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Boundary-Layer Detection at Cryogenic Conditions Using Temperature Sensitive Paint Coupled with a Carbon Nanotube
Kyle Z Goodman1, William E Lipford2, Anthony Neal Watkins3
1Analytical Mechanics Associates, Inc., 18 Langley Blvd., MS 493, Hampton, VA 23669, USA. kyle.z.goodman@nasa.gov.
Sensors (Basel, Switzerland)
|December 6, 2016
Summary
Researchers developed a new carbon nanotube paint for cryogenic wind tunnels, enabling accurate flow transition detection on aircraft models at temperatures as low as 77 K.
Area of Science:
- Aerospace Engineering
- Materials Science
- Fluid Dynamics
Background:
- Flow transition detection is crucial for aircraft development.
- Infrared thermography is limited in cryogenic wind tunnels.
- Temperature-sensitive paint is an alternative but has limitations.
Purpose of the Study:
- To modify carbon nanotube (CNT) paint for cryogenic applications.
- To enable flow transition detection at temperatures below 130 K.
- To compare the modified CNT paint with traditional methods.
Main Methods:
- A modified CNT paint system using a polyurethane binder was developed.
- The system was tested on a Natural Laminar Flow model in a cryogenic facility.
- Flow transition was visualized at temperatures ranging from 200 K to 110 K.
Main Results:
- The modified CNT paint operated successfully down to 77 K.
- Flow transition was visualized effectively in cryogenic conditions.
- Results were comparable to traditional temperature step methods.
Conclusions:
- The modified CNT paint is a viable method for flow transition detection in cryogenic wind tunnels.
- This technique overcomes the limitations of previous CNT paint systems.
- It offers a reliable alternative for evaluating future vehicle concepts.
