2 edition of Investigation of the vortex field generated by a slender delta wing found in the catalog.
Investigation of the vortex field generated by a slender delta wing
Thesis (M.Sc.) - University of Warwick, 1989.
|Statement||author: George Leftheriotis.|
The ﬂow over an aspect ratio 1 delta wing with twin vertical tails is studied in a combined computational and experimental investigation. This research is conducted in an effort to understand the vortex and ﬁn interaction process. The computational algorithm used solves both the thin-layer Navier-Stokes and the inviscid Euler equations and. Tim Lee’s journal publications Lee, T., and Tremblay-Dionne, V., () “Impact of wavelength and amplitude of a wavy ground on a static NACA airfoil” submitted to Journal of Aircraft (paper in review). Lee, T., () “Aerodynamic performance of non-slender reverse delta wing and delta wing in ground effect,” submitted to.
the leading-edge vortices (LEVs) generated by such wings that are so critical to delta wing performance.3 The stall behavior of classical high-aspect-ratio wings and the breakdown of the LEVs of slender delta wings are an extensively Presented asPaper at theAIAA31st Fluid DynamicsConfer-. The flow about a slender flat-plate delta wing at angle-of-attack is represented by replacing the vortex core-feeding sheet system associated with leading edge separation by a force-free concentrated vortex.
on a chord of mm delta wing. A schematic of the experimental system used in the present investigation is shown in Figure 1. The delta wing used had a chord length of C = mm at a sweep angle of = The thickness of the delta wing was mm. It was beveled at an an-gle of 34 on its windward side. The impingement plate had a. This paper presents an experimental investigation of the application of dielectric barrier discharge (DBD) plasma actuators on a slender delta wing to control the leading edge vortices (LEVs). The experiments are conducted in a wind tunnel with a Reynolds number of Cited by: 4.
letters of St. Paul to seven churches and three friends with the letter to the Hebrews
The politics of opera in Handels Britain
Scoping determination for the pavilion at park square: submission requirements for draft project impact report (dpir).
The Gulliver File: Mines, People and Land
Guide to the Lancashire Record Office.
Inter-American Development Bank
India and Sikkim, 1814-1970
analysis of domestic and foreign demand for U.S. soybeans and soybean products
Workshop Series on the Accelerated Agrarian Reform program, March 11-12, 1987
Mississippi roots n records
Vanguard acceptors of family planning in Senegal
The haunted bookshop
RACER # 3524303
The vortex flow produced by a slender delta wing with sharp leading edges at incidence was investigated experimentally. The tests were carried out in a wind tunnel using three delta wing models of 70°. 75° and 79° sweep-back angle, set at angles of attack varying from 10° to 30°.
This procedure was used for designing two turbines to operate in the vortex flow generated by a slender delta wing at incidence.
One turbine was designed for high chord Reynolds numbers and the. Carpenter, Investigation of the vortex field generated by a slender delta wing. Wind Eng., 14(3) ().
2 H.W. Lerbs, Moderately loaded propellcrs with a finite number of blades and an arbitrary distribution of : G. Leftheriotis, C.J.
Carpenter. The effect of apex flap and tip flap, deflected both independently and jointly, on the vortex flow and lift generation of a 65 deg-sweep delta wing was investigated experimentally. The drooped apex flap produced a higher lift at medium-to-high angle of attack regime and also a delayed by: 1.
An investigation into the use of GAMA water tunnel for visualization of vortex breakdown on the delta wing. Symmetry breaking and instabilities of conical vortex pairs over slender delta wings. 26 October | Journal of Fluid Mechanics, Vol. Experimental investigation of high-incidence delta-wing flow by: Thus vortex asymmetry was not generated.
However, significant vortex asymmetry was observed for round leading-edged delta wings. Asymmetric separation positions over the round leading edge was the result of laminar/turbulent transition which caused vortex asymmetry on these delta wing configurations.
Following breakdown, a larger region of vorticity made of small-scale, unsteady vortical structures is seen, with a concentration in the region of the primary LEV.
The delta wing vortex system, on the other hand, largely retains coherence. The trajectory of the delta wing primary vortex is tracked, showing the location of the vortex along the by: 4.
