Thomas J. Juliano

Thomas J. Juliano
University of Notre Dame | ND · Department of Aerospace and Mechanical Engineering (AME)

Doctor of Philosophy

About

104
Publications
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Introduction
Skills and Expertise

Publications

Publications (104)
Conference Paper
Background-oriented schlieren and stagnation-pressure measurements were taken for a variable-diameter 70 deg. half-angle sphere-cone model in the AFOSR–Notre Dame Large Mach-6 Quiet Tunnel under conventional noise to determine tunnel start conditions and run time. Model diameters ranging from 60–220 mm were tested at driver tube pressures from 105–...
Conference Paper
The impact of surface deformation on shock-wave/boundary-layer interactions (SWBLIs) was investigated by first applying thermo-structural finite element analysis to the ROcket Technology EXperiment–Transition (ROTEX-T) cone-flare to predict representative deformation of a hot-structure panel. The deformation was scaled to the boundary-layer thickne...
Conference Paper
Several practical problems require high thermal resistance and minimum compliance. An example is a high-temperature computer-controlled stage for additive manufacturing, which must be heated and precisely positioned. In this case, the heat transfer from the build plate must be limited to minimize the heating of the computer-controlled stage. The si...
Conference Paper
Full-text available
Infrared thermography and high-speed, high-resolution background-oriented schlieren (BOS) measurements were made simultaneously on a cone-flare model in the AFOSR–Notre Dame Large Mach-6 Quiet Tunnel at freestream unit Reynolds numbers from Re_{\infty} = 5.8x10^6 m^{-1} to 12.3x10^6 m^{-1} and nominally zero angle of attack. The model consisted of...
Article
Full-text available
Fast pressure-sensitive paint (PSP) was applied to an inlet/isolator designed using the Osculating Internal Waverider Inlet with Parallel Streamlines (OIWPS) method. The dorsal isolator surface pressure was measured using anodized-aluminum PSP through transparent cast acrylic that makes up the ventral portion of the isolator. Temperature-sensitive...
Article
Experiments and computational analysis have been conducted to study instabilities in the boundary layer over a swept fin–cone geometry in hypersonic flow. Experiments were carried out at the United States Air Force Academy’s Mach 6 Ludwieg Tube. Infrared thermography was employed to assess the surface temperature distribution, particularly the ther...
Conference Paper
Full-text available
As part of NATO STO AVT-346 “Predicting Hypersonic Boundary-Layer Transition on Complex Geometries,” coordinated experimental and computational studies were conducted on the ROTEX-T, a cone-flare geometry used in a successful flight-test experiment. At the as-flown conditions, a separation bubble existed at the compression corner. Separation, reatt...
Conference Paper
Full-text available
Experiments were performed in the Mach 3.5 Supersonic Low Disturbance Tunnel on the BOundary-Layer Transition (BOLT) geometry. The goal of this campaign was to assess changes to the transition front by varying the freestream noise and the model surface quality. The model was printed of polycarbonate and is 30% scale of the flight geometry. It was t...
Conference Paper
Full-text available
Most prior measurements of density via Background-Oriented Schlieren (BOS) numerically integrate the Poisson equation to reconstruct density fields, which is susceptible to errors in density gradient measurements and uncertainties in boundary values. An alternative technique, parallel-ray omni-directional integration, is compared here. Experiments...
Conference Paper
Full-text available
Infrared thermography measurements on an 8.8% scale BOLT-1a model were made in the NASA Langley Probe Calibration Tunnel for freestream unit Reynolds numbers from 7.7 M/m to 30.7 M/m, a freestream Mach number of 3.5, and nominal angle of attack of 0 degrees. The model was printed from polycarbonate and tested before and after fine-grit sanding to e...
Article
The design of an inward-turning high-speed three-dimensional streamline-traced intake is presented from osculating axisymmetric theory. To satisfy the osculating intake design criteria, a stitched Busemann diffuser and internal conical flow-A solution are used as the basic isentropic compressive streamline. This new contour provides efficient compr...
Conference Paper
A fast pressure-sensitive paint (PSP) was used to investigate unstart and shock-train mean and unsteady characteristics in a circular isolator with a conical inlet in Mach 6.3 flow. The internal surface pressure was imaged through transparent cast acrylic that constituted half of the isolator. Temperature-sensitive paint measured the internal surfa...
