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Theoretical investigation of the longitudinal response characteristics of a swept-wing fighter airplane having a pitch-attitude control system
Report presenting a theoretical analysis made of a pitch-attitude control system as applied to a swept-wing fighter airplane. The system is investigated with and without pitch-rate feedback. The effects of varying gain settings, Mach number, altitude, and variations of elevator deflection, normal acceleration, and flight path are provided.
Date:
January 1953
Creator:
Stokes, Fred H. & Matthews, J. T.
System:
The UNT Digital Library
Prediction of losses induced by angle of attack in cascades of sharp-nosed blades for incompressible and subsonic compressible flow
Report presenting a method of computing the losses in total pressure caused by a non-zero angle of attack at the inlet to a row of sharp-nosed blades for both incompressible and subsonic compressible flow. The method is based on momentum considerations across a row of zero-thickness flat plates and assumes that the blade force is normal to the plate surface.
Date:
January 1955
Creator:
Kramer, James J. & Stanitz, John D.
System:
The UNT Digital Library
Analysis of Straight Multicell Wings on Cal-Tech Analog Computer
Note presenting structural analyses made for four straight multicell wings. Wings with aspect ratios of 2 and 4 with rectangular and biconvex cross sections have been considered. The results indicated that under bending loads, all of the wings show fairly good agreement with beam theory.
Date:
January 1954
Creator:
Benscoter, Stanley U. & MacNeal, Richard H.
System:
The UNT Digital Library
Physical characteristics and test conditions of an ethylene-heated high-temperature jet
Report presenting an investigation of the effects of high temperatures incurred at hypersonic speeds using an ethylene-heated high-temperature jet.
Date:
January 1958
Creator:
English, Roland D.; Spinak, Abraham & Helton, Eldred H.
System:
The UNT Digital Library
Span Load Distribution Resulting From Constant Vertical Acceleration for Thin Sweptback Tapered Wings With Streamwise Tips: Supersonic Leading and Trailing Edges
Note presenting equations for the span load distribution resulting from constant vertical acceleration derived for a series of thin sweptback tapered wings with streamwise tips on the basis of the linearized supersonic-flow theory. The analysis is valid at Mach numbers for which the wing leading and trailing edges are supersonic.
Date:
January 1954
Creator:
Cole, Isabella J. & Margolis, Kenneth
System:
The UNT Digital Library
Some effects of aspect ratio and tail length on the contribution of a vertical tail to unsteady lateral damping and directional stability of a model oscillating continuously in yaw
Report presenting a fuselage-vertical-tail combination with tails of two aspect ratios, each of which was tested at four tail lengths, and oscillated in yaw through a range of reduced-frequency parameter corresponding to the lateral motions of airplanes. Three phase angles were measured with the tail in the presence of the fuselage.
Date:
January 1954
Creator:
Fisher, Lewis R.
System:
The UNT Digital Library
Experimental investigation at a Mach number of 2.41 of average skin-friction coefficients and velocity profiles for laminar and turbulent boundary layers and an assessment of probe effects
Report presenting an experimental investigation of laminar and turbulent boundary layers on the outer surface of a hollow cylinder at Mach number 2.41 and a range of Reynolds numbers. Results regarding static-pressure distribution, Schileren observations, velocity profiles, boundary-layer transition, determination of effective leading edge for turbulent flow, skin friction, and probe effect are provided.
Date:
January 1954
Creator:
O'Donnell, Robert M.
System:
The UNT Digital Library
Effect of Various Arrangements of Triangular Ledges on the Performance of a 23 Degree Conical Diffuser at Subsonic Mach Numbers
Note presenting an investigation to determine whether the use of annular ledges to promote turbulent momentum exchange will improve the performance of a short, wide-angle diffuser. Results are presented of tests of a 23 degree conical diffuser with a 2:1 ratio of exit to inlet area with both rough and smooth triangular ledges, approximately one-tenth of the inlet boundary-layer thickness in height, installed in succession from the inlet to the exit. Results regarding rough ledges, comparison between smooth and rough ledges, and effect of changing the height of the smooth ledge are provided.
Date:
January 1954
Creator:
Persh, Jerome & Bailey, Bruce M.
