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Two-dimensional subsonic compressible flows past arbitrary bodies by the variational method
Instead of solving the nonlinear differential equation which governs the compressible flow, an approximate method of solution by means of the variational method is used. The general problem of steady irrotational flow past an arbitrary body is formulated. Two examples were carried out, namely, the flow past a circular cylinder and the flow past a thin curved surface. The variational method yields results of velocity and pressure distributions which compare excellently with those found by existing methods. These results indicate that the variational method will yield good approximate solution for flow past both thick and thin bodies at both high and low Mach numbers.
Date:
March 1951
Creator:
Wang, Chi-Teh
System:
The UNT Digital Library
The Variation in Pressure in the Cabin of an Airplane in Flight
From Summary: "The pressure in the cabin of a Fairchild cabin monoplane was surveyed in flight, and was found to decrease with increased air speed over the fuselage and to vary with the number and location of openings in the cabin. The maximum depression of 2.2 inches of water (equivalent pressure altitude at sea level of 152 feet) occurred at the high speed of the airplane in level flight with the cabin closed."
Date:
March 1931
Creator:
Gough, Melvin N.
System:
The UNT Digital Library
Turbulent-heat-transfer measurements at a Mach number of 2.06
Report presenting turbulent-heat-transfer measurements obtained through the use of an axially symmetric annual nozzle consisting of an inner shaped center body and an outer cylindrical sleeve at Mach number 2.06. Results regarding the variation of wall temperature with longitudinal distance, variation of local Nusselt number with local Reynolds number, and variation of local temperature-recovery factor with local Reynolds number are provided.
Date:
March 1955
Creator:
Brevoort, Maurice J. & Rashis, Bernard
System:
The UNT Digital Library
A theory for predicting the flow of real gases in shock tubes with experimental verification
Report presenting the nonlinear characteristic differential equations applicable to a quasi-one-dimensional unsteady channel flow with friction and heat transfer, which are linearized and integrated in functional form for the particular study of small perturbations from ideal shock-tube flows.
Date:
March 1955
Creator:
Trimpi, Robert L. & Cohen, Nathaniel B.
System:
The UNT Digital Library
An investigation at low speed of the flow over a simulated flat plate at small angles of attack using pitot-static and hot-wire probes
Report presenting results from pitot-static and hot-wire anemometer surveys at low speed of the flow over a thin, sharp-edge airfoil which simulated a flat plate. The primary purpose was to obtain detailed measurements of the flow associated with the so-called thin-airfoil type of stall. Results regarding the preliminary tests, pressure distributions, mean flow measurements, velocity fluctuation measurements, and observations and measurements of the flow in the immediate vicinity of the leading edge are provided.
Date:
March 1957
Creator:
Gault, Donald E.
System:
The UNT Digital Library
Study of Effects of Microstructure and Anisotropy on Fatigue of 23S-T4 Aluminum Alloy
Note presenting a study of the effects of variation in microstructure on the fatigue properties of 24S-T4 aluminum-alloy notched specimens tested in both longitudinal and transverse directions. The results show that a definite anisotrophy exists in the fatigue strength of this alloy in tests. However, the results also indicate that a sample size of 10 specimens does not give statistically reproducible results in all cases.
Date:
March 1955
Creator:
Lipsitt, H. A.; Dieter, G. E.; Horne, G. T. & Mehl, R. F.
System:
The UNT Digital Library
Investigation of the planing lift of a flat plate at speeds up to 170 feet per second
Report presenting an investigation in the high-speed hydrodynamics facility to determine whether planing lift coefficient of a flat-bottom planing surface remains constant with increasing speed at the high towing speeds obtainable. The generally accepted assumption that there is no effect of speed on the lift coefficient of positive-pressure lifting surfaces is valid at least up to 170 fps.
Date:
March 1957
Creator:
Christopher, Kenneth W.
System:
The UNT Digital Library
Preliminary Data at a Mach Number of 2.40 of the Characteristics of Flap-Type Controls Equipped With Plain Overhang Balances
Report presenting an investigation at Mach number 2.40 to determine the aerodynamic characteristics of plain overhang balances on flap-type controls. Testing was performed on a two-dimensional wing with three trailing-edge flaps with balance lengths of 38, 60, and 82 percent of the flap chord. The effect of wing-flap gap size were investigated for the flap with 38 percent balance.
