The aeroelastic characteristics of the Saturn IB SA-203 launch vehicle
Aeroelastic properties, and effects of boundary layer-terminal shock wave interaction on Saturn IB SA-203 launch vehicle
AEROELASTICITY↗
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Results for “boundary effects”
Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Photoelastic analysis of prebuckling deformations of cylindrical shells.
Prebuckling deformation and stress-strain distributions in clamped thin cylindrical shell subjected to axial load, determining effect of boundary supports
AXIAL LOAD↗
Average pressure and skin friction on tapered plates in hypersonic flow.
Average pressure and skin friction on slender two- dimensional wings in hypersonic flow, taking into account displacement effects of boundary layer
SLENDER WING↗
On the solution of conical shells of linearly varying thickness subjected to lateral normal loads.
Asymptotic and particular solutions of conical shells subjected to lateral normal loads, discussing membrane forces, bending effects and boundary conditions for moments and shearing force
SHEARING STRESS↗
An experimental study of the influence of the turbulent boundary layer on panel flutter
Turbulent boundary layer effect on panel flutter
Gaspers, P. A., Jr.↗
Effect of hinge-line bleed on heat transfer and pressure distribution over a wedge-flap combination at Mach 10.4
Effect of boundary layer bleed on heat transfer and pressure distributions over wedge-flap surface at hypersonic speeds
Dearing, J. D.↗
An analysis of the ignition of slot-injected gaseous hydrogen in a supersonic air stream.
Initial air boundary layer effect on ignition of slot-injected gaseous hydrogen in supersonic airstream, discussing isotherm and streamline patterns
Favin, S.↗
Theoretical-experimental correlation of plate flutter boundaries at low supersonic speeds.
Thin flat plates flutter boundaries determination at supersonic speeds noting boundary layer effect
Dowell, E. H.↗
Aerodynamic forces of fluttering cylindrical and/or planar structures
Complexity of the phenomena of panel flutter instability has resulted in the necessity of developing separate design criteria for a variety of flow conditions and panel configurations. Vehicle panel configurations with low aspect ratios are of interest in low supersonic flow, where boundary layer effects are important.
Yates, J. E.↗
Effect of porous bleed in a high performance axisymmetric, mixed compression inlet at Mach 2.50
Effects of boundary layer bleed rate and location on performance of axisymmetric inlet designed for Mach 2.5
Cubbison, R. W.↗
Further experimental results on the influence of the turbulent boundary layer on panel flutter
Turbulent boundary layer effects on flutter of flat rectangular panels
Gaspers, P. A., Jr.↗
Theoretical considerations of some nonlinear aspects of hypersonic panel flutter Annual report, 1 Sep. 1968 - 31 Aug. 1969
Aerodynamic nonlinearity and turbulent boundary layer effects on hypersonic panel flutter
Lerner, J. I.↗
The influence of elastic boundary conditions on the resonant response of thin cylindrical shells
Elastic boundary conditions effect on natural frequencies and resonant displacement of thin isotropic circular cylindrical shell under concentrated load with harmonic time history
Egle, D. M.↗
On the specification of the blue edge of the RR Lyrae instability strip
Blue edge of RR Lyrae instability strip, examining convection, radiation and surface boundary conditions effects
Iben, I., Jr.↗
Dynamic instability of a cantilever column subjected to a follower force including thermomechanical coupling effect
Cantilever column critical dynamic instability load under nonconservative follower force including thermomechanical coupling effect from boundary value problem formulation
Shieh, R. C.↗
Inlet-engine-nozzle wind tunnel test techniques
Supersonic propulsion system inlet, engine and exhaust nozzle in wind tunnel and flight tests, discussing boundary layer effects on performance
Bowditch, D. N.↗
Shock wave-turbulent boundary layer interactions in rectangular channels.
Interaction regions created by the impingement of full span, externally generated, shock waves on a nozzle wall boundary layer were investigated. Incident shock strength was varied to produce unseparated, incipient, and fully separated flow fields. Significant departures from two-dimensionality were observed over the entire range of shock strengths tested and were identified with sidewall and corner boundary layer effects. However, comparisons of present centerline results with published two-dimensional data, obtained under similar test conditions and geometrical constraints, showed excellent agreement (e.g., incipient separation pressure levels, wall pressure distributions, free-interaction, and scale of the interaction region). This raises some question concerning the degree of two-dimensionality achieved in these previous investigations.
Reda, D. C.↗
Shock tube study of the reaction H plus O2 plus Ar yields HO2 plus Ar
Rate coefficient data for the recombination reaction H + 02 + Ar yields H02 + Ar have been determined from studies of lean hydrogen-oxygen mixtures behind incident shock waves over the temperature range of 948 to 1125 K. Hydroxyl radical concentration profiles were measured by ultraviolet absorption spectroscopy, and rate data were obtained through analysis of induction time and exponential growth parameter data. Analysis of the data yielded a rate coefficient which was generally lower than most of the more recent values obtained from shock tube studies. The effect of boundary layer formation on the conditions behind the shock was also examined and found to be negligible.
Jachimowski, C. J.↗