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  Partner: UNT Libraries Government Documents Department
 Collection: Technical Report Archive and Image Library
Tests of NACA 65(216)-420 and 66(218)-420 airfoils at high speeds
No Description digital.library.unt.edu/ark:/67531/metadc61374/
Tests of nacelle-propeller combinations in various positions with reference to wings II : thick wing - various radial-engine cowlings - tractor propeller
This report is the second of a series giving the results obtained in the 20-foot wind tunnel of the National Advisory Committee for Aeronautics on the interference drag and propulsive efficiency of nacelle-propeller-wing combinations. The first report gave the results of the test of a N.A.C.A. cowled air-cooled engine nacelle located in 21 positions with reference to a thick wing. The present report gives results of tests of a normal engine nacelle with several types of cowling and fairings in four of the positions with reference to the same wing. (author). digital.library.unt.edu/ark:/67531/metadc65687/
Tests of nacelle-propeller combinations in various positions with reference to wings III : Clark y wing - various radial-engine cowlings - tractor propeller
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 reference to same wing. The present report gives results of tests of the same nacelles and cowlings in the same positions with reference to a smaller wing of Clark y section. The lift, drag, and propulsive efficiency were determined at several angles of attack for each cowling and in each nacelle location. digital.library.unt.edu/ark:/67531/metadc66119/
Tests of nacelle-propeller combinations in various positions with reference to wings IV : thick wing - various radial-engine cowlings - tandem propellers
This report is the fourth of a series giving the results obtained from wind tunnel tests to determine the interference lift and drag and propulsive efficiency of wing-nacelle-propeller combinations. Previous reports give the results of tests with tractor propellers with various forms of nacelles and engine cowlings. This report gives the results of tests of tandem arrangements of engines and propellers in 11 positions with reference to a thick wing. digital.library.unt.edu/ark:/67531/metadc66160/
Tests of nacelle-propeller combinations in various positions with reference to wings. Part I : thick wing-N.A.C.A. cowled nacelle-tractor propeller
This report gives the results in the 20-foot propeller research tunnel of the National Advisory Committee for Aeronautics on the interference drag and propulsive efficiency of a nacelle-propeller combination located in 21 positions with reference to a thick wing. The lift, drag, and propulsive efficiency were obtained at several angles of attack for each of the 21 locations. A net efficiency was derived for determining the over-all effectiveness of each nacelle location. Best results were obtained with the propeller about 25 per cent of the chord directly ahead of the leading edge. A location immediately above or below the wing near the leading edge was very poor. digital.library.unt.edu/ark:/67531/metadc66072/
Tests of nacelle-propeller combinations in various positions with reference to wings V : Clark Y biplane cellule - NACA cowled nacelle - tractor propeller
This report is the fifth of a series giving the results obtained from wind tunnel tests on the interference drag and propulsive efficiency of nacelle-propeller-wing combinations. This report gives results of tests of an NACA cowled air-cooled engine nacelle with tractor propeller located in 12 positions with reference to a Clark Y biplane cellule. digital.library.unt.edu/ark:/67531/metadc66161/
Tests of nacelle-propeller combinations in various positions with reference to wings VI : wings and nacelles with pusher propeller
This report is the sixth of a series giving wind tunnel tests results on the interference drag and propulsive efficiency of nacelle-propeller-wing combinations. The present report gives the results of tests of a radial-engine nacelle with pusher propeller in 17 positions with reference to a Clark Y wing; tests of the same nacelle and propeller in three positions with reference to a thick wing; and tests of a body and pusher propeller with the thick wing, simulating the case of a propeller driven by an extension shaft from an engine within the wing. Some preliminary tests were made on pusher nacelles alone. digital.library.unt.edu/ark:/67531/metadc66162/
Tests of N-85, N-86 and N-87 airfoil sections in the 11-inch high speed wind tunnel
