DoW/USAF · DoW SBIR 2027 BAA

DAF27BZ01-NV005 — Luminescence-Based Surface Measurement Technique for Simultaneous Pressure and Temperature Measurements within Non-Oxygen Based Hypersonic Ground Test Facilities

Open | released 2026-10-07 | opens 2026-10-28 | closes 2026-11-25 | CMMC Level 2 (Self), SBIR

DSIP topics app (search DAF27BZ01-NV005) · no SBIR.gov page at the moment

Keywords: hypersonic, instrumentation, non-intrusive, wind-tunnel

Technology areas: Sensors

Objective

Develop and validate a non-intrusive, luminescence-based surface measurement technique for simultaneous pressure and temperature measurements within non-oxygen-based hypersonic ground test facilities.

Description

Within aerodynamic testing, pressure sensitive paint (PSP) provides crucial global surface pressure data that is utilized in calculating aerodynamic loads [1] and identifying small scale features within the flow. The working principle behind PSP involves luminophores that fluoresce at an intensity inversely proportional to the number of oxygen molecules present i.e., oxygen quenching [2]. While these paints/luminophores have been sufficiently researched, the use-case of these paints is severely limited due to the requirement of oxygen in the flow field. Advanced hypersonic wind tunnels such as the blowdown facility at AEDC Tunnel No. 9 which utilizes nitrogen as the working fluid, are unable to utilize PSP to capture global pressure data with this method and are therefore severely limited to discrete measurement techniques. It is required that a novel technique be developed to capture simultaneous global pressure and temperature measurements in nonoxygen-based hypersonic wind tunnels.

Phase I

Phase I efforts outline technique/paint development and establish feasibility through thorough characterization of the paint properties/sensitivities and reduction process using benchtop testing and testing within small-scale (educational) supersonic/hypersonic facilities.

Phase II

Phase II efforts outline full scale prototype demonstrations within a hypersonic test facility through either test probes or full-scale model testing on a well-known/standard test article. The completed technique and refined data reduction process will be delivered at this phase.

Phase III / dual use

The technique can be marketed for non-intrusive simultaneous pressure/temperature measurements in non-oxygen-based high-speed wind tunnels.

References

Gregory, J. W., Asai, K., Kameda, M., Liu, T., & Sullivan, J. P. (2008). A review of pressure-sensitive paint for high-speed and unsteady aerodynamics. Proceedings of the institution of mechanical engineers, part G: journal of aerospace engineering, 222(2), 249-290.
Sellers, M. E. (2000, June). Application of pressure sensitive paint for determining aerodynamic loads on a scale model of the F-16C. In 21st aerodynamic measurement technology and ground testing conference (p. 2528).

Copied from the official source and may be out of date. Confirm dates and requirements in the official solicitation.