Application of Pressure- and Temperature-Sensitive Paint in a Hypersonic Double Ramp Flow

  • L. Yang
  • E. Erdem
  • K. Kontis
Conference paper

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.

Keywords

Schlieren Image Pressure Sensitivity Reattachment Line Ramp Angle Thermal Insulation Layer 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. 1.
    Liu, T., Sullivan, J.P.: Pressure and Temperature Sensitive Paints. Springer, Heidelberg (2005)Google Scholar
  2. 2.
    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)Google Scholar
  3. 3.
    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)CrossRefGoogle Scholar
  4. 4.
    Raju, C., Viswanath, P.R.: Pressure-sensitive paint measurements in a blowdown wind tunnel. J. Aircraft 42(4), 908–915 (2005)CrossRefGoogle Scholar
  5. 5.
    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)CrossRefGoogle Scholar
  6. 6.
    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)CrossRefGoogle Scholar
  7. 7.
    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)CrossRefGoogle Scholar
  8. 8.
    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)Google Scholar
  9. 9.
    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)CrossRefGoogle Scholar
  10. 10.
    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)CrossRefGoogle Scholar
  11. 11.
    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)CrossRefGoogle Scholar
  12. 12.
    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)Google Scholar
  13. 13.
    Sakaue, H., Matsumura, S., Schneider, S.P., Sullivan, J.P.: Anodized Aluminum Pressure Sensitive Paint for Short Duration Testing. AIAA-2002-2908 (2002)Google Scholar
  14. 14.
    Erdem, E., Yang, L., Kontis, K.: Drag reduction by energy deposition in hypersonic flows. AIAA 2009-7347 (2009)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • L. Yang
    • 1
  • E. Erdem
    • 1
  • K. Kontis
    • 1
  1. 1.The School of MACEThe University of ManchesterManchesterUK

Personalised recommendations