Date:
March 1957
Creator:
Mueller, James N. & Czarnecki, K. R.
System:
The UNT Digital Library
Experimental Investigation of the Oscillating Forces and Moments on a Two-Dimensional Wing Equipped With an Oscillating Circular-Arc Spoiler
Report presenting an experimental investigation in the flutter research tunnel on the oscillating forces and moments on a two-dimensional wing equipped with an oscillating circular-arc spoiler.
Date:
March 1957
Creator:
Clevenson, Sherman A. & Tomassoni, John E.
System:
The UNT Digital Library
Flight measurements of the velocity distribution and persistence of the trailing vortices of an airplane
Report regarding the measurement of velocity distribution and persistence of the trailing vortices of a propeller-driven fighter-type airplane. Vortex strength did not decrease appreciably up to 35 seconds after the vortices had been shed. When flying in the trailing wake of another airplane, the pilot reported that it was difficult to maintain a precise course and that the disturbance was similar to severe turbulence.
Date:
March 1955
Creator:
Kraft, Christopher C., Jr.
System:
The UNT Digital Library
The erosion of meteors and high-speed vehicles in the upper atmosphere
From Summary: "A simple inelastic collision model of meteor-atmosphere interaction is used and analytic relations for velocity, deceleration, size, and relative luminous magnitude of meteors are derived and expressed in dimensionless parametric form. The analysis is compared with available quantitative observations of meteor behavior and it is indicated that a large fraction of the atmospheric bombardment energy is used in eroding meteor material. The erosion from large, high-speed vehicles as they traverse the high-altitude, free-molecule portion of the atmosphere is calculated, on the assumption that the vaporization process is similar to that which occurs for meteors."
Date:
March 1957
Creator:
Hansen, C. Frederick
System:
The UNT Digital Library
Effect of Wall Cooling on Inlet Parameters of a Scoop Operating in a Turbulent Boundary Layer on a Flat or Conical Surface for Mach Numbers 2 to 10
Note presenting analytical results obtained for boundary-layer mass flow, momentum, total-temperature, and total-pressure recovery ratios of a scoop inlet with a height equal to the boundary-layer thickness and operating in a turbulent boundary layer, for flat and conical surfaces with wall cooling. The results indicate that design of boundary-layer intake devices or diverters must reflect the effects of wall cooling by either variable or compromised size.
Date:
March 1958
Creator:
Beke, Andrew
System:
The UNT Digital Library
An Investigation of High-Temperature Vacuum and Hydrogen Furnace Brazing
Note presenting an investigation of the vacuum and hydrogen brazing of four heat-resistant alloys with two types of high-temperature brazing alloy. The effect of time at two brazing temperatures on the 1200 degrees Fahrenheit shear strength of joints and on the base-metal properties was studied. Shear specimens of all four base alloys brazed in hydrogen with box types of brazing alloy exhibited erratic joint coverage by the brazing alloys.
Date:
March 1957
Creator:
Russell, Walter E. & Wisner, John P.
System:
The UNT Digital Library
Effect of leading-edge geometry on boundary-layer transition at Mach 3.1
Report presenting the effect of leading-edge geometry on transition position, recovery-factor distribution, boundary-layer profile, and the roughness required to induce transition at Mach number 3.1 for a hollow cylinder aligned with the air stream. Results regarding leading-edge effect, roughness elements in laminary boundary layer, surface-heat condition effects, and effect of stream total temperature are provided.
Date:
March 1956
Creator:
Brinich, Paul F.
System:
The UNT Digital Library
Theoretical Loss Relations for Low-Speed Two-Dimensional-Cascade Flow
Note presenting a theoretical analysis of the relations between wake characteristics and total-pressure defect for the incompressible flow across a two-dimensional cascade of compressor blades. Results indicated that the total-pressure-loss coefficient for unseparated flow varied almost directly with the ratio of wake momentum thickness to blade chord length and with the solidity, and inversely with the cosine of the air outlet angle.
Date:
March 1956
Creator:
Lieblein, Seymour & Roudebush, William H.
