Search NASA⌕ Search

SEARCH · Search NASA

Results for “FENCES”

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.

Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.

At least 55 records · Page 3
All sourcesNASA NTRSDOE OSTI
NASA NTRS1983

A miniature, directional surface-fence gage for three-dimensional turbulent boundary layer measurements

A new miniature (3.175 mm overall diameter) surface-fence gage was developed to measure simultaneously the magnitude and direction of wall shear stress under three-dimensional turbulent boundary layers. Two fence elements were placed orthogonal to each other on the end surface of the gage. The gage was calibrated for its directional and magnitude sensitivities. It was then tested under an axisymmetric swirling boundary layer, subject to a sudden transverse strain. The advantage of the gage was demonstrated, and excellent agreement was obtained with the results from surface oil flow interferometry and velocity field measurements. The results also compared well with numerical computations.

Higuchi, H.↗
NASA NTRS1991

Aerodynamics of airfoils with vortex trapped by two spanwise fences

An airfoil configuration is presented whose lift is enhanced by a trapped-vortex flow field. Based on the research to date, it is recommended that two spanwise fences be used to enclose the trapped vortex and that the fence heights be adjusted so that the equilibrium condition can be achieved with little or no mass removal from the core region of the vortex. It is also shown that the vortex bubble can be located fore and aft on the airfoil to control aerodynamic parameters, such as the pitching moment. Applications of the high-lift concept presented here are briefly discussed.

Rossow, Vernon J.↗
NASA NTRS1992

Two-fence concept for efficient trapping of vortices on airfoils

Previous work on the use of a vortex trapped above a wing in order to produce high lift at low angles of attack is extended here. It is first postulated that the optimum way to trap a vortex is to design the airfoil section and wing so that the flow along the vortex core is minimized. It is then shown that a vertical fence both in front of and behind the separation bubble generated by the trapped vortex is an effective way to reduce the mass flow removal and its associated drag to a negligible amount. In order to show that vertical surfaces upstream and downstream of the vortex separation bubble have an opposite effect on the source requirements for vortex trapping, conformal mapping methods are used to obtain the solutions for a variety of simple two-dimensional, inviscid, incompressible flow configurations. Trapped-vortex flowfield solutions for the flow over flat plate and Clark-Y airfoils are then used to demonstrate that the heights of the fences can be tailored to make the required mass withdrawal (and therefore, the drag due to trapping) to be vanishingly small.

Rossow, Vernon J.↗
NASA NTRS1998

Characterization of Plated Via Hole Fences for Isolation Between Stripline Circuits in LTCC Packages

Reduced coupling between adjacent striplines in LTCC packages is commonly accomplished by walls made of plated via holes. In this paper, a 3D-FEM electromagnetic simulation of stripline with filled via fences on both sides is presented. It is shown that the radiation loss of the stripline and the coupling between striplines increases if the fence is placed too close to the stripline.

Ponchak, George E.↗
NASA NTRS1961

Wind-Tunnel Investigation of the Effects of Wing Bodies, Fences, Flaps, and a Fuselage Addition on the Wing Buffet Response of a Transonic-Transport Model

The experimental wing buffet response of a transport-type airplane model with and without wing bodies, fences, flaps, and a fuselage addition has been investigated at Mach numbers from 0.20 to 1.03. The wing had NACA 64A-series airfoil sections inclined 5 degrees to the free-stream direction. The quarter-chord line of the wing was swept back 45 degrees, the aspect ratio was 7, the taper ratio was 0.3, and the thickness ratio varied from 0.115 at the root to 0.074 at the midsemispan and was constant from that station to the tip. The wing was twisted and cambered for a design lift coefficient of 0.3. The results of the investigation indicated that a marked reduction of buffet intensity and a delay of buffet onset at transonic speeds were achieved by the addition to the wing of special bodies designed to reduce shock-induced separation. The further addition of wing fences and wing trailing-edge flaps deflected 30 degrees increased the lift coefficients at which low-speed stall buffeting occurred. An addition to the fuselage near the upper forward portion produced no consistent change in the buffet characteristics.

Cornette, Elden S.↗
NASA NTRS2010

Transition Induced by Fence Geometrics on Shuttle Orbiter at Mach 10

Fence-induced transition data simulating a raised gap filler have been acquired on the wing lower surface of a Shuttle Orbiter model in the Langley 31-Inch Mach 10 Tunnel to compare with the Shuttle Boundary Layer Transition Flight and HYTHIRM Experiments, and to provide additional correlation data for the Boundary Layer Transition Tool. In a qualitative assessment, the data exhibit the expected response to all parameter variations; however, it is unclear whether fully effective tripping at the fence was ever realized at any test condition with the present model hardware. A preliminary, qualitative comparison of the ground-based transition measurements with those obtained from the STS-128 HYTHIRM imagery at Mach 15 reveal similar transition-wake response characteristics in terms of the spreading and the path along the vehicle surface.