Three airfoils, the N-85, the N-86, and the N-87, were tested at the request of the Bureau of Aeronautics, Navy Department, to determine the suitability of these sections for use as propeller-blade sections. Further tests of the NACA 0009-64 airfoil were also made to measure the aerodynamic effect of thickening the trailing edge in accordance with current propeller practice. The N-86 and the N-87 airfoils appear to be nearly equivalent aerodynamically and both are superior to the N-85 airfoil. Comparison of those airfoils with the previously developed NACA 2409-34 airfoils indicate that the NACA 2409-34 is superior, particularly at high speeds. Thickening the trailing edge appears to have a detrimental effect, although the effect may be small if the trailing-edge radius is less than 0.5 percent of the cord. The N-86 and the N-87 airfoils appear to be nearly equivalent. digital.library.unt.edu/ark:/67531/metadc54455/
Tests of oil scraper piston ring and piston fitted with oil drain holes
Tests were conducted to determine whether or not a properly located and properly designed oil scraper piston ring, installed on a piston provided with oil drain holes of sufficient area, would prevent the excessive oiling of the Liberty engine, particularly with the engine running at idling speed with full oil pressure. Results showed that excessive oiling was in fact prevented. It is strongly recommended that scraper rings and pistons be adopted for aircraft engines. digital.library.unt.edu/ark:/67531/metadc53754/
Tests of Permissible Explosives
No Description digital.library.unt.edu/ark:/67531/metadc12280/
Tests of propeller-speed cooling blowers
No Description digital.library.unt.edu/ark:/67531/metadc61979/
Tests of related forward-camber airfoils in the variable-density wind tunnel
A recent investigation of numerous related airfoils indicated that positions of camber forward of the usual location resulted in an increase of the maximum lift. As an extension of this investigation, a series of forward-camber airfoils has been developed, the members of which show airfoil characteristics superior to those of the airfoils previously investigated. The primary object of this report is to present fully corrected results for airfoils in the useful range of shapes. With the data thus made available, an airplane designer may intelligently choose the best possible airfoil-section shape for a given application and may predict to a reasonable degree the aerodynamic characteristics to be expected in flight from the section shape chosen. digital.library.unt.edu/ark:/67531/metadc66268/
Tests of ring-stiffened circular cylinders subjected to a transverse shear load
Thirty-four circular cylinders stiffened by heavy rings were loaded to failure in combined bending and shear with a transverse shear load. The results are presented in the form of an interaction curve which is applicable to the design of ring-stiffened cylinders that fail as a result of local buckling. (author). digital.library.unt.edu/ark:/67531/metadc57404/
Tests of Rock-Dust Barriers in the Experimental Mine
No Description digital.library.unt.edu/ark:/67531/metadc12523/
Tests of rotating cylinders
Tests were made in the no. 1 wind tunnel at Langley Memorial Aeronautical Laboratory to determine the air forces acting on rotating cylinders with axes perpendicular to the direction of motion. One cylinder had a circular cross-section, the other that of a greek cross. digital.library.unt.edu/ark:/67531/metadc53882/
Tests of round and flat spoilers on a tapered wing in the NACA 19-foot pressure wind tunnel
Several arrangements of round and flat spanwise spoilers attached to the upper surface of a tapered wing were tested in the NACA 19-foot pressure wind tunnel to determine the most effective type, location, and size of spoiler necessary to reduce greatly the lift on the wings of large flying boats when moored. The effect of the various spoilers on the lift, the drag, and the pitching-moment characteristics of the tapered wing was measured over a range of angles of attack from zero to maximum lift. The most effective type of spoiler was found to be the flat type with no space between it and the wing surface. The chordwise location of such a spoiler was not critical within the range investigated, from 5 to 20 percent of the wing chord from the leading edge. digital.library.unt.edu/ark:/67531/metadc53666/
Tests of Run-of-Mine and Briquetted Coal in a Locomotive Boiler
No Description digital.library.unt.edu/ark:/67531/metadc12250/
Tests of several bearing materials lubricated by gasoline
This investigation on the relative wear of several bearing materials lubricated by gasoline was conducted at the Langley Memorial Aeronautical Laboratory, as part of a general research on fuel injection engines for aircraft. The specific purpose of the work was to find a durable bearing material for gear pumps to be used for the delivery of gasoline and diesel engine fuel oil at moderate pressures to the high pressure pumps of fuel injection engines. digital.library.unt.edu/ark:/67531/metadc53935/
Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing
No Description digital.library.unt.edu/ark:/67531/metadc62110/
Tests of Several Model Nacelle-Propeller Arrangements in Front of a Wing