Lift of Slender Delta Wings According to Newtonian Theory ARTHUR F. MESSITER* California Institute of Technology, Pasadena, Calif.
An approximate system of equations is derived to describe the inviscid flow past a flat slender wing at angle of attack, in the limit y —»• 1 and Mm sin a.
FLOW FIELD INVESTIGATION AND VORTEX BREAK-DOWN Turbomachinery, Thessaloniki Greece Keywords: Delta wing, Vortex breakdown, URANS, Reynolds stress model Abstract. The lift of a Delta wing is produced by two counter rotating vortices, generated from the wing’s sharp swept leading edge as a result of the unequal wing’s pressure.
The behaviour of the ﬂow over slender delta wings under transonic conditions is highly complex. With the occurrence of a number of shocks in the ﬂow the behaviour of vortex breakdown is quite diﬀerent to that for subsonic ﬂow.
This investigation considers this behaviour over the 65o sharp leading edge delta wing used in the 2nd. An Investigation of the Breakdown of the Leading Edge Vortices on a Delta Wing at High Angles of Attack“, AIAA paper no. 83–, Google Scholar Payne, F.M.,”Cited by: In the flow past a slender delta wing at incidence one can observe a roughly axially symmetric core of spiralling fluid, formed by the rolling-up of the shear layer that separates from a leading edge.
The aim in this paper is to predict the flow field within this vortex core, given appropriate conditions at its outside by: The flow at incidence to a slender delta wing with a sharp leading edge usually separates along this edge, i.e.
a vortex layer extends from the edge into the main flow. This layer rolls up above and inboard of the leading edge to form a region of high vorticity which strongly influences the flow pattern.
The ground effect on the aerodynamic loading and leading-edge vortex (LEV) flow generated by a slender delta wing was investigated experimentally. Both the lift and drag forces were found to increase with reducing ground distance (up to 50% of the wing chord).Cited by: 3.
Considering the above concerns, a strategy to combine smoke flow visualization and PIV measurement is proposed and demonstrated here to study the complex flow over a slender delta wing.
Numerous studies of LEV flows over delta wings have been conducted 7, 8, with flow visualization techniques used as the primary by: 1. Ff A great deal of attention has been paid to phenom-ena of the leading-edge vortex breakdown over delta wing, and much achievement has been obtained in ex-periments and theoretical analysis.[1−7] It has been concluded that the vortex breakdown location moves forward as the angle of attack α increases, and back-ward as the sweep angle Λ.
Abstract This paper presents an experimental investigation of the oscillations of the leading-edge vortex breakdown locations over a slender delta wing with a 75 deg sweep : Lu Shen, Chih-yung Wen.
The vortex structures on the leeward side of a large delta wing have been investigated by use of laser sheet imaging (LSI) and particle image velocimetry (PIV). NASA Langley researchers A. Ayoub and B.G. McLachlan of the Fluid Mechanics Lab provide a study to examine flow past a delta wing at a critical.
The vortex flow and lift force generated by a 50°-sweep non-slender reverse delta wing were investigated via particle image velocimetry, together with flow visualization and force balance measurement, at Re = 11, The non-slender reverse delta wing produced a delayed stall but a lower lift compared to its delta wing by: 1.
The modification of the tip vortex generated by a rectangular NACA wing via a tip-mounted slender half-delta wing (HDW) was attempted experimentally at Re=×10 addition to the increase in lift with increasing HDW deflection, compared to the baseline wing, the roll-up process of the tip vortex was also found to be significantly modified, as a result of the breakdown of the HDW by: 8.vortex generators to energize the local boundary layer to larger wing leading-edge extensions, strakes, and canards to control the global flow field.
The aerodynamic benefits of vortex flows can be extended, and undesired effects mitigated, by tailoring the vehiclegeometry or incorporating passive and active flow control concepts.The book discusses the behavior of vortices over sharp and highly swept wing configurations used for current and future military aircraft.
Special attention is paid to the effects of critical flow phenomenon such as vortex breakdown occuring at high angles of attack or high angular rates.