System:
The UNT Digital Library
Flight tests of a model of a high-wing transport vertical-take-off airplane with tilting wing and propellers and with jet controls at the rear of the fuselage for pitch and yaw control
An investigation of the stability and control of a high-wing transport vertical-take-off airplane with four engines during constant-altitude transitions from hovering to normal forward flight was conducted with a remotely controlled free-flight model. The model had four propellers distributed along the wing with the thrust axes in the wing chord plane. The wing could be rotated to 90 degrees incidence so that the propeller thrust axes were vertical for hovering flight. An air jet at the rear of the fuselage provided pitch and yaw control for hovering and low-speed flight.
Date:
March 1957
Creator:
Lovell, Powell M., Jr. & Parlett, Lysle P.
System:
The UNT Digital Library
Calculations of the Effect of Wing Twist on the Air Forces Acting on a Monoplane Wing
"A method is presented for calculating the aerodynamic forces on a moncylane wing, taking into account the elastic twisting of the wing due to these forces. The lift distribution along the span is calculated by the formulas of Amstutz as a function of the geometrical characteristics of the wing and of the twist at stations 60 and 90 percent of the semispan. The twist for a given lift distribution is calculated by means of influence lines" (p. 1).
Date:
March 1935
Creator:
Dätwyler, G.
System:
The UNT Digital Library
A Study of the Impact Behavior of High-Temperature Materials
Note presenting the impact properties of titanium carbide base cermets, some high-temperature alloys, and the intermetallic NiAl, obtained at room and elevated temperatures up to 1750 degrees Fahrenheit. The impact energies of cermets were found to increase with increased amounts of metallic binder. Results regarding the variables of drop test, impact resistance of cermets, high-temperature alloys, and comparison of cermets and alloys are provided.
Date:
March 1957
Creator:
Probst, H. B. & McHenry, Howard T.
System:
The UNT Digital Library
A correlation of low-speed, airfoil-section stalling characteristics with Reynolds number and airfoil geometry
From Summary: "The low-speed stalling characteristics of a large number of airfoil sections have been correlated with Reynolds number and a single airfoil ordinate near the leading edge as the correlation parameters. The correlation is appropriate only to airfoils without high-lift devices in flows of very low turbulence and with aerodynamically smooth surfaces."
Date:
March 1957
Creator:
Gault, Donald E.
System:
The UNT Digital Library
Measurements of Lift Fluctuations Due to Turbulence
Note presenting a study of the fluctuating lift of a rigid wing in turbulent flow and the power spectra of the lift and turbulent fluctuations. Using these measurements, the aerodynamic admittance of the wing was obtained. Results regarding the infinite wing and aspect-ratio effect are provided.
Date:
March 1957
Creator:
Lamson, P.
System:
The UNT Digital Library
Investigation of separated flows in supersonic and subsonic streams with emphasis on the effect of transition
Report presenting experimental and theoretical research on flow separation associated with steps, bases, compression corners, curved surfaces, shock-wave boundary-layer reflections, and configurations producing leading-edge separation. Results were obtained from pressure-distribution measurements, shadowgraph observations, high-speed motion pictures, and oil-film studies.
Date:
March 1957
Creator:
Chapman, Dean R.; Kuehn, Donald M. & Larson, Howard K.
System:
The UNT Digital Library
Analysis of stresses and deflections in a disk subjected to gyroscopic forces
From Summary: "Results are presented in dimensionless form suitable for design purposes. The method for solving the problem of a disk of variable thickness with a temperature gradient is also presented."
Date:
March 1958
Creator:
Hirschberg, M. H. & Mendelson, A.
System:
The UNT Digital Library
Propellant vaporization as a criterion for rocket engine design; Relation between percentage of propellant vaporized and engine performance
Report presenting an anakysis of the quantitative effect of incomplete propellant vaporization on rocket-engine performance. Results regarding the effect of incomplete vaporization on engine performance and an interpretation of experimental data are provided.
Date:
March 1958
Creator:
Heidmann, Marcus F. & Priem, Richard J.
System:
The UNT Digital Library
Drop-size distributions for impinging-jet breakup in airstreams simulating the velocity conditions in rocket combustors
Report presenting drop-size-distribution data obtained for heptane sprays produced by pairs of impinging jets in airstreams over ranges of orifice diameter, liquid-jet velocity, and velocity difference between the airstream and the liquid jet.
Date:
March 1958
Creator:
Ingebo, Robert D.
System:
The UNT Digital Library