System:
The UNT Digital Library
A Method for Estimating the Effect of Turbulent Velocity Fluctuations in the Boundary Layer on Diffuser Total-Pressure-Loss Measurements
Note presenting a method for estimating the effect of turbulent velocity fluctuations on diffuser total-pressure-loss measurements. When the longitudinal velocity fluctuations are large, as evidenced by discrepancies between the inlet and exit weight flows, the method compensates for the discrepancies by adjusting the boundary-layer profile.
Date:
January 1954
Creator:
Persh, Jerome & Bailey, Bruce M.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Effect of Sweep on Rolling Derivatives at Angles of Attack up to 13 Degrees and at High Subsonic Mach Numbers, Including a Semiempirical Method of Estimating the Rolling Derivatives
Note presenting an investigation performed in the high-speed 7- by 10-foot tunnel to determine the rolling derivatives for swept wing-body configurations at angles of attack from 0 to 13 degrees and at high subsonic Mach numbers. Results regarding experimental rolling derivatives and estimations of rolling derivatives are provided.
Date:
January 1958
Creator:
Wiggins, James W.
System:
The UNT Digital Library
Method for rapid graphical evaluation of cooled or uncooled turbojet and turboprop engine or component performance (effects of variable specific heat included)
Report presenting a series of curves that have been prepared to simplifying and accelerate calculation procedures for component or overall cycle performance of gas-turbine engines. The curves are based on the thermodynamic properties of air and combustion gases for a hydrogen-combustion ratio of 0.167.
Date:
January 1955
Creator:
Esgar, Jack B. & Ziemer, Robert R.
System:
The UNT Digital Library
Investigation of temperature limitation of various lubricants for high-temperature 20-millimeter-bore ball bearings
Report presenting lubrication studies of bearings lubricated with liquids and solids in a bearing test rig under conditions of minimum lubricant flow. Six liquid lubricants were investigated, including two petroleums and four synthetics. Results regarding bearings with silver-plated beryllium copper cages, bearings with cast Inconel cages, and an analysis of experimental results are provided.
Date:
January 1955
Creator:
Nemeth, Z. N. & Anderson, W. J.
System:
The UNT Digital Library
Analysis of Laminar Forced-Convection Heat Transfer in Entrance Region of Flat Rectangular Ducts
From Introduction: "Beyond the position where the boundary layer treatment can no longer be used, curves have been faired to connect the Nusselt number results of the present analysis with those of reference 3, in which a parabolic velocity profile is assumed throughout the entire duct length. So that a comparison could be made with the results of reference 3, the boundary layer analysis was used to study the development of the temperature profile associated with a parabolic velocity profile throughout."
Date:
January 1955
Creator:
Sparrow, E. M.
System:
The UNT Digital Library
Shape of Initial Portion of Boundary of Supersonic Axisymmetric Free Jets at Large Jet Pressure Ratios
"Calculations have been made of the initial portion of the boundary of axisymmetric free jets exhausting at large pressure ratios from a conically divergent nozzle having a jet exit Mach number of 2.5 and a semidivergence angle of 15 degrees. The results of the calculations indicate the size and shape of the jet to be expected at large pressure ratios, the effects of ratio of specific heats, and the large initial inclinations of the boundary that are likely to be encountered by hypersonic vehicles at high altitude" (p. 1).
Date:
January 1958
Creator:
Love, Eugene S. & Lee, Louise P.
System:
The UNT Digital Library
The Ames 10- by 14-Inch Supersonic Wind Tunnel
"The purpose of the present report is to describe the 10- by 14-inch supersonic wind tunnel and its operational characteristics over the nominal Mach number range from 2.7 to 6.3. Rather complete calibration data on characteristics of flow in the test section are presented and briefly discussed" (p. 2).
Date:
January 1954
Creator:
Eggers, A. J., Jr. & Nothwang, George J.
System:
The UNT Digital Library
Data on the compressive strength of skin-stringer panels of various materials
"Flat skin-stringer compression panels of stainless steel, mild steel, titanium, copper, four aluminum alloys, and a magnesium alloy were tested. The results show the effect of variations in yield stress, Young's modulus, and both yield stress and Young's modulus for constant yield strain on the average stress at maximum load, on the stress for local buckling, and on the load-shortening characteristics of the panels" (p. 1).
