You limited your search to:

 Collection: Technical Report Archive and Image Library
Test data on the shear strength of machine countersunk-riveted joints assembled by an NACA flush-riveting procedure
No Description
Test flight of the Handley Page torpedo-carrying airplane
No Description
Test Manual (Tentative) For Permselective Membranes
No Description
Test of 0.14-scale models of the control surfaces of Army project MX-511 in attitudes simulating spins
No Description
Test of a dual-rotation axial-flow fan
No Description
Test of a model propeller with symmetrical blade sections
This report, prepared at the request of NACA, gives the results of tests on a model propeller having blade sections with form of Gottingen airfoil no. 409. The model is shown to have a dynamic pitch practically equal to the nominal or geometrical pitch, and a somewhat higher efficiency but lower coefficient than would be expected of a propeller of more conventional sections.
Test of an adjustable pitch model propeller at four blade settings
This note describes tests of an adjustable blade metal model propeller, both in a free wind stream and in combination with a model fuselage, at four settings of the blades. The model propeller is designed for a uniform nominal pitch/diameter ratio of .7 and the blade settings used correspond to nominal pitch/diameter ratios of .5, .7, .9, and 1.1 at the .6 radius. The tests show that propellers of this type may be considerably changed in setting from the designed pitch angles and yet give excellent performance. The efficiency realized and power absorbed when blades are set at other than the designed angle, are little different than would be obtained from a propeller with uniform pitch equal to the mean pitch of the propeller under test.
Test of an aerodynamically heated multiweb wing structure (MW-1) in a free jet at Mach number 2
No Description
Test of NACA 66,2-116, a = 0.6 airfoil section fitted with pressure balanced and slotted flaps for the wing of the XP-63 airplane
No Description
Test of single-stage axial-flow fan
A single-stage axial fan was built and tested in the shop of the propeller-research tunnel of the NACA. The fan comprised a simple 24-blade rotor having a diameter of 21 inches and a solidity of 0.86 and a set of 37 contravanes having a solidity of 1.33. The rotor was driven by a 25-horsepower motor capable of rotating at a speed of 3600 r.p.m. The fan was tested for volume, pressure, and efficiency over a range of delivery pressures and volumes for a wide range of contravane and blade-angle settings. The test results are presented in chart form in terms of nondimensional units in order that similar fans may be accurately designed with a minimum effort. The maximum efficiency (88 percent) was obtained by the fan at a blade angle of 30 degrees and a contravane angle of 70 degrees. An efficiency of 80 percent was obtained by the fan with the contravanes removed.
Test of six types of Bakelite-bonded wire strain gages
No Description
Test of specimen of wood of longerons of the S.E.5 airplane after seven years' service
A transverse test was made of the wood sample using a 5,000 pound Olsen testing machine, the deflection under load being measured by means of a Wissler dial. The results of the transverse test are given and the stress-strain curve is attached.
Test Report on Measurements on a Series of Tapered Wings of Small Aspect Ratio (Trapezoidal Wing with Fuselage)
This is the second of a series of six reports dealing with three- and six-component measurements on the tapering series at small aspect ratio. The present report concerns the trapezoidal wing with fuselage.
Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio
The investigations of the reports to 4 on wings of small aspect ratio are continued. The present report deals with the results of the three- and six-component measurements and the flow pictures of the triangular wing series with the aspect ratio Lambda = 3 to Lambda = 1.
Test Report on Three-and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Elliptic Wing)
The report UM No. 1023/1 which presented the results of measurements for a series of trapezoidal wings was the beginning of a series on wings with aspect ratio 1 to 3 and various contours. In report No. 1023/1 the aspect ratio (Lambda = 4/3) remained the same; the tapering was modified. The present report gives the results of the series of elliptic wings. Here the aspect ratio varies from 1 to 2 with the sweepback. The contour is formed by elliptic arcs. The influence of sweepback and contour upon the neutral point is shown.
Test Report on Three- and Six-Component Measurements on a Series of Tapered Wings of Small Aspect Ratio (Partial Report: Trapezoidal Wing)
The present report, which forms the first of six articles on experiments with airfoils of aspect ratio from 1 to 3 and various planforms, deals with the three- and six-component measurements made on the trapezoidal wing series in the 2.15 x 3-meter wind tunnel of the DVL at the request of the Henschel Aircraft Company.
