Trade.Information

Topic Name: Wind tunnel experimentation

Category: Mechanical

Research persons: Iain D BoydProfessor
ADDRESS: 3012 FXB
PHONE: (734)615-3281
EMAIL: iainboyd@umich.edu

PERSONAL WEBPAEG: http://www-personal.engin.umich.edu/~iainboyd/

Location: Department of Aerospace Engineering, University of Michigan, Ann Arbor
FXB Building 1320 Beal Avenue Ann Arbor, Michigan 48109-2140
, United States

Details

The University of Michigan Department of Aerospace Engineering can boast among its many resources 10 wind tunnels for instructional and research work. These tunnels are run by the Gas Dynamics Laboratories (GDL), which consists of a closely integrated group of professors, technicians, and students within the Aerospace Department. The function of this group is to conduct experimental and theoretical research, teach lecture and lab courses, and to guide PhD theses. The research interests of the group include a wide range of fluid dynamic, combustion, and propulsion problems, much of which is based on wind tunnel experimentation. Below is a list of the wind tunnel facilities that the department offers.
Subsonic Low Turbulence 5 ft x 7 ft Wind Tunnel
Subsonic 2 ft x 2 ft Instructional Tunnel
Variable Mach Number Supersonic Wind Tunnel
Edward A. Stalker 2 ft x 2 ft Subsonic Wind Tunnel
- (5) Subsonic 6 inch Wind Tunnels for Student Classroom Laboratories
Mach 2 Induced Flow Supersonic Wind Tunnel


Subsonic Low Turbulence 5 ft x 7 ft Wind Tunnel
The subsonic tunnel was built in 1956 in a joint effort with the U.S. Air Force. It was initially designed to study the effects of gusts on aircraft, but has since been upgraded to suit a variety of applications. It is now fully owned by the university, and is used for education and research.
The facility is a closed circuit, single return tunnel with a 7 ft. wide by 5 ft. high by 25 ft. long test section. With a contraction ratio of 15:1 and the use of multiple diffusion screens, very low turbulence is achievable. The tunnel is capable of continuous operation at velocities of over 150 mph. Large windows on the side and top of the test section allow for excellent model viewing.
Force and moment data are obtained from a below floor balance system capable of supporting models having gross weights of over 300 pounds. It resolves all six force and moment components to an accuracy of one part in 3,000, with less than 0.1% interaction error.
The wind tunnel facility also has instrumentation for the measurement and recording of operating pressures, the angle of attack or angle of yaw, tunnel static pressure, dynamic pressure and temperatures. A computer/data acquisition system is used to average and record the results. Boundary layer velocity profiles on the tunnel walls or on the model can be obtained via Pitot tubes or hot wire probes.
This Laboratory has extensive facilities for flow visualization. The introduction of helium-filled bubbles or smoke into the flow, small vanes mounted on a given surface to show flow direction, coating the model with oil, and the use of tufts are some of those methods. Photographic systems from still to motion (5 frames/sec up to 1 million frames/sec) are available. Video cameras and recorders are also available.
Specifications:
Design:
- Closed return loop
335' diameter at center line
Test Section:
- 7 ft wide x 5 ft high x 25 ft long
Maximum speed:
- 170 mph with minimal blockage
- 150 mph with 3 square foot blockage
Contraction Ratio 15:1
Power Source: 10 blade fan driven by 1200 HP motor generator set
Balance type: 6 component pyramidal
Load Ranges :
- Lift Force-600 lb.
- Drag Force-120lb.
- Side Force-80lb.
Pitch Moment....3,000 in.lb.
Roll Moment....3,000 in.lb.
Yaw Moment....1,800 in.lb.

Variable Mach Number Supersonic Wind Tunnel
Specifications:
Nozzle Size - 4 x 4 inch, Mach range - 1.3 to 4.6:: Design Intermittent - Flow blowdown type in which air is caused to flow from atmospheric down to an evacuated tank.
This tunnel was designed under an Air Force Contract to study variable Mach number nozzle contours. T he facility continues to be used for instructional and research purposes. A schlieren optical system is mounted on an overhead boom which in turn is mounted on a rail system. With this arrangement, schlieren photographs can be made at any position along the window areas.
Edward A. Stalker 2 ft x 2 ft Subsonic Wind Tunnel
Specifications:
Design: - Open circuit Eiffel type
Dimensions:
- length 27 ft, 8" - height 8 ft - width 7 ft
Test section:
- 24 in x 24 in x 48 in long ; - 1" clear, GM grade acrylic Plexiglas
Maximum Speed:
- 160 fps (110 mph)
Balance: : - 6 component sting type Contractoin ratio:: - 6.25:1 Turbulence: : - less than 0.25% Maximum Loads:: - Lift Force - 50 lb.; - Drag Force - 50 lb.; - Side Force - 50 lb. :: Pitch Moment - 75 in-lb.; Roll Moment - 75 in-lb.; Yaw Moment - 25 in-lb