UNT Libraries Government Documents Department - 30 Matching Results

Search Results

Results: 1 - 24 next
open access

An Investigation of the Effectiveness of Ignition Sparks

Description: "The effectiveness of ignition sparks was determined by measuring the volume (or mass) of hydrogen and of oxygen which combines at low pressures. The sparks were generated by a magneto and an ignition spark coil. It was found that with constant energy the amount of reaction increases as the capacitance component of the spark increases" (p. 575).
Date: April 1930
Creator: Peters, Melville F.; Summerville, Wayne L. & Davis, Merlin
Item Type: Refine your search to only Report
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
open access

Experimental determination of jet boundary corrections for airfoil tests in four open wind tunnel jets of different shapes

Description: "This experimental investigation was conducted primarily for the purpose of obtaining a method of correcting to free air conditions the results of airfoil force tests in four open wind tunnel jets of different shapes. Tests were also made to determine whether the jet boundaries had any appreciable effect on the pitching moments of a complete airplane model. Satisfactory corrections for the effect of the boundaries of the various jets were obtained for all the airfoils tested, the span of the la… more
Date: April 16, 1930
Creator: Knight, Montgomery & Harris, Thomas A.
Item Type: Refine your search to only Report
open access

Measurement of the Differential and Total Thrust and Torque of Six Full-Scale Adjustable-Pitch Propellers

Description: "Force measurements giving total thrust and torque, and propeller slip stream surveys giving differential thrust and torque were simultaneously made on each of six full-scale propellers in the 20-foot propeller-research tunnel of the National Advisory Committee for Aeronautics. They were adjustable-pitch metal propellers 9.5 feet in diameter; three had modified Clark Y blade sections and three had modified RAF-6 blade sections. This report gives the differential thrust and torque and the variat… more
Date: April 15, 1932
Creator: Stickle, George W.
Item Type: Refine your search to only Report
open access

Measurements of flow in the boundary layer of a 1/40-scale model of the U. S. Airship "Akron"

Description: This report presents the results of measurements of flow in the boundary layer of a 1/40-scale model of the U. S. Airship "Akron" (ZRS-4) made with the object of determining the boundary-layer thickness, the point of transition from laminar to the turbulent flow, and the velocity distribution in the boundary layer.
Date: April 27, 1932
Creator: Freeman, Hugh B.
Item Type: Refine your search to only Report
open access

Tests of nacelle-propeller combinations in various positions with reference to wings 3: Clark y wing - various radial-engine cowlings - tractor propeller

Description: From Summary: "This report is the third of a series giving the results obtained in the 20-foot wind tunnel on the interference drag, and propulsive efficiency of nacelle-propeller-wing combinations. The first report gave the results of the tests of an NACA cowled air-cooled engine nacelle with tractor propeller located in 21 positions with reference to a thick wing. The second report gave the results for several engine cowlings and nacelles with tractor propeller located in four positions with … more
Date: April 20, 1933
Creator: Wood, Donald H.
Item Type: Refine your search to only Report
open access

Air conditions close to the ground and the effect on airplane landings

Description: This report presents the results of an investigation undertaken to determine the feasibility of making glide landings in gusty air. Wind velocities were measured at several stations between the ground and a height of 51 feet, and flight tests were made to determine the actual influence of gusts on an airplane gliding close to the ground.
Date: April 3, 1934
Creator: Thompson, F. L.; Peck, W. C. & Beard, A. P.
Item Type: Refine your search to only Report
open access

Analysis of 2-Spar Cantilever Wings With Special Reference to Torsion and Load Transference

Description: "This paper deals with the analysis of 2-spar cantilever wings in torsion, taking cognizance of the fact that the spars are not independent, but are interconnected by ribs and other structural members. The principles of interaction are briefly explained, showing that the mutual relief action occurring depends on the "pure torsional stiffness" of the wing cross section. Various practical methods of analysis are outlined" (p. 45).
Date: April 10, 1934
Creator: Kuhn, Paul
Item Type: Refine your search to only Report
open access

Heat transfer from finned metal cylinders in an air stream

Description: This report presents the results of tests made to supply design information for the construction of metal fins for the cooling of heated cylindrical surfaces by an air stream. A method is given for determining fin dimensions for a maximum heat transfer with the expenditure of a given amount of material for a variety of conditions of air flow and metals.
Date: April 26, 1934
Creator: Biermann, Arnold E. & Pinkel, Benjamin
Item Type: Refine your search to only Report
open access

