PRESSURE- AND TEMPERATURE-SENSITIVE PAINTS FOR HIGH-SPEED AERODYNAMIC DIAGNOSTICS
Abstract
High-speed aerodynamic phenomena have not been fully understood due to the limitation in high-fidelity experimental data that leads to numerical and analytical modeling. For an instance, it can be seen in hypersonic speed for a space re-entry object. Herein, pressure- and temperature-sensitive paints (P/TSPs) are proposed to acquire experimental data in spatiotemporal manner. The proposers have demonstrated the feasibility of P/TSP in “cold” high-speed flow where the stagnation temperature is less than 500 K. The focus on the development of P/TSPs is to exceed the temperature to a “high” temperature around 1500 K. If successful, high-fidelity spatiotemporal measurement in pressure and temperature can be achieved that will be used to understand high-speed aerodynamics in high-temperature environment. P/TSP developments in static conditions are focused in the first year and dynamic response will be studied for the P/TSPs in the consecutive year that give promising characteristics in the static test. Demonstration of spatiotemporal measurement will be performed in a “high” temperature high-speed flow such as using the Arc Heated Tunnel at the University of Notre Dame in the last year.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Apr 20, 2023
- Source ID
- FA23862214032
Entities
People
- Hirotaka Sakaue
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Notre Dame