Conference Paper
Full-text available
Background-oriented schlieren and infrared thermography measurements were made simultaneously on a ROTEX-T cone/flare model in the AFOSR–Notre Dame Large Mach-6 Quiet Tunnel at freestream unit Reynolds numbers from 5.8 to 12.1 M/m and nominally zero angle of attack. The surface heat-flux and Stanton number distributions were computed. Separation an...
Article
Full-text available
View Video Presentation: https://doi.org/10.2514/6.2022-3259.vid The testing of an inward-turning, high-speed, 3D streamline traced inlet is presented from osculating axisymmetric theory. A new method of high-speed inlet design, labeled the Osculating Internal Waverider inlet with Parallel Streamlines (OIWPS), was used to design two inlet-isolator...
Article
A novel technique for obtaining quantitative infrared-thermography data on metallic (e.g., aluminum or steel) wind-tunnel models is developed. The methodology incorporates a matte-black, thin, wrap-film (3M\texttrademark Wrap Film Series 1080), which is both commercially available and relatively inexpensive. Compared to painting the model to increa...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2022-0598.vid A series of new experiments have been conducted to study the effects of varying nose bluntness and free stream Reynolds number on the boundary layer that develops over a swept fin-cone geometry in hypersonic flow. The experimental model was a 7° half-angle right circular cone coupled...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2022-0064.vid The design of an inward-turning, high-speed, 3D streamline traced intake is presented from osculating axisymmetric theory. To satisfy the osculating intake design criteria, a stitched Busemann diffuser and Internal Conical Flow-A (ICFA) solution is used as the basic isentropic compres...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2022-2223.vid A static pressure probe has been employed in three hypersonic wind tunnels: the von Karman Institute (VKI) Longshot at a freestream Mach number of 14 and freestream unit Reynolds number of Re =1.5 – 3.5 ·106, the VKI H3 Mach-6 at M =6 and Re =3 ·107, and the Notre Dame arc-heated tunn...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2022-2340.vid A fast pressure-sensitive paint (PSP) has been applied to a cylindrical duct with a conical intake in Mach 6 flow. The duct's internal surface pressure distribution was imaged through a transparent acrylic piece that made up a portion of the duct. Preliminary time-resolved PSP data is...
Article
Full-text available
The global surface pressure was measured on a 7° half-angle circular cone/flare model at a nominally zero angle of attack using pressure-sensitive paint (PSP). These experiments were conducted to illustrate fast PSP’s usefulness and effectiveness at measuring the unsteady structures inherent to hypersonic shock-wave/boundary-layer interactions (SWB...
Article
Full-text available
Global surface pressure measurements have been carried out on a 7° half-angle circular cone/flare model at nominally zero angle of attack using pressure-sensitive paint (PSP). These experiments were conducted to illustrate the PSP technique’s usefulness and effectiveness at measuring the unsteady structures inherent to hypersonic shock-wave/boundar...
Article
Stagnation-point heat flux was measured on 7 • half-angle circular cones with spherical nose diameters of 5, 10, and 25 mm using infrared thermography in hypersonic flow. All models were machined from polyether ether ketone (PEEK). A nominal freestream Mach number of 6 with varying initial stagnation conditions allowed for testing at length Reynold...
Article
Hypersonic International Flight Research Experimentation 5 (HIFiRE-5) is a hypersonic flight-test experiment designed to investigate the aerothermodynamics of a 3-D geometry. The vehicle is an elliptic cone with a 2:1 aspect ratio and 2.5 mm nose radius. The HIFiRE-5b achieved a Mach number of 7.7–7.9 and freestream unit Reynolds number of 5⋅106/m...
Article
The purpose of this research was to design, fabricate, and test a plasma-based active flow-control system to accelerate and delay crossflow-induced boundary-layer transition on a cone at an angle of attack at Mach 6 under quiet-flow conditions. A model with interchangeable nosetips was designed and fabricated from stainless steel, polyether ether k...
Article
Analysis of the hypersonic cross-flow instability with experimental wavenumber distributions - Volume 883 - Harrison B. Yates, Matthew W. Tufts, Thomas J. Juliano
Article
Time-resolved surface temperature measurements have been carried out on a 7° half-angle circular cone/flare model in the Air Force Research Laboratory’s Mach-6 Ludwieg Tube using infrared thermography. Measurements were performed at zero angle of attack on a total of 16 different nose bluntness/flare angle geometries at three different freestream u...