Tests of 16 related airfoils at high speed

Description: From Summary: "In order to provide information that might lead to the development of better propeller section, 13 related symmetrical airfoils were tested in the NACA high-speed wind tunnel for a study of the effect of thickness form on the aerodynamic characteristics. The thickness-form variables studies were the value of the maximum thickness, the position along the chord at which the maximum thickness occurs, and the value of the leading-edge radius. The tests were conducted through the low … more
Date: April 28, 1934
Creator: Stack, John & von Doenhoff, Albert E.
Item Type: Refine your search to only Report
open access

Distribution and Regularity of Injection From a Multicylinder Fuel-Injection Pump

Description: This report presents the results of performance test conducted on a six-cylinder commercial fuel-injection pump that was adjusted to give uniform fuel distribution among the cylinders at a throttle setting of 0.00038 pound per injection and a pump speed of 750 revolutions per minute. The throttle setting and pump speed were then varied through the operating range to determine the uniformity of distribution and regularity of injection.
Date: April 9, 1935
Creator: Rothrock, A. M. & Marsh, E. T.
Item Type: Refine your search to only Report
open access

Hydrogen as an auxiliary fuel in compression-ignition engines

Description: From Summary: "An investigation was made to determine whether a sufficient amount of hydrogen could be efficiently burned in a compression-ignition engine to compensate for the increase of lift of an airship due to the consumption of the fuel oil. The performance of a single-cylinder four-stroke-cycle compression-ignition engine operating on fuel oil alone was compared with its performance when various quantities of hydrogen were inducted with the inlet air. Engine-performance data, indicator c… more
Date: April 15, 1935
Creator: Gerrish, Harold C. & Foster, Hampton H.
Item Type: Refine your search to only Report
open access

Measurements of fuel distribution within sprays for fuel-injection engines

Description: Two methods were used to measure fuel distribution within sprays from several types of fuel-injection nozzles. A small tube inserted through the wall of an air tight chamber into which the sprays were injected could be moved about inside the chamber. When the pressure was raised to obtain air densities of 6 and 14 atmospheres, some air was forced through the tube and the fuel that was carried with it was separated by absorbent cotton and weighed. Cross sections of sprays from plain, pintle, mul… more
Date: April 8, 1936
Creator: Lee, Dana W.
Item Type: Refine your search to only Report
open access

The effect of lateral controls in producing motion of an airplane as computed from wind-tunnel data

Description: This report presents the results of an analytical study of the lateral controllability of an airplane in which both the static rolling and yawing moments supplied by the controls and the reactions due to the inherent stability of the airplane have been taken into account. The investigation was undertaken partly for the purpose of coordinating the results of a long series of wind-tunnel investigations with phenomena observed in flight tests; for this reason a hypothetical average airplane, embod… more
Date: April 20, 1936
Creator: Weick, Fred E. & Jones, Robert T.
Item Type: Refine your search to only Report
open access

Wing-nacelle-propeller interference for wings of various spans force and pressure-distribution tests

Description: Report presents the results of an experimental investigation made in the NACA full-scale wind tunnel to determine the effect of wing span on nacelle-propeller characteristics and, reciprocally, the lateral extent of nacelle and propeller influence on a monoplane wing. The results provide a check on the validity of the previous research on nacelles and propellers with 15-foot-span wings tested in the 20-foot wind tunnel and reported in technical reports 415, 462, 505, 506, and 507.
Date: April 21, 1936
Creator: Robinson, Russell G. & Herrnstein, William H., Jr.
Item Type: Refine your search to only Report
open access

The quiescent-chamber type compression-ignition engine

Description: Report presents the results of performance tests of a single-cylinder 4-stroke-cycle compression-ignition engine having a vertical disk form of combustion chamber without air flow. The number, size, and direction of the orifices of the fuel-injection nozzles used were independently varied. A table and graphs are presented showing the performance of the engine with different nozzles; results of tests at different compression ratios, boost pressures, and coolant temperatures are also included.
Date: April 30, 1936
Creator: Foster, H. H.
Item Type: Refine your search to only Report
open access

Pressure-distribution measurements at large angles of pitch on fins of different span-chord ratio on a 1/40-scale model of the U. S. Airship "Akron"