Date:
January 1954
Creator:
Dow, Norris F.; Hickman, William A. & Rosen, B. Walter
System:
The UNT Digital Library
Noise survey under static conditions of a turbine-driven full-scale modified supersonic propeller with an advance ratio of 3.2
Report presenting overall sound-pressure levels and frequency spectra under static conditions from a modified supersonic propeller designed to operate efficiently at a high forward speed without the high noise levels associated with the supersonic propeller. The three-blade, 10-foot-diameter, 1700-rpm propeller is powered by a turbine engine and is designed to operate at a Mach number of 0.95 at 40,000 feet.
Date:
January 1958
Creator:
Kurbjun, Max C.
System:
The UNT Digital Library
Effects of Airplane Flexibility on Wing Strains in Rough Air at 35,000 Feet as Determined by a Flight Investigation of a Large Swept-Wing Airplane
A flight investigation was made on a large sweptback-wing bomber airplane and the results are compared with data previously obtained at low altitude (5,000 feet). The effects of wing flexibility on the wing strains were, on the average, about 20 percent larger at the higher altitude.
Date:
January 1958
Creator:
Rhyne, Richard H.
System:
The UNT Digital Library
Fatigue Behavior of Aircraft Structural Beams
Report presenting an investigation of the correlation of composite structural fatigue behavior, basic material, and simple-element behavior. Fatigue and static testing were made on aluminum-alloy box beams and I-beams and on elements simulating key failure locations in the two beams.
Date:
January 1958
Creator:
Hyler, W. S.; Popp, H. G.; Gideon, D. N.; Gordon, S. A. & Grover, H. J.
System:
The UNT Digital Library
Reflection of Weak Shock Wave From a Boundary Layer Along a Flat Plate 2: Interaction of Oblique Shock Wave With a Laminar Boundary Layer Analyzed by Differential-Equation Method
Note presenting an investigation of the interaction of an oblique shock with a laminar boundary layer in a compressible supersonic stream. This report is a complement to previous report and uses the differential equation method.
Date:
January 1953
Creator:
Kuo, Yung-Huai
System:
The UNT Digital Library
Power-off flare-up tests of a model helicopter rotor in vertical autorotation
Report presenting the results of an experimental investigation of the problem of reducing the descending velocity of a helicopter model in steady vertical autorotation by expending the kinetic energy of the rotor in a collective-pitch flare. Test data were obtained over a wide range of operating conditions from a freely falling model rotor restrained laterally by a guide wire. Results regarding justification of initial conditions, effect or rate of change of blade pitch angle, effect of final blade pitch angle, effect of rotor inertia and disk loading, and semiempirical theory are provided.
Date:
January 1953
Creator:
Slaymaker, S. E. & Gray, Robin B.
System:
The UNT Digital Library
Effect of Surface Roughness Over the Downstream Region of a 23 Degree Conical Diffuser
Note presenting an experimental investigation conducted to determine the effects of varying extents of surface roughness over the downstream region of a 23 degree conical diffuser with an inlet-boundary-layer thickness of the order of 5 percent of the inlet diameter. The air flows used in the investigation cover an inlet Mach number range from about 0.10 to 0.40. The results indicate that the flow in the roughened diffuser was steady and reproducible for all conditions.
Date:
January 1954
Creator:
Persh, Jerome & Bailey, Bruce M.
System:
The UNT Digital Library
A Photographic Method for Determining Vertical Velocities of Aircraft Immediately Prior to Landing
"A photographic method employing a long-focal-length (40-inch) lens for obtaining statistical data on vertical velocities of aircraft immediately prior to landing contact developed for use with land-based airplanes is described. It requires no instrument installation on the aircraft or interference with airport operation and employs relatively simple data reduction. Vertical velocities can be obtained by this method within a probable maximum error of 0.31 fps" (p. 1).
Date:
January 1954
Creator:
Rind, Emanuel
System:
The UNT Digital Library
Effect of temperature on rolling-contact fatigue life with liquid and dry powder lubricants
Report presenting an investigation of the effect of temperature using di(2-ethylhexyl) sebacate lubricant and dry powder lubricants on rolling-contact fatigue life on AISI M-1 tool-steel balls in the rolling-contact fatigue spin rig at maximum theoretical Hertz stress levels of 650,000 and 725,000 pounds per square inch in compression.
Date:
January 1958
Creator:
Carter, Thomas L.
System:
The UNT Digital Library