Article
Results from experimental, theoretical, and computational efforts are combined in a comprehensive review to summarize the improved understanding of the underlying physical mechanisms causing second-mode dominated laminar–turbulent transition on a 3 m circular-arc flared cone for the Boeing/U.S. Air Force Office of Scientific Research Mach 6 Quiet T...
Article
HIFiRE-5 is a hypersonic flight-test experiment designed to investigate the aerothermodynamics of a three-dimensional geometry. The vehicle is an elliptic cone with a 2:1 aspect ratio and 2.5 mm nose radius. The HIFiRE-5b achieved a Mach number of 7.7 to 7.9 and freestream unit Reynolds number of 5⋅106/m to 50⋅106/m during descent. Heat flux was ca...
Article
The principal goal of the Hypersonic International Flight Research Experimentation (HIFiRE) flight 5 is to measure hypersonic boundary-layer transition on a three-dimensional body. This paper presents measurements of heat flux and boundary-layer transition in the Boeing/U.S. Air Force Office of Scientific Research Mach-6 Quiet Tunnel. This facility...
Article
Full-text available
A measurement technique for identifying lee-side crossflow-induced boundary-layer separation on a blunt \(7^{\circ }\) half-angle circular cone at high angle of attack has been developed and tested. Previous work has shown that local minima in root-mean-squared (rms) pressure fluctuations on the surface are good identifiers of separation. These sur...
Article
Full-text available
Hypersonic International Flight Research Experimentation (HIFiRE)-5 is a hypersonic flight-test experiment designed to investigate the aerothermodynamics of a three-dimensional geometry. The vehicle is a 7 deg minor-axis half-angle elliptic cone with a 2∶1 aspect ratio and 2.5 mm nose radius. The HIFiRE-5b achieved a Mach number of 7.7–7.9 and a fr...
Article
Full-text available
The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight-test program executed by the U.S. Air Force Research Laboratory and the Australian Defence Science and Technology Group, including flight, ground test, and computation. HIFiRE flights one and five (HIFiRE-1 and HIFiRE-5, respectively) were devoted t...
Article
Full-text available
Laminar and turbulent flow computations are carried out for a range of conditions bounding the flight conditions of the Hypersonic International Flight Research and Experimentation (HIFiRE) 5b laminar–turbulent transition research flight. The resulting computational database is used to create an interpolant for heat transfer and pressure in the fol...
Conference Paper
This paper summarizes the efforts to improve the understanding of boundary-layer transition caused by the second-mode instability on a 3-meter circular arc flared cone geometry by combining experimental and computational results. With a nominally smooth wall at unit Reynolds numbers from 7.3×10^6/m to 12×10^6/m, a hot-cold-hot heating pattern compo...
Article
Numerical simulations were conducted to optimize the shape and wall-temperature distribution of the Notre Dame Mach 6 quiet tunnel nozzle. The design was optimized by minimizing the overall nozzle length while maintaining sufficiently low disturbance amplification factors and uniform flow at the exit plane. The Boeing Computational Fluid Dynamics f...
Article
The Hypersonic International Flight Research Experimentation program is a hypersonic flight test program. It successfully measured the three-dimensional transition front on a cone at angle of attack in hypersonic flight during its reentry. The test article consisted of a nonablating, 7 deg half-angle, axisymmetric cone with a small bluntness of 2.5...
Article
The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratory and Australian Defence Science and Technology Organisation. The principal goal of HIFiRE flight five is to measure hypersonic boundary-layer transition on a three-dimensional body. The HIFiR...
Article
The Hypersonic International Flight Research Experimentation (HIFiRE-5) is a hypersonic flight test vehicle designed to investigate the aerothermodynamics of a three-dimensional geometry. It is a 7-deg minor-axis half-angle elliptic cone with a 2:1 aspect ratio and 2.5mm nose radius. The flight test occurred in April2012, but the upper stage of the...
Conference Paper
The HIFiRE-1 is a 7-degree half-angle circular cone with a 2.5-mm nose radius. A successful HIFiRE-1 flight experiment was carried out in March 2010. Due to an anomaly in the exoatmospheric pointing maneuver, the reentry angle of attack was higher than anticipated (5–15 degrees instead of near zero). A test campaign in the H2K hypersonic wind tunne...