Everhart, Joel L.↗
DOE OSTI2012

Turbine blade squealer tip rail with fence members

A turbine blade includes an airfoil, a blade tip section, a squealer tip rail, and a plurality of chordally spaced fence members. The blade tip section includes a blade tip floor located at an end of the airfoil distal from the root. The blade tip floor includes a pressure side and a suction side joined together at chordally spaced apart leading and trailing edges of the airfoil. The squealer tip rail extends radially outwardly from the blade tip floor adjacent to the suction side and extends from a first location adjacent to the airfoil trailing edge to a second location adjacent to the airfoil leading edge. The fence members are located between the airfoil leading and trailing edges and extend radially outwardly from the blade tip floor and axially from the squealer tip rail toward the pressure side.

42 ENGINEERING↗
DOE OSTI2025

Determination of Ground Subsidence Around Snow Fences in the Arctic Region

In this study, we analyzed the effects of snow cover changes caused by snow fences (SFs) installed in 2017 in the Alaskan tundra to examine ground subsidence. Digital surface model data obtained through LiDAR-based remote sensing in 2019 and 2022, combined with a field survey in 2021, revealed approximately 0.2 m of ground subsidence around the SF. To investigate the relationship between SF-induced snow cover changes and ground subsidence, geophysical methods, electrical resistivity tomography (ERT) and ground-penetrating radar (GPR), were applied in 2023 to analyze subsurface characteristics. The increased snow cover due to the SF-enhanced insulation, delaying the penetration of winter cold into the subsurface. This delay caused subsurface temperatures to decrease more slowly, melting the upper permafrost and increasing the thickness of the active layer. ERT and GPR surveys well delineated the boundary between the active layer and permafrost, confirming that the increased snow cover thickened the active layer. This thickening led to the melting of pore ice, causing water runoff and ground compaction, which resulted in subsidence. The runoff also formed channels flowing eastward over the SF. This study highlights how changes in snow cover can influence active layer properties, leading to localized environmental changes and ground subsidence.

54 ENVIRONMENTAL SCIENCES↗
NASA NTRS1971

Fence guide for millimeter waves

Fence guide waveguide on dielectric substrate for millimeter wave, applying to power dividers, directional couplers, hybrid rings and resonators

Tischer, F. J.↗
NASA NTRS1983

A radio-frequency analysis of paraboloidal antennas located near diffracting fences

The cylindrical waves associated with the Sommerfeld solution for a diffracting half-plane are applied in the evaluation of the effects of secondary radiation on the focal-region-fields of paraboloids. A cross-correlation between the computed focal-region-fields and the feed-antenna-fields is then introduced to determine the modified radiation pattern of paraboloidal antennas. The half-plane solution is adapted to estimate the effects of a polygonal fence on 9-meter S-band and 3-meter S- and Ku-band antennas at the Merrit Island, Fl Spacecraft Tracking and Data Network Station.

Schmidt, R. F.↗
NASA NTRS1987

The focal plane reception pattern calculation for a paraboloidal antenna with a nearby fence

A computer simulation program is described which is used to estimate the effects of a proximate diffraction fence on the performance of paraboloid antennas. The computer program is written in FORTRAN. The physical problem, mathematical formulation and coordinate references are described. The main control structure of the program and the function of the individual subroutines are discussed. The Job Control Language set-up and program instruction are provided in the user's instruction to help users execute the present program. A sample problem with an appropriate output listing is made available as an illustration of the usage of the program.

Schmidt, Richard F.↗
NASA NTRS1951

Wind-tunnel investigation of the effects of horizontal-tail position on the low-speed longitudinal stability characteristics of an airplane model with a 35 degrees sweptback wing equipped with chordwise fences

An experimental investigation was made in the Langley stability tunnel to determine whether the low-speed longitudinal stability characteristics of a model with a 35 degree sweptback wing could be improved appreciably by lowering the horizontal tail. The investigation included tests of several components of the model and of various model configurations with chordwise fences on the wing.

Queijo, M J↗
NASA NTRS1953

Flight Determination of the Longitudinal Stability in Accelerated Maneuvers at Transonic Speeds for the Douglas D-558-II Research Airplane Including the Effects of an Outboard Wing Fence

The results of transonic flight measurements of the longitudinal stability characteristics of the Douglas D-558-II research airplane in the original configuration and with outboard fences mounted on the wings are presented. The levels of normal-force coefficient at which the stability decreases and pitch-up starts have been determined for both airplane configurations at Mach numbers up to about 0.94.

AIRPLANES - PECIFIC TYPES↗