An investigation was conducted in the N.A.C.A. 20-foot wind tunnel to determine the drag, the propulsive and net efficiencies, and the cooling characteristics of severa1 scale-model arrangements of air-cooled radial-engine nacelles and present-day propellers in front of an 18- percent-thick, 5- by 15-foot airfoil. This report deals with an investigation of wing-nacelle arrangements simulating the geometric proportions of airplanes in the 40,000- to 70,000- pound weight classification and having the nacelles located in the vicinity of the optimum location determined from the earlier tests. digital.library.unt.edu/ark:/67531/metadc65031/
Tests of six symmetrical airfoils in the variable density wind tunnel
This paper is the first of a series covering an investigation of a family of airfoils all formed from a basic profile. It gives in preliminary form the results of six symmetrical airfoils, differing only in maximum thickness. The maximum thickness-to-chord ratios are 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. digital.library.unt.edu/ark:/67531/metadc54117/
Tests of spheres with reference to Reynolds number, turbulence, and surface roughness
The behavior of the Reynolds Number of the sphere is explained (in known manner) with the aid of the boundary-layer theory. Rear spindles may falsify, under certain conditions, the supercritical sphere drag, while suspension wires in the space behind the sphere leave no traceable influence. The critical Reynolds Number of the sphere was arrived at by an unconventional method; that is, by determining the critical wind speed at which the static pressure at the back of the sphere is the same as that of the undisturbed flow. The method makes it possible to interpret the critical Reynolds Number with only one test station. digital.library.unt.edu/ark:/67531/metadc63443/
Tests of Strength of Roof Supports Used in Anthracite Mines of Pennsylvania
No Description digital.library.unt.edu/ark:/67531/metadc12476/
Tests of submerged duct installation on a modified airplane in the Ames 40- by 80-foot wind tunnel
No Description digital.library.unt.edu/ark:/67531/metadc58156/
Tests of Submerged Duct Installation on the Ryan FR-1 Airplane in the Ames 40- by 80-Foot Wind Tunnel
An investigation of an NACA submerged intake installation on the Ryan FR-1 was conducted to determine the full-scale aerodynamic characteristics of this installation. In addition, tests were conducted on the submerged inlet with revised entrance lips and deflectors to determine the configuration which would result in the best dynamic pressure recovery measured at the inlet for this installation without a major rework of the entrance. Stalling of the air flow over the inner lip surface created excessive dynamic pressure losses with the original entrance. The revised entrance produced a 12-percent increase in dynamic pressure recovery at the design high-speed inlet-velocity ratio and resulted in an improvement of thte critical-speed characteristics of the entrance lip. A complete redesign of the entrance including a decrease in ramp angle and adjustment of lip camber is necessary to secure optimum results from this submerged duct installation. digital.library.unt.edu/ark:/67531/metadc63768/
Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel
Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectively. digital.library.unt.edu/ark:/67531/metadc64264/
Tests of the AN/SPS-1 Radar Antenna in the Langley Full-Scale Tunnel
Tests have been conducted to determine the drive-motor torque and the static force and moment characteristics of the AN/SPS-1 radar antenna. Shifting the longitudinal position of the antenna had very little effect on the drive-motor torque, which reached a maximum value expressed in terms of dynamic pressure (T/q)(sub max) of 1.15 at an azimuth angle of 245 deg. The maximum observed values of rolling, pitching, and yawing moments in terms of dynamic pressure are -29.0, 66.6, and 13.4, respectively. digital.library.unt.edu/ark:/67531/metadc64604/
Tests of the Anthratube
Report issued by the U.S. Bureau of Mines on the equipment testing of the Anthratube. The report follows the methods used and the results gained from testing the Anthratube. This report includes tables of data, as well as illustrations and photographs of equipment tested. digital.library.unt.edu/ark:/67531/metadc38592/
Tests of the Daimler D-IVa engine at a high altitude test bench
Reports of tests of a Daimler IVa engine at the test-bench at Friedrichshafen, show that the decrease of power of that engine, at high altitudes, was established, and that the manner of its working when air is supplied at a certain pressure was explained. These tests were preparatory to the installation of compressors in giant aircraft for the purpose of maintaining constant power at high altitudes. digital.library.unt.edu/ark:/67531/metadc53701/