Article
Full-text available
Image blurring is a problem encountered when pressure-sensitive paint is applied to rotating surfaces such as rotorcraft blades. The issue is particularly problematic near the leading and trailing edges of the blade; these are the regions where the impact of blurring is the most significant, yet they also contain the most valuable pressure informat...
Conference Paper
The HIFiRE-1 is a 7-degree half-angle circular cone with a 2.5-mm nose radius. A successful HIFiRE-1 flight experiment was carried out in March 2010. Due to an anomaly in the exoatmospheric pointing maneuver, the reentry angle of attack was higher than anticipated (5–15 degrees instead of near zero). A test campaign in the H2K hypersonic wind tunne...
Article
Full-text available
Unsteady pressure-sensitive paint (PSP) measurements were acquired on an articulated model helicopter rotor of 0.26 m diameter in edgewise flow to simulate forward flight conditions. The rotor was operated at advance ratios (free stream velocity normalized by hover tip speed) of 0.15 and 0.30 at a cycle-averaged tip chord Reynolds number of 1.1 × 1...
Conference Paper
Full-text available
During the descent phase of the transition flight experiment HIFiRE-1 the angle of attack was higher than expected, since an anomaly occurred in the exoatmospheric pointing maneuver. All pre-flight ground tests were carried out at angles of attack below 6°. Therefore several post-flight experiments at high angles of attack were performed in the hyp...
Conference Paper
The HIFiRE-1 is a 7-degree half-angle circular cone with a 2.5-mm nose radius. A successful HIFiRE-1 flight experiment was carried out in March 2010. Due to an anomaly in the exoatmospheric pointing maneuver, the reentry angle of attack was higher than anticipated (5-15 degrees instead of ≈ 0). A test campaign in the H2K hypersonic wind tunnel at D...
Conference Paper
The HIFiRE-5 is a 7-degree minor-axis half-angle elliptic cone with a 2.5-mm nose radius and 2:1 aspect ratio. Its flight test occurred in April 2012. The upper stage of the sounding rocket failed to ignite, resulting in a peak Mach number of about 3 instead of the target of 7. The instrumentation (almost 300 thermocouples and 50 pressure transduce...
Article
Spatially temporally resolved unsteady pressure fields on a surface of a hemisphere-on-cylinder turret with either a flat or a conformal window with realistic features such as gaps and ‘‘smile’’ cutouts were characterized using fast-response pressure-sensitive paint at M = 0.33 for several window viewing angles. Various statistical properties of pr...
Article
Full-text available
This paper describes the development of a two-color fast-responding pressure-sensitive paint with temperature correction capability. This paint uses a platinum porphyrin compound as the pressure sensor with perylene as the reference sensor and a laser dye added to adjust the spectrum distribution and temperature sensitivity of the reference channel...
Conference Paper
Spatially-temporally-resolved unsteady pressure fields on a surface of a hemisphere-on-cylinder turret with either a flat- or a conformal-window were characterized using fast-response pressure sensitive paint at M = 0.33 for several window viewing angles. Various statistical properties of pressure fields were computed and geometry effects on unstea...
Conference Paper
Fast-response pressure-sensitive paint (PSP) was used in this work for a study of the unsteady surface pressures resulting from the complex separated flow over a hemispherical turret model. The turret includes several distinct features such as a flat window and crevices that are based on functional requirements, but also introduce interesting addit...
Conference Paper
The spatially-temporally-resolved pressure field on a surface of a hemisphere-on-cylinder optical turret was characterized in a wind tunnel at M = 0.33 using fast-response Pressure Sensitive Paint (PSP), simultaneously with 8 pressure sensors. A sparse unsteady pressure field was also obtained in-flight for subsonic speeds of M = 0.5 on the Airborn...
Conference Paper
The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratory (AFRL) and Australian Defence Science and Technology Organisation (DSTO). HIFiRE flight five flew in April 2012. Principle goals of this flight were to measure hypersonic boundary-layer tran...
Conference Paper
Full-text available
Blurring is a problem encountered when pressure-sensitive paint (PSP) is applied to rotating surfaces such as rotorcraft blades. The issue is particularly problematic near the leading and trailing edges of the blade: these are the regions where the impact of blurring is the most significant, yet they also contain the most valuable pressure informat...