Test-stand investigation of a rectangular ram-jet engine
No Description
Test-stand investigation of cooling characteristics and factors affecting temperature distribution of a double-row aircraft engine
No Description
Testing a windmill airplane ("autogiro")
In order to clear up the matter ( In the Spanish report it was stated that the reference surface for the calculation of the coefficients c(sub a) and c(sub w) was the area of all four wings, instead of a single wing), the model of a windwill airplane was tested in the Gottingen wind tunnel.
Testing airplane fabrics
The following considerations determine the strength of airplane fabrics: 1. maximum air forces acting on the surfaces (including local stresses); 2. tensions produced in the fabrics, in the directions of both warp and filling; 3. factor of safety required. The question of the permissible depression of the fabric as affecting the aerodynamic requirements in regard to the maintenance of shape of the section, the tenacity and extensibility of the layer of dope, its strength and its permeability to water is almost as important.
Testing airplanes in flight: determining position of resultant of action of air and longitudinal stability of an airplane at different angles of attack
Measurements made during flight with the triple recording device which gives the horizontal and vertical speeds of an airplane and the angle it makes with the horizon, render it possible to calculate its lift, its drag, and R the resultant of the action of the air both in magnitude and direction, but with these data alone, it is impossible to determine the position of this resultant in the plane of symmetry of the airplane. We will also see how we may determine the position of R during flight and then calculate the variations in the stability of an airplane.
Testing balloon gas
In the generation, storage, and use of hydrogen for balloon purposes it is necessary to be able to determine, first, its lifting power, and, secondly, its purity. The lifting power may be determined directly from the specific gravity. Contamination by other gases may be determined by analysis for oxygen, carbon dioxide, etc., by the usual methods of gas analysis. The determination of oxygen is important, since the presence of oxygen in amounts beyond certain limits will make the compressing, handling, and use of the gas hazardous. If the specific gravity of the gas is known, however, it may not be necessary to analyze the gas for oxygen and other gases, because the specific gravity in itself is a delicate criterion of the purity of hydrogen. Report describes a simple, portable apparatus for testing hydrogen, with special reference to its use in balloons.
The testing of airplane fabrics
This report considers the determining factors in the choice of airplane fabrics, describes the customary methods of testing and reports some of the experimental results. To sum up briefly the results obtained with the different fabrics, it may be said that increasing the strength of covering fabrics by using coarser yarns ordinarily offers no difficulty, because the weight increment from doping is relatively smaller.
The testing of aviation engines
No Description
The testing of balloon fabrics
Report describes methods and materials used in waterproofing and fireproofing airplane fabrics using dopes. The determination of the probable life of a balloon fabric in service by experimental means is of great value in choosing the most suitable fabrics for a given purpose and in pointing the way to improvements in compounding and construction. The usefulness of exposure to the weather for this purpose has been amply demonstrated. Various attempts have been made to reproduce by artificial means the conditions promoting deterioration in service, but without marked success. Exposure to the weather remains the most satisfactory method for this purpose, and a consideration of the characteristics of such tests is therefore important. This report presents the results of a typical series of exposure tests made in 1917.
Testing of Containment Capabilities of Reinforced Concrete-Shielded Enclosures
No Description
Testing of Fire-Clay Brick with Special Reference to their Use in Coal-Fired Boiler Settings
Technical paper issued by the Bureau of Standards over studies conducted on fire-clay bricks. The results of the studies are discussed. This paper includes tables, and illustrations.
The Testing of Glass Volumetric Apparatus
Report issued by the Bureau of Standards over testing conducted on volumetric glass apparatus. Types of glass apparatus being tested are presented and discussed. The results of the testing are also discussed. This report includes tables, illustrations, and photographs.
Testing of high-octane fuels in the single-cylinder airplane engine
One of the most important properties of aviation fuels for spark-ignition engines is their knock rating. The CFR engine tests of fuels of 87 octane and above does not always correspond entirely to the actual behavior of these fuels in the airplane engine. A method is therefore developed which, in contrast to the octane number determination, permits a testing of the fuel under various temperatures and fuel mixture conditions. The following reference fuels were employed: 1) Primary fuels; isooctane and n-heptane; 2) Secondary fuels; pure benzene and synthetic benzine.
