Results 61 to 70 of about 92,283 (210)

Study on the Suppression of Tip Leakage Vortex in Axial Flow Pumps Based on Circumferential Grooving in the Rotor Chamber

Journal of Marine Science and Engineering
The stability of axial flow pumps is significantly affected by the tip leakage vortex (TLV), which is generated through the entrainment of the main flow.
Haoran Wu, Desheng Zhang, Xi Shen, Chen Ni, Gang Yang   +4 more
doaj   +1 more source

Numerical Analysis of Leading-Edge Vortex Effect on Tidal Current Energy Extraction Performance for Chord-Wise Deformable Oscillating Hydrofoil

Journal of Marine Science and Engineering, 2019
To improve the energy extraction performance of the oscillating hydrofoil, the lift force that acts on the oscillating hydrofoil is analyzed. The pressure difference between the oscillating hydrofoil‘s opposing surfaces is dominant to generate the ...
Jianan Xu, Haiyang Zhu, Daitao Guan, and Yong Zhan   +3 more
doaj   +1 more source

Subsonic balance and pressure investigation of a 60 deg delta wing with leading edge devices [PDF]

Low supersonic wave drag makes the thin highly swept delta wing the logical choice for use on aircraft designed for supersonic cruise. However, the high-lift maneuver capability of the aircraft is limited by severe induced-drag penalties attributed to ...
Rao, D. M., Tingas, S. A.
core   +1 more source

Leading-Edge Vortex Control by Unsteady Blowing [PDF]

, 2021
At high incidences, a leading-edge vortex becomes unstable, endangering the flight stability and controllability of delta-wing configurations. Active flow control by pulsed blowing offers an effective mean for stabilising the vortex system and enlarging the flight envelope.
openaire  

Thresholds and influencing factors on vortex bursting of an ogive-cylinder body-delta wing: an experimental and numerical approach

Advances in Aerodynamics
Despite the exceptional aerodynamic performance of delta wing-body configurations, the phenomenon of vortex bursting and its influencing factors remain inadequately understood.
Arash Alipoor, Mohammad Mehdi Alishahi, Mohammad Hossein Montazeri   +2 more
doaj   +1 more source

Investigation of variation in the leading edge shapes on the aerodynamic characteristics over a delta wing [PDF]

EPJ Web of Conferences
The present study deals with the effect of varying the slender delta wing's leading edge shapes on the aerodynamic characteristics using a subsonic wind tunnel.
Gupta Sugandh, Kumar Rakesh, Kumar Sanjeev, Siag Tushar   +3 more
doaj   +1 more source

Numerical study of delta wing leading edge blowing [PDF]

Spanwise and tangential leading edge blowing as a means of controlling the position and strength of the leading edge vortices are studied by numerical solution of the three-dimensional Navier-Stokes equations.
Roberts, Leonard, Tavella, Domingo, Yeh, David   +2 more
core   +1 more source

Water-tunnel and analytical investigation of the effect of strake design variables on strake vortex breakdown characteristics [PDF]

A systematic water-tunnel study was made to determine the vortex breakdown characteristics of 43 strakes. The strakes were mounted on a 1/2-scale model of a Langley Research Center general research fighter fuselage model with a 44deg leading-edge-sweep ...
Frink, N. T., Lamar, J. E.
core   +1 more source

Flow field over the wing of a delta-wing fighter model with vortex control devices at Mach 0.6 to 1.2 [PDF]

As part of a cooperative research program between NASA, McDonnell Douglas Corporation, and Wright Research and Development Center, a flow field investigation was conducted on a 7.52 percent scale windtunnel model of an advanced fighter aircraft design ...
Bare, E. Ann, Haddad, Raymond C., Reubush, David E.   +2 more
core   +1 more source

Exploratory subsonic investigation of vortex-flap concept on arrow wing configuration [PDF]

The drag reduction potential of a vortex flap concept, utilizing the thrust contribution of separation vortices maintained over leading edge flap surfaces, was explored in subsonic wind tunnel tests on a highly swept arrow wing configuration.
Rao, D. M.
core   +1 more source