Resume

• 2008

  Spanish

  English

  Italian

  Doctor of Philosophy (Ph.D.)

  Dissertation: “Active Flow Control of Cantilevered Cylinders of Low-Aspect Ratio”

  Mechanical Engineering

  Rensselaer Polytechnic Institute

• 2006

  Master of Science (M.S.)

  Thesis: “Design and testing of a rechargeable

  pressure-compensated

  lithium-\nion battery module for underwater use”

  Aerospace Engineering

  Sigma Gamma Tau

  AIAA

  Tau Beta Pi

  University at Buffalo

• 2002

  Bachelor of Science (B.S.)

  Aerospace and Mechanical Engineering

  AIAA\n\nSigma Gamma Tau\n\nTau Beta Pi

  University at Buffalo

• 1.40

  High-speed

  time-resolved particle image velocimetry with a pulse-burst laser was used to measure the gas-phase velocity upstream and downstream of a shock wave–particle curtain interaction at three shock Mach numbers (1.22

  and 1.45) at a repetition rate of 37.5 kHz. The particle curtain was formed from free-falling soda-lime particles resulting in volume fractions of 9% or 23% at mid-height

  depending on particle diameter (106–125 and 300–355 μm

  respectively). Following impingement by a shock wave

  a pressure difference was created between the upstream and downstream sides of the curtain

  which accelerated flow through the curtain. Jetting of flow through the curtain was observed downstream once deformation of the curtain began

  demonstrating a long-term unsteady effect. Using a control volume approach

  the unsteady drag on the curtain was estimated from velocity and pressure data. The drag imposed on the curtain has a strong volume fraction dependence with a prolonged unsteadiness following initial shock impingement. In addition

  the data suggest that the resulting pressure difference following the propagation of the reflected and transmitted shock waves is the primary component to curtain drag.

  Unsteady drag following shock wave impingement on a dense particle curtain measured using pulse-burst PIV

  Control of a laminar separation bubble on a two-dimensional NACA 0009 was investigated experimentally in an open-return wind tunnel using Stereoscopic Particle Image Velocimetry (SPIV) measurements at a range of chord-based Reynolds numbers

  ReC between 2.0∙104 and 3.0∙104. In this study

  flow control was accomplished through a row of surface-mounted Electro-Active Polymers (EAPs)

  centered at x/c = 0.2. A three-dimensional separation bubble was seen to exist at  = 5˚

  in agreement with literature. Furthermore

  the streamwise and cross-stream extents of the bubble decrease with increase of the Reynolds number. The most amplified mode of the separated mixing layer was found by applying linear stability analysis on the experimental data. Using this information

  By actuating the EAP was actuated at a frequency corresponding to the Kelvin-Helmholtz instability of the separated mixing layer

  which resulted in mitigation of the separation bubble was achieved.

  Control of a Laminar Separation Bubble on a Pitched NACA 0009 Airfoil Using Electro-Active Polymers

  Russell W. Spillers

  John F. Henfling

  Justin L. Wagner

  Steven J. Beresh

  Volumetric measurements of the flow within four open cavities were made using stereoscopic particle image velocimetry at a freestream Mach number of 0.8. The cavities nominally had a length-to-diameter ratio

  L/D = 7

  along with an aspect ratio

  b/L= 0.5. The\nthree complex cavity geometries were selected to model features representative of real air-\ncraft bays and compare them to a finite-span rectangular cavity: these included features\nsuch as leading edge and side ramps

  a scooped leading edge ramp

  and a jagged leading\nedge. Flow is drawn into the cavity at the edges due to a lack of pressure recovery within the\ncavity. Due to the influence of the leading edge shape and side edges

  three-dimensionalities\nare formed within the cavities that influence the development of the Rossiter tones. In the\nrectangular cavity

  these three-dimensionalities lead to the formation of a set of counter-\nrotating streamwise-oriented vortices

  which create a nearly-sinusoidal

  spanwise waviness\nwithin its mixing layer. The addition of leading edge and side ramps disrupt the formation of these vortical structures and displace the mixing layer vertically

  reducing Rossiter\nmodal amplitudes. The leading edge ramp accelerates the oncoming flow

  resulting in a\nshift in the Rossiter frequencies. A scooped leading edge reintroduced streamwise vorticity

  \nincreasing cavity turbulence

  whereas an overhanging jagged leading edge reduced cavity\nvelocity fluctuations while increasing the strength of the second Rossiter mode.

  Three-Dimensional Measurement of Edge Effects in Open Cavities of Finite-Span

  Paul A. Farias

  Brian O. Pruett

  Daniel R. Guildenbecher

  Katya M. Casper

  Steven J. Beresh

  Justin L. Wagner

  AIAA Paper No. 2016-0791

  Time-resolved particle image velocimetry (TR-PIV) measurements were made in a shock tube using a pulse-burst laser. Two transient flow fields were investigated including the baseline flow in the empty shock tube and the wake growth downstream of a cylinder spanning the width of the test section. Boundary layer growth was observed following the passage of the incident shock in the baseline flow

  while the core flow velocity increased with time. The measured core flow acceleration was compared to that predicted using a classical unsteady boundary layer growth model. The model typically provided good estimates of core flow acceleration at early times

  but then typically underestimated the acceleration. As a result of wall boundary layers

  a significant amount of spatial non-uniformity remained in the flow following the passage of the end-wall reflected shock

  which could be an important factor in combustion chemistry experiments. In the transient wake growth measurements

  the wake downstream of the cylinder was symmetric immediately following the passage of the incident shock. At later times (= 0.5 ms)

  the wake transitioned to a von Karman vortex street. The TR-PIV data were bandpass filtered about the vortex frequency to reveal additional details on the transient wake growth.