Testing of Metal Volumetric Standards
No Description
Tests and approximate analysis of bending stresses due to torsion in a D-section box
No Description
Tests at Mach number 1.62 of a series of missile configurations having tandem cruciform lifting surfaces
No Description
Tests for determining the effect of a rotating cylinder fitted into the leading edge of an airplane wing
Experiments were performed with a wing model, to which a rotary cylinder had been fitted. The rotation of the cylinder had a remarkable effect on the aerodynamic properties of the wing.
Tests for the determination of the stress condition in tension fields
The present experiments treat the stress of actual tension fields within the elastic range. They give the magnitude of the flexural stresses due to wrinkling. They also disclose, particularly by slightly exceeded buckling load, the marked unloading - as compared with the tension-field theory - of the uprights as a result of the flexural stiffness of the web plate. The test sheets were clamped at the edges and brought to buckling through shearing and compressive stresses applied in the direction of the long sides.
Tests for the elimination of tail flutter
On various low-wing monoplanes the horizontal tail surfaces flutter in flight at large angles of attack and occasionally in curvilinear flight. This flutter leads to torsional vibrations of the rear end of the fuselage, as manifested by vibrations of the control stick. According to the earlier DVL investigations tail flutter is due to the influence, on horizontal tail surfaces, of eddies or vortices shed at large angles of attack by the upper surface of the wing root. The cause of tail flutter on a low-wing monoplane and the means of preventing it are investigated in the present report.
Tests in the 19-foot pressure tunnel of a 1/2.75-scale model of the F4U-1 airplane with several balanced elevators, full-span flaps, and droppable gas tank
No Description
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with a variable-incidence triangular wing and an all-movable horizontal tail
No Description
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : lateral characteristics
No Description
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 2 triangular wing and an all-movable horizontal tail : longitudinal characteristics
No Description
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 3 triangular wing and an all-movable horizontal tail : longitudinal and lateral characteristics
No Description
Tests in the Ames 40- by 80-foot wind tunnel of an airplane configuration with an aspect ratio 4 triangular wing and an all-movable horizontal tail - longitudinal characteristics
No Description
Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls
No Description
Tests in the Ames 40- by 80-foot wind tunnel of the aerodynamic characteristics of airplane models with plain spoiler ailerons
No Description
Tests in the Ames 40- by 80-foot wind tunnel of the effects of varying wing modifications on the longitudinal characteristics of two-triangular wing airplane models with and without horizontal tails
No Description
Tests in the Ames 40- by 80-foot wind tunnel of two airplane models having aspect ratio 2 trapezoidal wings of taper ratios 0.33 and 0.20
No Description
Tests in the gust tunnel of a model of the XBM-1 airplane
No Description
Tests in the NACA two-dimensional low-turbulence tunnel of airfoil sections designed to have small pitching moments and high lift-drag ratios
No Description
Tests in the Variable-Density Tunnel of Seven Tapered Wings Having N.A.C.A. 230 Mean Lines, Special Report
At the request of the Materiel Division of the Army Air Corps, seven tapered wings having sections based on the N.A,C.A. 230 mean line were tested in the variable-density wind tunnel, The characteristics of the wings are given.
Tests in the variable-density wind tunnel of related airfoils having the maximum camber unusually far forward
A family of related airfoils having the position of maximum camber unusually far forward was investigated in the variable-density tunnel as an extension of the study recently completed of a large number of related airfoils. The new airfoils gave improved characteristics over those previously investigated, especially in regard to the pitching moment. Some of the new sections are markedly superior to well-known and commonly used sections and should replace them in applications requiring a slightly cambered section of moderate thickness having a small pitching-moment coefficient.
Tests in the variable-density wind tunnel of the NACA 23012 airfoil with plain and split flaps
Section characteristics for use in wing design are presented for the NACA 23012 airfoil with plain and split flaps of 20 percent wing chord at a value of the effective Reynolds number of about 8,000,000. The flap deflections covered a range from 60 degrees upward to 75 degrees downward for the plain flap and from neutral to 90 degrees downward for the split flap. The split flap was aerodynamically superior to the plain flap in producing high maximum lift coefficients and in having lower profile-drag coefficients at high lift coefficients.