Structures

Case Western University
Miami University
NASA Glenn Research Center
Plum Brook Station
The Ohio State University
University of Akron
University of Dayton

Case Western University

Case Low Speed Research Wind Tunnel

  • Provides very low free stream turbulence levels
  • The tunnel is completely modular, allowing a variety of different experimental configurations to be realized, greatly extending the tunnel’s functionality.

Laser Flow Diagnostics Laboratory

  • State-of-the-art Particle Image Velocimetry (PIV) equipment
  • Phase Doppler and laser Doppler anemometers
  • Modern data acquisition and analysis equipment including PCs
  • Clear centrifugal slurry flow pump loop and heart pump loop

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Miami University

Mechanical Vibrations and Dynamic Systems Laboratory

  • 10 PC Workstations and Laptops with Matlab and Data Acquisition toolbox
  • Vibration Isolation Station with NX 5.0
  • Crossbow wireless sensor network with Matlab / Simulink
  • Modal Impact Hammer with Working Model
  • MB Dynamics Modal Shaker with Amplifier, NI-DAQ

Dynamic Systems Laboratory

  • 7 AB Compact Logix Units with Logix 5000 Software
  • 2 Feedback Servo Trainers
  • PID Heating System

Quality Planning and Control (QPC) Laboratory

  • Comparator, Optical with WINEDGE
  • 2 CMM, Brown and Sharpe and Tooling with CMM Software
  • Micrometers, Calipers
  • 4 Statistical Process Experiment Tool, QUINCUNX

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NASA Glenn Research Center

1′x1′ Supersonic Wind Tunnel (1×1)

  • Used to conduct fundamental research in supersonic and hypersonic fluid mechanics, supersonic-vehicle-focused research and detailed benchmark quality experiments for CFD code validation
  • Uses 10 discrete airspeeds between Mach 1.3 and 6.0

2.2 Second Drop Tower

Used to study the effects of microgravity on physical phenomena such as combustion and fluid dynamics, and to develop new technology for future space missions.

8′x6′ Supersonic Wind Tunnel (8×6)

  • Provides researchers with the opportunity to explore higher speed regions of flight
  • Able to reach speeds of up to Mach 2
  • Can also operate at very low speeds from 0 to Mach 1
  • Operates either in an aerodynamic closed-loop cycle, testing aerodynamic performance, or in a propulsion open-loop cycle that tests live fuel burning engines and models

9′x15′ Low-Speed Wind Tunnel (9×15)

Providing airspeeds from 0 to 175 mph, this facility has unique and nationally recognized capabilities to evaluate aerodynamic performance and acoustic characteristics of nozzles, inlets, and propellers, and investigate hot gas re-ingestion of advanced STOVL concepts.

Abe Silverstein Supersonic Wind Tunnel (10×10)

  • Specifically designed to test supersonic propulsion components such as inlets and nozzles, propulsion system integration, and full-scale jet and rocket engines.
  • Can operate as a closed-loop system (aerodynamic cycle) or open-loop system (propulsion cycle), reaching test section speeds of Mach 2.0 to 3.5 and very low speeds from 0 to Mach 0.36

Icing Research Tunnel (IRT )

  • Instrumental in developing and testing ice protection systems for piston- and propeller-driven aircraft
  • Can produce continuous airspeeds from 50 to 350 knots and temperatures as low as -25°F year-round, controllable to within one degree Fahrenheit
  • Supercooled water droplets between 15 and 50 microns with water content controllable between 0.2 and 2.5g/m3 can be produced to form an icing cloud.

Structural Dynamics Laboratory (SDL)

Performs tests to verify the survivability of a component or assembly when exposed to vibration stress screening or a controlled simulation of the actual flight or service vibration environment.

Structural Static Laboratory (SSL)

  • Structural testing is performed to verify the structural integrity of space flight and ground test hardware.
  • Testing is also performed to verify the finite element analysis by measuring stiffness and induced stress at points in a test article.
  • A structural test can be used to verify the modes of failure of a design when exposed to simulated service loads.
  • The modes of failure include but are not limited to the following: leak before burst, buckling, ultimate failure, yield or excessive deflection.
  • The test lab is also outfitted with a tensile test machine that can be used to develop mechanical properties, at up to 1300°F

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Plum Brook Station

Hypersonic Tunnel Facility (HTF)

  • A blow-down, non-vitiated, free jet wind tunnel that is capable of simulating Mach 5, Mach 6, and Mach 7 true enthalpy conditions
  • The primary performance differentiator between the HTF and other hypersonic free jet facilities is its non-vitiated (clean) flow.

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The Ohio State University



Experimental Wind Tunnel Facilities

  • Subsonic: 3’ x 5’ Open Circuit Low Turbulence Wind Tunnel
    • Top speed 150 ft/sec
    • Steady and Unsteady Test Equipment
    • Pressure, Force and Moment Measurements used for many airfoil, wind energy aircraft studies
  • Transonic: 6” x 22” Blowdown Wind Tunnel
    • Airfoil Test – Surface Pressure and Wake Survey
      • M = 0.2 – 1.05,
      • Re/ft = 1 x 106 to 24 x 106
      • On-line Data

6” x 6” Heated Blowdown Tunnel

  • M = 0.6 – 0.8
  • Used for Heat Transfer Measurements on Turbine Blades

6” Diameter Blowdown Wind Tunnel (Now in Assembly)

  • Hypersonic
  • Mach 6
  • P0 = 600 psia T0 = 10000F
  • To be used in NANOTECH Studies

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University of Akron


Physical Testing

  • Instron Tensile Test Machine Model 5567 – Load Cell Range to 6500 Lbs
  • Alpha Technologies T-10 and T-2000 Tensiometers
  • Rex Digital Durometers with Computer Interface – Shore A, C

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University of Dayton


Structural Failure Analysis Laboratory

  • Provides solutions to mechanical component and airframe failures, including mechanical and metallurgical joining of aluminum and advanced nickel-based, titanium-based, and refractory metals and nonmetallic and composite materials

Structural Test Laboratory

  • Closed-loop, servo-hydraulic test systems for superior control during testing
  • Load frames and T-slot tables for a wide variety of load configurations
  • Uni-axial loading up to 220,000 lb
  • Test speeds up to 300 in/sec closed loop, and 1,000 in/sec monotonic
  • Torque from 25 in-lb to 75,000 in-lb
  • Torsional test rates of 500°/sec up to 5,000 in-lb and 100°/sec up to 70,000 in-lb
  • Environmental chambers for temperatures from -320°F to 2,000°F
  • Testing environments such as lab air, high humidity air, corrosive atmospheric environments, and solution baths
  • Pressures from ambient to vaccuum (10-5 torr)
  • Multi-axial testing
  • Instrumentation:
    • axial and torsional loadcells
    • force washers
    • strain gauges
    • linear variable differential transformers (LVDTs)
    • pressure transducers
    • mechanical and optical extensometers
    • traveling microscopes
    • thermocouples
    • oscilloscopes
    • precision voltmeters
    • micrometers
    • callipers
    • monitoring for up to 10 high speed strain gages
    • high speed digital acquisition up to 32 channels
    • Labview(R) instrumentation and programming expertise

Vibration Damping and Modal Analysis

  • Modal Analysis/Operational Deflection Shapes: field-portable systems to determine the dynamic characteristics of structures and acoustic environments under real operating conditions.
  • Passive Damping System Design and Validation: proven process that combines experimental modal analysis and finite element analysis to optimize damping system performance to reduce vibratory stress levels.
  • Damping Materials Characterization: unique capability to develop and characterize new damping materials across a broad range of frequencies and temperatures.
  • Dynamic Testing: wide variety of dynamic testing equipment: from servo-hydraulic systems to a 5000 lbf-3000 Hz shaker with appropriate accelerometer and strain gage instrumentation, to assess structural integrity under combined cyclic thermal and mechanical loading.

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