Tests of the jet-motor air-intake duct system on a 1/4-scale stub-wing model of a pursuit-type airplane
No Description digital.library.unt.edu/ark:/67531/metadc62023/
Tests of the landing on water of a model of a high-speed airplane - Langley tank model 229
No Description digital.library.unt.edu/ark:/67531/metadc58102/
Tests of the landing on water of a model of a high-speed airplane - langley tank model 229
No Description digital.library.unt.edu/ark:/67531/metadc53125/
Tests of the N.P.L. airship models in the variable density wind tunnel
No Description digital.library.unt.edu/ark:/67531/metadc59648/
Tests of the NACA 0010-1.50 40/1.051 airfoil section at high subsonic Mach numbers
No Description digital.library.unt.edu/ark:/67531/metadc59614/
Tests of the NACA 0025 and 0035 airfoils in the full-scale wind tunnel
This report presents the results of an investigation conducted in the NACA full-scale wind tunnel to determine the aerodynamic characteristics of the 6 by 36-foot rectangular NACA 0025 and 0035 airfoils. The aerodynamic characteristics of the plain airfoils with rounded and square tips were determined by force tests through a complete angle-of-attack range, in addition, the profile drag was determined by the momentum method. The transition points on the airfoils were located by boundary-layer determinations with small total-head and static tubes. Each airfoil was also tested with a 0.20c full-span split flap. Tuft surveys were included to show the progressive breakdown of flow with increasing angles of attack. Previously published data from tests of the NACA 0009, 0012, and 0018 airfoils in the full-scale tunnel have been included in the summary curves. digital.library.unt.edu/ark:/67531/metadc66369/
Tests of the NACA 64-010 and 64A010 airfoil sections at high subsonic Mach numbers
No Description digital.library.unt.edu/ark:/67531/metadc58363/
Tests of the NACA 64(sub 1)-012 and 64(sub 1)A012 airfoils at high subsonic Mach numbers
No Description digital.library.unt.edu/ark:/67531/metadc57760/
Tests of the NACA 64(SUB 1)A212 airfoil section with a slat, a double slotted flap, and boundary-layer control by suction
No Description digital.library.unt.edu/ark:/67531/metadc55224/
Tests of the NACA 653-018 airfoil section with boundary-layer control by suction
No Description digital.library.unt.edu/ark:/67531/metadc61409/
Tests of the Northrop MX-334 glider airplane in the NACA full-scale tunnel
No Description digital.library.unt.edu/ark:/67531/metadc62631/
Tests of the Northrop XB-62 missile in the Ames 40 by 80 foot wind tunnel
No Description digital.library.unt.edu/ark:/67531/metadc53262/
Tests of the Northrop XSSM-A-3 Missile in the Ames 40- by 80-Foot Wind Tunnel: Wing Modifications
Wind-tunnel tests were conducted to determine the longitudinal stability characteristics of a full-scale Northrop XSSM-A-3 missile. Various wing modifications were investigated in an effort to provide a configuration that would maintain longitudinal stability to lift coefficients necessary for landing the missile during flight tests. The results of the tests led to the choice of a wing with an increased leading-edge radius. A short discussion of the results is presented, but no analysis of the data has been made in order to make the data available as soon as possible. digital.library.unt.edu/ark:/67531/metadc64104/
Tests of Thermal-Electric De-Icing Equipment for Propellers
Flights were made in natural icing conditions at the NACA Ice Research Project, Minneapolis, Minn. to test several designs of thermal-electric propeller de-icing blade shoes and a hub-generator design. It was found that a minimum average unit power of 2.5 watts per square inch of blade-shoe area would protect the propeller blades at the test conditions. The most satisfactory blade shoe of the three designs tested extended to the 20-percent-chord point and to 90 percent of the blade radius. A concentration of heat in the leading-edge region of this shoe was found to reduce the power input necessary for satisfactory de-icing. A satisfactory thermal design of blade shoe and a hub generator of sufficient capacity were developed. digital.library.unt.edu/ark:/67531/metadc61822/
Tests of three tapered airfoils based on the N.A.C.A. 2200, the N.A.C.A.-M6, and the Clark Y sections
Three tapered airfoils based on the N.A.C.A. 2200, the N.A.C.A.-M6, and the Clark Y sections were tested in the variable-density wind tunnel at a Reynolds Number of approximately 3,100,000. The models, which were of aspect ratio 6, had constant core center sections and rounded tips, and tapered in thickness from 18 percent at the roots to 9 percent at the tips. The aerodynamic characteristics are given by the usual dimensionless coefficients plotted for both positive and negative angles of attack and by effective profile-drag coefficients plotted against lift coefficients. digital.library.unt.edu/ark:/67531/metadc54379/
Tests of Two-Blade Propellers in the Langley 8-Foot High-Speed Tunnel to Determine the Effect on Propeller Performance of a Modification of Inboard Pitch Distribution
Tests of two propellers having two blades and differing only in the inboard pitch distribution were made in the Langley 8-foot highspeed tunnel to determine the effect of inboard pitch distribution on propeller performance. propeller was designed for operation in the reduced velocity region ahead of an NACA cowling; the inboard pitch distribution of the modified propeller was increased for operation at or near free-stream velocities, such as would be obtained in a pusher installation. conditions covering climb, cruise, and high-speed operation. Wake surveys were taken behind the propellers in order to determine the distribution of thrust along the blades and to aid in the analysis of the results. Test results showed that the modified propeller was about 2.5 percent less efficient for a typical climb condition at all altitudes, 2 percent more efficient for one cruise condition, and 5 percent more efficient for high-speed operation. speed condition, the modified propeller showed a 6-percent loss in efficiency due to compressibility; whereas the original propeller showed an 11-percent efficiency loss due to compressiblity. The lower compressibility loss for the modified propeller resulted from the fact that the inboard sections of this propeller could operate at increased thrust loading after compressibility losses had occurred at the outboard sections. digital.library.unt.edu/ark:/67531/metadc55644/
Tests of two full-scale propellers with different pitch distributions, at blade angles up to 60 degrees
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 design speeds up to 500 miles per hour, were investigated. Propeller blade angles at 0.75r from 15 degrees to 60 degrees, corresponding to design speeds up to 500 miles per hour, were investigated. The results indicated that the propulsive efficiency at a blade angle of 60 degrees was about 9 percent less than the maximum value of 86 percent, which occurred at blade angle of about 30 degrees. The efficiency at a blade angle of 60 degrees was increased about 7 percent by correcting for the effect of a spinner and, at a blade angle of 30 degrees about 3 percent. The peak efficiencies for the propeller having the washed-out pitch distribution were slightly less than for the normal propeller but the take-off efficiency was generally higher. digital.library.unt.edu/ark:/67531/metadc66316/
Tests of two models representing intermediate inboard and outboard wing sections of the XB-36 airplane
No Description digital.library.unt.edu/ark:/67531/metadc61355/
Tests of Wing Machine-Gun and Cannon Installations in the NACA Full-Scale Wind Tunnel, Special Report
At the request of the Bureau of Aeronautics, an investigation was conducted in the full-scale wind tunnel of wing installations of .50-caliber machine guns and 20-millimeter cannons. The tests were made to determine the effect of various gun installations on the maximum lift and the high-speed drag of the airplane. digital.library.unt.edu/ark:/67531/metadc65183/
Tests on a model of the D.F.W. airplane T-29 of the "Deutsche Flugzeug derke" (German airplane works)
Experiments similar to those carried out with the A.E.G (Allgemeine Elektrizitats-Gesellschaft) were made in the small wind tunnel of the Gottingen laboratory on a model of the D.F.W. airplane T-29. Three series of tests were carried out on the model with a velocity head (or dynamic pressure) of 5 kg/sq m (1.02 lb/sq ft), during which one of the movable surfaces was deflected at various angles, while both the others were retained in their central positions. Of special interest among the results of the tests is the different run of the elevating moments. The curves for the A.E.G. model, rising to the right, denote stability with the elevator locked, while the slight inclination to the left with the D.F.W model denotes a slight instability. For the maximum C(sub L) values, the stability of A.E.G. model continues to increase and the instability of the D.F.W. model is converted into stability. The rolling moments shown when the angular deflection of the ailerons is 0 degrees are due, in both series of tests, to the unequal distribution of the air velocity over the cross section of the wind tunnel, rather than to a lack of symmetry in the model. digital.library.unt.edu/ark:/67531/metadc53841/
Tests on air propellers in yaw
This report contains the results of tests to determine the thrust (pull) and torque characteristics of air propellers in movement relative to the air in a line oblique to the line of the shaft, and specifically when such angle of obliquity is large, as in the case of helicopter flight with the propeller serving for both sustentation and traction. digital.library.unt.edu/ark:/67531/metadc65763/