Description: Report presents the results of pressure-distribution measurements on a 1/40-scale model of the U. S. Airship "Akron" conducted in the NACA 20-foot wind tunnel. The measurements were made on the starboard fin of each of four sets of horizontal tail surfaces, all of approximately the same area but differing in span-chord ratio, for five angles of pitch varying from 11.6 degrees to 34 degrees, for four elevator angles, and at air speeds ranging from 56 to 77 miles per hour. Pressures were also mea… more
Date: April 4, 1937
Creator: McHugh, James G.
Item Type: Refine your search to only Report
open access

An analysis of the factors that determine the periodic twist of an autogiro rotor blade, with a comparison of predicted and measured results

Description: Report presents an analysis of the factors that determine the periodic twist of a rotor blade under the action of the air forces on it. The results of the analysis show that the Fourier coefficients of the twist are linear expressions involving only the tip-speed ratio, the pitch setting, the inflow coefficient, the pitching-moment coefficient of the blade airfoil section, and the physical characteristics of the rotor blade and machine.
Date: April 14, 1937
Creator: Wheatley, John B.
Item Type: Refine your search to only Report
open access

Spinning characteristics of the XN2Y-1 airplane obtained from the spinning balance and compared with results from the spinning tunnel and from flight tests

Description: Report presents the results of tests of a 1/10-scale model of the XN2Y-1 airplane tested in the NACA 5-foot vertical wind tunnel in which the six components of forces and moments were measured. The model was tested in 17 attitudes in which the full-scale airplane had been observed to spin, in order to determine the effects of scale, tunnel, and interference. In addition, a series of tests was made to cover the range of angles of attack, angles of sideslip, rates of rotation, and control setting… more
Date: April 16, 1937
Creator: Bamber, M. J. & House, R. O.
Item Type: Refine your search to only Report
open access

Resume and analysis of NACA lateral control research

Description: "An analysis of the principal results of recent NACA lateral control research is made by utilizing the experience and progress gained during the course of the investigation. Two things are considered of primary importance in judging the effectiveness of different control devices: the (calculated) banking and yawing motion of a typical small airplane caused by a deflection of the control, and the stick force required to produce this deflection. The report includes a table in which a number of di… more
Date: April 20, 1937
Creator: Weick, Fred E. & Jones, Robert T.
Item Type: Refine your search to only Report
open access

Pressure distribution over a rectangular airfoil with a partial-span split flap

Description: This report presents the results of pressure-distribution tests of a Clark y wing model with a partial-span split flap made to determine the distribution of air loads over both the wing and the flap. The model was used in conjunction with a reflection plane in the NACA 7 by 10 foot wind tunnel. The 20-percent-chord split flap extended over the inboard 60 percent of the semispan. The tests were made at various flap deflections up to 45 degrees and covered a range of angles of attack from zero li… more
Date: April 28, 1937
Creator: Wenzinger, Carl J. & Harris, Thomas A.
Item Type: Refine your search to only Report
open access

Tests of Two Full-Scale Propellers With Different Pitch Distributions, at Blade Angles Up to 60 Degrees

Description: "Two 3-blade 10-foot propellers were operated in front of a liquid-cooled engine nacelle. The propellers differed only in pitch distribution; one had normal distribution (nearly constant pitch for a blade angle of 15 degrees at 0.75 radius), and the other had the pitch of the tip sections decreased with respect to that for the shank sections (blade angle of 35 degrees for nearly constant pitch distribution). Propeller blade angles at 0.75r from 15 degrees to sixty degrees, corresponding to desi… more
Date: April 14, 1938
Creator: Biermann, David & Hartman, Edwin P.
Item Type: Refine your search to only Report
open access

Theoretical stability and control characteristics of wings with various amounts of taper and twist

Description: From Summary: "Stability derivatives have been computed for twisted wings of different plan forms that include variations in both the wing taper and the aspect ratio. Taper ratios of 1.0, 0,50, and 0.25 are considered for each of three aspect ratios: 6, 10, and 16. The specific derivatives for which results are given are the rolling-moment and the yawing-moment derivatives with respect to (a) rolling velocity, (b) yawing velocity, and (c) angle of sideslip. These results are given in such a for… more
Date: April 19, 1938
Creator: Pearson, Henry A. & Jones, Robert T.
Item Type: Refine your search to only Report
Back to Top of Screen