Introduction
Pressure- and Temperature-Sensitive Paint (PSP, TSP) was considered as novel nonintrusive flow diagnostics which can provide quantitative global surface pressure and temperature mapping on complex geometry with high spatial resolution [1]. PSP and TSP has been mainly applied in transonic flows [2, 3, 4], supersonic flows [5, 6, 7] and low speed flows [8]. The application of PSP and TSP has been extended to hypersonic flow [9, 10, 11] but not reported as many as at the other flow conditions. The testing condition is challenging for PSP measurement in hypersonic mainly based on the following reasons. The critical aerodynamic heating will cause considerable error for the PSP measurement because of thermal quenching mechanism.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
References
Liu, T., Sullivan, J.P.: Pressure and Temperature Sensitive Paints. Springer, Heidelberg (2005)
Asai, K., Nakakita, K., Kameda, M., Teduka, K.: Recent topics in fast-responding pressure-sensitive paint technology at National Aerospace Laboratory. In: International Congress on Instrumentation in Aerospace Simulation Facilities, pp. 25–36 (2001)
Dowgwillo, R.M., Morris, M.J., Donovan, J.F., Benne, M.E.: Pressure sensitive paint in transonic wind-tunnel testing of the F-15. J. of Aircraft 33(1), 109–116 (1996)
Raju, C., Viswanath, P.R.: Pressure-sensitive paint measurements in a blowdown wind tunnel. J. Aircraft 42(4), 908–915 (2005)
Hubner, J.P., Carroll, B.F., Schanze, K.S., Ji, H.F.: Pressure-sensitive paint measurements in a shock tube. Exp. in Fluids 28(1), 21–28 (2001)
Klein, C., Engler, R.H., Henne, U., Sachs, W.E.: Application of pressure-sensitive paint for determination of the pressure field and calculation of the forces and moments of models in a wind tunnel. Exp. in Fluids 39(2), 475–483 (2005)
Zare-Behtash, H., Gongora-Orozco, N., Kontis, K., Holder, S.J.: Application of novel pressure-sensitive paint formulations for the surface flow mapping of high-speed jets. Exp. Therm. Fluid Sci. 33(5), 852–864 (2009)
Watkins, A.N., Oglesby, D.M., Leighty, B.D., Jordan, J.D.: Low Speed Pressure Sensitive Paint Measurements-Requirements and Applications. In: Proceedings of the International Instrumentation Symposium, vol. 47, pp. 203–214 (2001)
Hirschen, C., Gulhan, A., Beck, W.H., Henne, U.: Experimental study of a scramjet nozzle flow using the pressure-sensitive- paint method. J. Prop. Power 24(4), 662–672 (2008)
Hirschen, C., Gulhan, A., Beck, W.H., Henne, U.: Measurement of flow properties and thrust on scramjet nozzle using pressure-sensitive paint. J. Prop. Power 25(2), 267–280 (2009)
Hubner, J.P., Carroll, B.F., Schanze, K.S., Ji, H.F., Holden, M.S.: Temperature- and pressure-sensitive paint measurements in short-duration hypersonic flow. AIAA J. 39(4), 654–659 (2001)
Nakakita, K., Yamazaki, T., Asai, K., Teduka, N., Fuji, A., Kameda, M.: Pressure Sensitive Paint Measurement in a Hypersonic Shock Tunnel. AIAA-2000-2523 (2000)
Sakaue, H., Matsumura, S., Schneider, S.P., Sullivan, J.P.: Anodized Aluminum Pressure Sensitive Paint for Short Duration Testing. AIAA-2002-2908 (2002)
Erdem, E., Yang, L., Kontis, K.: Drag reduction by energy deposition in hypersonic flows. AIAA 2009-7347 (2009)
Author information
Authors and Affiliations
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2012 Springer-Verlag Berlin Heidelberg
About this paper
Cite this paper
Yang, L., Erdem, E., Kontis, K. (2012). Application of Pressure- and Temperature-Sensitive Paint in a Hypersonic Double Ramp Flow. In: Kontis, K. (eds) 28th International Symposium on Shock Waves. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-25688-2_115
Download citation
DOI: https://doi.org/10.1007/978-3-642-25688-2_115
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-25687-5
Online ISBN: 978-3-642-25688-2
eBook Packages: EngineeringEngineering (R0)