  Pulse-burst PIV measurements of transient phenomena in a shock tube

  The present work aims to identify and quantify underlying physics behind the formation of three-dimensional stall cell using oil flow visualization and stereoscopic particle image velocimetry (SPIV) on a two-dimensional NACA 0015 airfoil. The three dimensional structures were explored at various angles of attack (14-18-degrees) and Reynolds numbers. Surface oil flow visualization was used to qualitatively identify the stall cells and resolve associated equivalent near surface skin friction. In addition

  SPIV measurements were taken in order to visualize the stall cells above the surface of the airfoil. Results showed that the stall cells are highly sensitive to Reynolds number and angle of attack

  with evidence of an apparent bi-stable state. Using SPIV the flow fields and the associated vorticity fields for the various cases were measured and correlated to the surface oil flow visualization.

  Measurements of 3-D stall cells on 2-D airfoils

  Michael Amitay

  Chia Min Leong

  This paper discusses the interaction s single synthetic jet with the flow over a finite span low aspect ratio cylinder. The synthetic jet was located at the mid-span of the cylinder

  and was oriented such that the length of the jet orifice was parallel to the freestream direction. The investigation incorporated experimental techniques such as stereoscopic particle image velocimetry (SPIV) and hot-wire anemometry

  as well as hydrodynamic stability analysis. The near wake of the cylinder was dominated by a non-negligible spanwise velocity

  or downwash

  from the cylinder’s free-end that interacted with the near wake resulting in a highly three-dimensional flow field with a strong spanwise dependence. SPIV measurements within the near wake showed that

  due to the actuation of the synthetic jet

  the wake was vectored and narrowed

  resulting in a redirection of the downwash behind the cylinder. Furthermore

  the synthetic jet actuation resulted in a localized region of inward-directed flow at a spanwise location outboard of the jet orifice leading to vortex dislocations within the streamwise vorticity field within the near wake. The result was a three-dimensional separation line along the span of the cylinder that gave rise to the spanwise dependency seen in the near wake. Finally

  it was shown

  using a stability theory analysis that the near surface interaction of the synthetic jet with the separated mixing layer did not result in excitation of the mixing layer instability.

  Interaction of a synthetic jet with the flow over a low aspect ratio cylinder

  Michael Amitay

  Chia Min Leong

  Modification to the flow field about a finite-span cylinder of low-aspect ratio (AR = 3) by a single synthetic jet

  mounted normal to the cylinder axis

  was studied experimentally using surface-mounted pressure taps

  stereoscopic particle image velocimetry (SPIV)

  and constant-temperature anemometry (CTA). The synthetic jet altered the circulation about the cylinder and created a large spanwise change to the surface pressure

  much greater than the dimensions of its orifice. SPIV measurements in the near wake showed that the synthetic jet enhances mixing of the downwash from the cylinder free end with the wake deficit

  vectoring and narrowing the wake. The synthetic jet penetrates through the streamwise vorticity

  enhancing mixing within the wake and reducing the power associated with the shedding frequency

  St = 0.155

  except below the vortex dislocation

  where the shedding frequency was increased to that corresponding to a quasi-two-dimensional cylinder

  St = 0.22.

  Modification of the near wake behind a finite-span cylinder by a single synthetic jet

  Edward P.

  DeMauro

  Sandia National Laboratories

  Rutgers University

  Rensselaer Polytechnic Institute

  Piscataway

  NJ

  Experimental aerodynamics and flow control

  Assistant Professor of Mechanical and Aerospace Engineering

  Rutgers University

  Troy

  New York

  * Designed wind tunnel model for capturing and canceling Tollmein-Schichting waves using Electro-Active Polymers\n\n* Published peer-reviewed papers\n\n* Instructed and oversaw graduate student projects

  Postdoctoral Research Assistant at RPI Center for Flow Physics and Control (CEFPAC)

  Rensselaer Polytechnic Institute

  Troy

  NY

  Fall 2013 - Spring 2014: Thermal and Fluids Engineering II and Thermal and Fluids Engineering Lab\n\nFall 2014: Flight Mechanics and Thermal and Fluids Engineering Lab

  Mechanical and Aeronautical Engineering Lecturer

  Rensselaer Polytechnic Institute

  Albuquerque

  NM

  Experimental aerodynamics work within Sandia National Labs' trisonic wind tunnel (TWT) and multiphase shock tube (MST). I have worked with a variety of equipment

  including stereoscopic PIV and time-resolved PIV using a pulse-burst laser.

  Aerosciences Department Postdoctoral Appointee

  Sandia National Laboratories

• Fluid Dynamics

  NI LabVIEW

  Heat Transfer

  Tecplot

  Wind Tunnel Testing

  Aerodynamics

  PIV

  Fluid Mechanics

  Aerospace Engineering

  Flow Control

  Mechanical Engineering

  Matlab

  Physics

  Research

  LabVIEW

  Unsteady drag following shock wave impingement on a dense particle curtain measured using pulse-burst PIV

  Paul A. Farias

  Steven J. Beresh

  Justin L. Wagner