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Pressure and Temperature Sensitive Paints

Part of the book series: Experimental Fluid Mechanics ((FLUID))

Abstract

Quantitative measurements of surface pressure and temperature in wind tunnels and flight testing are essential for understanding the aerodynamic performance and heat transfer characteristics of flight vehicles. Surface pressure data are required to determine the distribution of aerodynamic load for the design of a flight vehicle, while surface temperature data are used to estimate heat transfer on the vehicle surface. Surface pressure and temperature measurements provide critical information on important flow phenomena such as shocks, flow separation, boundary-layer transition, and vortices. In addition, experimental pressure and temperature data are necessary for the validation and verification of computational fluid dynamics (CFD) codes. Traditionally, in wind tunnel testing, surface pressure is measured by utilizing a pressure tap (or orifice) at a location of interest connected through a small tube to a pressure transducer (Barlow et al. 1999). Hundreds of pressure taps are needed to obtain a crude pressure field on a complex aircraft model. Manufacturing, tubing, and preparing such a model for wind tunnel testing are very labor-intensive and costly. For thin wings and blades, the installation of pressure taps is difficult. Furthermore, pressure measurements at discrete taps ultimately limit the spatial resolution of data such that some details of a complex flow field cannot be revealed. Similarly, a surface temperature field is traditionally measured using temperature sensors (such as thermocouples and resistance thermometers) distributed at discrete locations (Moffat 1990).

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Authors and Affiliations

  1. Department of Mechanical and Aerospace Engineering, Western Michigan University, Kalamazoo, MI, USA

    Tianshu Liu

  2. School of Aeronautics and Astronautics, Purdue University, West Lafayette, IN, USA

    John P. Sullivan

  3. Department of Aerospace Engineering, Tohoku University, Sendai, Japan

    Keisuke Asai

  4. German Aerospace Center DLR, Institute of Aerodynamics and Flow Technology, Göttengen, Germany

    Christian Klein

  5. Department of Mechanical Engineering, Aichi Institute of Technology, Toyota, Aichi, Japan

    Yasuhiro Egami

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  5. Yasuhiro Egami
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Liu, T., Sullivan, J.P., Asai, K., Klein, C., Egami, Y. (2021). Introduction. In: Pressure and Temperature Sensitive Paints. Experimental Fluid Mechanics. Springer, Cham. https://doi.org/10.1007/978-3-030-68056-5_1

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