loads on the various subassemblies of the airplane structure, (2) To study the phenomenon of center of pressure movement and normal force coefficient variation in accelerated flight, and (3) to measure the normal accelerations at the center of gravity, wing-tip, and tail, i… more
Date: February 3, 1930
Creator: Rhode, Richard V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Pressure Fluctuations in a Common-Rail Fuel Injection System

Description: This report presents the results of an investigation to determine experimentally the instantaneous pressures at the discharge orifice of a common-rail fuel injection system in which the timing valve and cut-off valve were at some distance from the automatic fuel injection valve, and also to determine the methods by which the pressure fluctuations could be controlled. The results show that pressure wave phenomena occur between the high-pressure reservoir and the discharge orifice, but that these… more
Date: May 20, 1930
Creator: Rothrock, A. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

The Prevention of the Ice Hazard on Airplanes

Description: A review of various methods to prevent ice formation and adhesion to aircraft surfaces is given. It was concluded that the adhesion of ice to a surface may be reduced somewhat by the application of certain waxes and varnishes. In the experiments described, the varnishes containing calcium stearate and calcium oleate gave the best results. In wind tunnel tests, the adhesion was further reduced by the application of these waxes and varnishes to a thin, heat insulating layer of rubber.
Date: July 1930
Creator: Geer, William C. & Scott, Merit
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Propulsion by Reaction

Description: This report concerns propulsion by means of rockets. The author concerns himself mainly with efficiency of propulsion and he defines and mathematically expresses those efficiencies.
Date: June 1930
Creator: Roy, Maurice
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Rate of Heat Transfer From Finned Metal Surfaces

Description: The object was to evaluate the factors which control the rate of heat transfer to a moving current of air from finned metal surfaces similar to those used on aircraft engine cylinders. This was to establish data which will enable the finning of cooling surfaces to be designed to suit the particular needs of any specific application. Most of the work was done on flat copper specimens 6 inches square, upon which were mounted copper fins with spacings varying from 1/2 inch to 1/12 inch. All fins w… more
Date: January 1930
Creator: Taylor, C. Fayette & Rehbock, A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Ratier Metal Propeller With Pitch Variable in Flight

Description: One of the serious sources of difficulties in variable pitch propellers is the turning moment or torque due to the centrifugal force which tends to bring the mean plane of the blades into the plane of rotation. This moment, which is found elsewhere only in propellers with removable blades, is so great that the aerodynamic forces, as regards their effect on the torsion, become entirely negligible in comparison with it. This report presents the Ratier Company's solution to changing the pitch of a… more
Date: April 1930
Creator: Léglise, Pierre
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Recent Tests of Tailless Airplanes

Description: This report details the advantages and construction of tailless airplanes. Both a glider and a powered model were built and the specifications of both airplanes are listed.
Date: May 1930
Creator: Lippisch, Alexander
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Refrigerated wind tunnel tests on surface coatings for preventing ice formation

Description: "This investigation was conducted to determine the effectiveness of various surface coatings as a means for preventing ice formations on aircraft in flight. The substances used as coatings for these tests are divided into two groups: compounds soluble in water, and those which are insoluble in water. It was found that certain soluble compounds were apparently effective in preventing the formation of ice on an airfoil model, while all insoluble compounds which were tested were found to be ineffe… more
Date: May 1930
Creator: Knight, Montgomery & Clay, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Relation Between the Stability Characteristics and the Controllability of German Airplanes

Description: This survey is intended to give a general approximate idea of the stability and controllability of German airplanes. Both flight characteristics, including the behavior of the airplane under the action of deflected controls and external disturbances, and flight performance, which refers to climbing, speed, take-off, and landing qualities.
Date: February 1930
Creator: Hübner, Walter
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen