Collection
Technical Report Archive and Image Library
431
National Advisory Committee for Aeronautics Collection
366
Texas Attorney General Opinions
258
Office of Scientific & Technical Information Technical Reports
93
TRAIL Microcard Collection
44
World War Two Collection
24
Government Documents A to Z Digitization Project
23
World War Two Newsmaps
18
Texas State Publications
15
USDA Farmers' Bulletins
4
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Column and plate compressive strengths of aircraft structural materials: extruded 75S-T aluminum alloy
Report presenting column and plate compressive strengths of extruded 75S-T aluminum alloy both within and beyond the elastic range from tests of thin-strip columns and local-instability tests of H-, Z-, and channel-section columns. The tests are part of an extensive research investigation to provide data on the structural strength of various aircraft materials. Results regarding compressive stress-strain curves and column and plate compressive strengths are provided.
Date:
July 1945
Creator:
Heimerl, George J. & Roy, J. Albert
Object Type:
Report
System:
The UNT Digital Library
The biology and control of the sorghum midge.
Describes the life cycle of the sorghum midge, its history in the United States, the damage it can cause to plants, and the steps farmers can take to control the pest and its damage.
Date:
July 1941
Creator:
Walter, E. V. (Elmer Valentine), 1891-
Object Type:
Book
System:
The UNT Digital Library
Propeller analysis from experimental data
The operation of the propeller is analyzed by the use of the distribution of forces along the radius, combined with theoretical equations. The data were obtained in the NACA 20-foot wind tunnel on a 4-foot-diameter, two-blade propeller, operating in front of four body shapes, ranging from a small shaft to support the propeller to conventional NACA cowling. A method of estimating the axial and the rotational energy in the wake as a fractional part of the propeller power is given. A knowledge of the total thrust and torque is necessary for the estimation.
Date:
July 19, 1940
Creator:
Stickle, George W. & Crigler, John L.
Object Type:
Report
System:
The UNT Digital Library
A high-speed motion-picture study of normal combustion, knock and preignition in a spark-ignition engines
Combustion in a spark-ignition engine was investigated by means of the NACA high-speed motion-picture cameras. This camera is operated at a speed of 40,000 photographs a second and therefore makes possible the study of changes that take place in the intervals as short as 0.000025 second. When the motion pictures are projected at the normal speed of 16 frames a second, any rate of movement shown is slowed down 2500 times. Photographs are presented of normal combustion, of combustion from preignitions, and of knock both with and without preignition. The photographs of combustion show that knock may be preceded by a period of exothermic reaction in the end zone that persists for a time interval of as much as 0.0006 second. The knock takes place in 0.00005 second or less.
Date:
July 24, 1940
Creator:
Rothrock, A. M.; Spencer, R. C. & Miller, Cearcy D.
Object Type:
Report
System:
The UNT Digital Library
Investigation in Simulated Vertical Descent of the Characteristics of a Cargo-Dropping Device having Extensible Rotating Blades
The characteristics of a cargo-dropping device having extensible rotating blades as load-carrying surfaces have been studied in simulated vertical descent in the Langley 20-foot free-spinning tunnel. The investigation included tests to determine the variation in vertical sinking speed with load. A study of the blade characteristics and of the test results indicated a method of dynamically balancing the blades to permit proper functioning of the device.
Date:
July 1949
Creator:
Stone, Ralph W., Jr. & Hultz, Burton E.
Object Type:
Report
System:
The UNT Digital Library
Hydrodynamic Characteristics of an Aerodynamically Refined Planing-Tail Hull
The hydrodynamic characteristics of an aerodynamically refined planing-tail hull were determined from dynamic model tests in Langley tank no. 2. Stable take-off could be made for a wide range of locations of the center of gravity. The lower porpoising limit peak was high, but no upper limit was encountered. Resistance was high, being about the same as that of float seaplanes. A reasonable range of trims for stable landings was available only in the aft range of center-of-gravity locations.
Date:
July 16, 1948
Creator:
McKann, Robert & Suydam, Henry B.
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel. Part III - Longitudinal-Control Characteristics TED No. NACA DE308, Part 3, Longitudinal-Control Characteristics, TED No. NACA DE308
Tests have been conducted in the Langley high speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0,08-scale model of the Chance Vought XF7U-1 airplane. The longitudinal-control characteristics of the complete model are presented in the present report with a limited analysis of the results.
Date:
July 29, 1947
Creator:
Kuhn, Richard E. & King, Thomas J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Performance of J33-A-27 Turbojet-Engine Compressor 1: Over-all performance characteristics at equivalent impeller speeds from 6100 to 11,800 rpm
The J33-A-27 compressor was operated at an inlet pressure of 14 inches of mercury absolute and ambient inlet temperature over a range of equivalent impeller speeds from 6100 to 11,800 rpm. At the design equivalent speed of 11,800 rpm, the J33-A-27 compressor had a peak pressure ratio of 4.40 at an equivalent weight flow of 105.7 pounds per second and a peak adiabatic temperature-rise efficiency of 0.745. The maximum equivalent weight flow at design speed was 113.5 pounds per second.
Date:
July 11, 1949
Creator:
Kovach, Karl & Osborn, Walter M.
Object Type:
Report
System:
The UNT Digital Library
Altitude Performance of AN-F-58 Fuels in British Rolls-Royce Nene Single Combustor
"An investigation was conducted with a single combustor from a British Rolls-Royce Nene turbojet engine to determine the altitude performance characteristics of AN-F-58 fuels. Three fuel blends conforming to AN-F-58 specifications were prepared in order to determine the influence of fuel boiling temperatures and aromatic content on combustion efficiencies and altitude operational limits. The performance of the three AN-F-58 fuels was compared in the range of altitudes from sea level to 65,000 feet, engine speeds from 40- to 100- percent normal rated, and flight Mach numbers of 0.0 and 0.6" (p. 1).
Date:
July 8, 1949
Creator:
Cook, William P. & Koch, Richard G.
Object Type:
Report
System:
The UNT Digital Library
Flight Tests of a Curtiss No. 838-1C2-18 Three-Blade Propeller Having Trailing-Edge Extensions
"Flight tests to determine propeller performance have been made of a Curtiss No. 838-102-18 three-blade propeller having trailing-edge extensions on a Republic P-47D-28 airplane in climb and high speed. These tests are a part of a general propeller flight-test program at the Langley Laboratory of the National Advisory Committee for Aeronautics. Results of climb tests indicate that when power is changed from approximately 1475 horsepower at 2550 rpm (roughly normal power) to 2400 horsepower at 2700 rpm (approximately military power) there is a loss in propeller efficiency of 3 percent at an altitude of 7000 feet, and 4 percent at 21,000 feet" (p. 1).
Date:
July 16, 1947
Creator:
Gardner, John J.
Object Type:
Report
System:
The UNT Digital Library
A Time History of Control Operation of a C-54 Airplane in Blind Landing Approaches
"Tests were made with a C-54 airplane in which airline pilots made several blind approaches to determine whether any special flying techniques were used in blind landings and whether any special handling-qualities requirements would have to be formulated because of such special techniques. It was found that the airplane was flown at all times in the normal manner; that is, all turns were banked turns that were nearly coordinated by use of the rudder so that the sideslip was held close to zero. The pilot expended considerable physical work in continually moving the controls but this wake was due in part to the large friction in the three control systems" (p. 1).
Date:
July 18, 1947
Creator:
Talmage, Donald B.
Object Type:
Report
System:
The UNT Digital Library
Preliminary Results of a Free-Flight Investigation of the Static Stability and Aileron Control Characteristics of 1/6 Scale Models of the Bell MX-776
"An investigation of the static longitudinal stability, static directional stability, and aileron control characteristics at transonic and supersonic speeds is being made of 1/6 scale rocket-propelled model of the Bell MX-776. A stability investigation has been made of two symmetrical models with controls undeflected and centers of gravity one-half and one-body diameter, respectively, ahead of the equivalent design center-of-gravity location of the full-scale version. Both models developed large normal-force coefficients in both the subsonic and supersonic ranges which indicated longitudinal instability at low angles of attack" (p. 1).
Date:
July 1949
Creator:
Michal, David H. & Mitcham, Grady L.
Object Type:
Report
System:
The UNT Digital Library
The Design of Jet Pumps
This report shows that by applying both energy and impulse theorems the optimum throat dimension of the mixing nozzle and the best shape of intake can be predicted approximately in a relatively simple manner. The necessary length of the mixing nozzle follows from Prandtl's turbulent mixing theory. The calculations are carried out for the mixing of similar and dissimilar fluids.
Date:
July 1941
Creator:
Flügel, Gustav
Object Type:
Report
System:
The UNT Digital Library
New Method of Calculating the Power at Altitude of Aircraft Engines Equipped With Superchargers on the Basis of Tests Made Under Sea-Level Conditions
"The present article deals with what is considered to be a simpler and more accurate method of determining, from the results of bench tests under approved rating conditions, the power at altitude of a supercharged aircraft engine, without application of correction formulas. The method of calculating the characteristics at altitude, of supercharged engines, based on the consumption of air, is a more satisfactory and accurate procedure, especially at low boost pressures" (p. 1).
Date:
July 1941
Creator:
Sarracino, Marcello
Object Type:
Report
System:
The UNT Digital Library
Performance of J33-A-23 Turbojet-Engine Compressor, Part 1, Over-All Performance Characteristics of Compressor with 17-Blade Impeller
"The production-model 333-A-23 turbojet-engine compressor with a 17-blade impeller was operated at ambient and 0 F inlet temperatures and at inlet pressures of 14 and 5 inches mercury absolute for equivalent impeller speeds from 6000 to 12,750 rpm. The results of this investigation are compared with those of the 533-A-21 compressor. At the design equivalent speed of 11,750 rpm the maximum pressure ratio was 4.39" (p. 1).
Date:
July 20, 1948
Creator:
Beede, William L. & Kottas, Harry
Object Type:
Report
System:
The UNT Digital Library
An Investigation of the Aerodynamic Characteristics of an 0.08-Scale Model of the Chance Vought XF7U-1 Airplane in the Langley High-Speed 7- by 10-Foot Tunnel: Part II - Basic Lateral Stability Characteristics TED No. NACA DE308, Part 2, Basic Lateral Stability Charactistics, TED No. NACA DE308
Tests have been conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range from 0.40 to 0.91 to determine the stability and control characteristics of an 0.08-scale model of the Chance Vought XF7U-1 airplane. The basic lateral stability characteristics of the complete model with undeflected control surfaces are presented in the present report with a very limited analysis of the results.
Date:
July 18, 1947
Creator:
Kemp, William B., Jr.; Goodson, Kenneth W. & Kuhn, Richard E.
Object Type:
Report
System:
The UNT Digital Library
New Equipment for Testing the Fatigue Strength of Riveted and Welded Joints
"The mechanical and electrical construction of a new experimental instrument for fatigue testing riveted and welded joints is described. This experimental device has the advantage of being able to stress, even with comparatively low magnetic exciter force, structural components in alternate bending by resonance vibrations up to incipient fatigue failure (p .1)".
Date:
July 1940
Creator:
Müller, W.
Object Type:
Report
System:
The UNT Digital Library
Experimental Results With Airfoils Tested in the High-Speed Tunnel at Guidonia
The results are presented of a triple series of tests using force measurements, pressure-distribution measurements, and air flow photographs on airfoil sections suitably selected so that comparison could be made between the experimental and theoretical results. The comparison with existing theory is followed by a discussion of the divergences found, and an attempt is made to find their explanation.
Date:
July 1940
Creator:
Ferri, Antonio
Object Type:
Report
System:
The UNT Digital Library
Experiments on Ball and Roller Bearings Under Conditions of High Speed and Small Oil Supply
This report describes a testing machine on which 35 millimeter bearings (bore) can be run at speeds of the order of 21,000 rpm, while the following factors are recorded: 1) oil circulation through bearing and oil temperature. 2) maximum temperature of outer bearing ring, 3) radial and axial load on bearing, 4) radial, axial, and angular clearance of bearing, 5) power consumption of bearing. The experiments show that the lubrication was most reliable and oil consumption lowest when the oil was introduced through a hole in the outer or inner ring of the bearing.
Date:
July 1940
Creator:
Getzlaff, Günter
Object Type:
Report
System:
The UNT Digital Library
Integral Methods in the Theory of the Boundary Layer
From Summary: "The application of the well-known basic principle of mechanics, the principle of Jourdain, to problems of the theory of the boundary layer leads to an equation from which the equations of Von Karman, Leibenson, and Golubev are derived as special cases. The given equation may be employed in other integral methods. The present paper deals with the method of the variation of the thickness of the boundary layer. A number of new approximate formulas valuable in aerodynamic calculations for the friction distribution are derived from this procedure. The method has been applied only to laminar boundary layers, but it seems probable that it may be generalized to include turbulent layers as well."
Date:
July 1944
Creator:
Loitsianskii, L. G.
Object Type:
Report
System:
The UNT Digital Library
Diagrams for Calculation of Airfoil Lattices
"The field for curved blades is represented by a vortex series with a vortex removed at the blade point. Further, an example of calculation of a curved blade from this series is given, whereby the necessary accuracy required of the different methods in practice is shown according to the case considered" (p. 1).
Date:
July 1942
Creator:
Betz, Albert
Object Type:
Report
System:
The UNT Digital Library
Prediction of Downwash and Dynamic Pressure at the Tail From Free-Flight Measurements
"The present measurements form a continuation of earlier flight tests published in a previous report for predicting the downwash at the tail of an airplane. The method makes use of the tail itself as integrating contact surface to the extent that, beginning from the measurement of the self-alignment of the elevator, the mean downwash angle and dynamic pressure at the tail are determined. The instrumental accuracy is considerably improved if the elevator is completely separate from the controls during the tests, because the effect of friction on the self-alignment of the elevator is then reduced to a minimum and a finer elevator weight balance is rendered possible" (p. 1).
Date:
July 1942
Creator:
Eujen, E.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Flow in a Centrifugal Pump
"The investigation of the flow in a centrifugal pump indicated that the flow patterns in frictional fluid are fundamentally different from those in frictionless fluid. In particular, the dead air space adhering to the section side undoubtedly causes a reduction of the theoretically possible delivery head. The velocity distribution over a parallel circle is also subjected to a noticeable change as a result of the incomplete filling of the passages" (p. 1).
Date:
July 1946
Creator:
Fischer, Karl
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements of the Flying Qualities of a Lockheed P-80A Airplane (Army No. 44-85099): Longitudinal-Stability and -Control Characteristics
This report contains the flight-test results of the longitudinal-stability and -control phase of a general flying qualities investigation of the Lockheed P-80A airplane (Army No. 44-85099). The tests were conducted at indicated airspeeds up to 530 miles per hour (0.76 Mach number) at low altitude and up to 350 miles per hour (0.82) Mach number) at high altitude. These tests showed that the flying qualities of the airplane were in accordance with the requirements of the Army Air Forces Stability and Control Specification except for excessive elevator control forces in maneuvering flight and the inadequacy of the longitudinal trimming control at low airspeeds.
Date:
July 1, 1947
Creator:
Anderson, Seth B.; Christofferson, Frank E. & Clousing, Lawrence A.
Object Type:
Report
System:
The UNT Digital Library