Skip to main content
SpringerLink
Log in

Simultaneous PSP and TSP measurements of transient flow in a long-duration hypersonic tunnel

  • Research Article
  • Published:
Experiments in Fluids Aims and scope Submit manuscript

Abstract

The current work presents simultaneous measurements of transient flow using fast-responding pressure- and temperature-sensitive paints in a long-duration hypersonic tunnel; the pressure, temperature and heat flux fields were obtained on a standard model (HB-2) at Ma = 5. Fast PSP and TSP were applied symmetrically on the model with low thermal conductivity. Both coatings were illuminated by a UV-LED, and unsteady pressure and temperature data were recorded at 500 Hz using a high-speed camera. Time-dependent temperature correction was applied on the PSP data based on the TSP results, while the heat flux was calculated from the time-resolved temperature fields using a 1D semi-finite heat conduction model. The temperature-induced errors in PSP data were effectively removed by the current compensation method. The pressure and heat flux results showed good agreement with the reference data from previous studies. The key events throughout the hypersonic tunnel run were captured by the unsteady PSP/TSP data, including the tunnel start-up, the flow build-up, the steady flow period and the tunnel shutdown. The differences caused by the change of attack angle were also clearly recognized. The current PSP/TSP system has shown great potential for unsteady flow diagnostics in hypersonic flows.

This is a preview of subscription content, log in via an institution to check access.

Access this article

Log in via an institution

Price excludes VAT (USA)
Tax calculation will be finalised during checkout.

Instant access to the full article PDF.

Institutional subscriptions

Fig. 1
Fig. 2
Fig. 3
Fig. 4
Fig. 5
Fig. 6
Fig. 7
Fig. 8
Fig. 9
Fig. 10
Fig. 11
Fig. 12
Fig. 13
Fig. 14
Fig. 15
Fig. 16
Fig. 17
Fig. 18
Fig. 19
Fig. 20
Fig. 21
Fig. 22
Fig. 23

Similar content being viewed by others

Abbreviations

C p :

Pressure coefficient

c :

Specific heat

h :

Depth from the model surface

I :

Intensity

I PSP :

Intensity of PSP

I PSP_ref :

Intensity of PSP at reference condition

I TSP :

Intensity of TSP

I TSP_ref :

Intensity of TSP at reference condition

I ref :

Intensity at reference condition

K :

Ratio of temperature sensitivity between PSP and TSP

k :

Heat conductivity

L :

Length of the model

Ma:

Mach number

P :

Pressure

P ref :

Pressure at reference condition

P 0 :

Stagnation pressure

P ∞ :

Static pressure

q :

Heat flux

q err :

Heat flux difference between two adjacent iterations

q 0 :

Heat flux at stagnation point

R :

Radius of the model

Re :

Reynolds number

r :

Coordinate in radial direction

T :

Temperature

T err :

Difference between the calculated temperature and the measured temperature

T ref :

Temperature at reference condition

T TSP :

Temperature measured by temperature-sensitive paint

T 0 :

Stagnation temperature

T 1 :

Temperature determined by heat flux through 1D heat conduction equation

T ∞ :

Static temperature

t :

Time from the start of the wind tunnel

x :

Coordinate in streamwise direction

ΔT :

Temperature change with respect to the wind-off temperature

α :

Angle of attack

ε :

Error tolerance

θ :

Circumferential angle

ρ :

Density

References

  • Borovoy V, Bykov A, Mosharov V, Orlov A, Radchenko V, Phonov S (1995) Pressure sensitive paint application in shock wind tunnel. In: Proceedings of the 16th international congress on instrumentation in aerospace simulation facilities

  • Bryce DM (2001) Troubleshooting: a guide for injection molders. Techtrax, Georgetown

    Google Scholar 

  • Cai Z, Liu T, Wang B, Rubal J, Sullivan JP (2011) Numerical inverse heat transfer analysis for temperature-sensitive-paint measurements in hypersonic tunnels. J Thermophys Heat Transf 25:59–67. doi:10.2514/1.49217

    Article  Google Scholar 

  • Cook WJ, Felderman EJ (1966) Reduction of data from thin film heat transfer gauges—a concise numerical technique. AIAA J 4:561–562. doi:10.2514/3.3486

    Article  Google Scholar 

  • Fay JA, Riddell FR (1958) Theory of stagnation point heat transfer in dissociated air. J Aeronaut Sci 25:78–85

    MathSciNet  Google Scholar 

  • Gray JD (1964) Summary report on aerodynamic characteristics of standard models HB-1 and HB-2. AEDC-TDR-64-137

  • Gregory JW, Asai K, Kameda M, Liu T, Sullivan JP (2008) A review of pressure-sensitive paint for high-speed and unsteady aerodynamics. Proc Inst Mech Eng G J Aerosp 222:249–290. doi:10.1243/09544100JAERO243

    Article  Google Scholar 

  • Hirschen C, Gulham A, Beck WH, Henne U (2008) Experimental study of a scramjet nozzle flow using the pressure-sensitive-paint method. J Propuls Power 24:662–672. doi:10.2514/1.34626

    Article  Google Scholar 

  • Hubner JP, Carroll BF, Schanze KS, Ji HF, Holden MS (2001) Temperature- and pressure-sensitive paint measurements in short-duration hypersonic flow. AIAA J 39:654–659. doi:10.2514/2.1358

    Article  Google Scholar 

  • Hubner JP, Carroll BF, Schanze KS (2002) Heat-transfer measurements in hypersonic flow using luminescent coating techniques. J Thermophys Heat Transf 16:516–522. doi:10.2514/2.6726

    Article  Google Scholar 

  • Jensen CD, Gompertz KA, Peng D, Gregory JW, Bons JP (2012) Measurement techniques for shock movement capture on a NACA 0012 in unsteady compressible flow. 28th Aerodynamic measurement technology, ground testing, and flight testing conference

  • Jiang Z, Yu H (2014) Experiments and development of the long-test-duration hypervelocity detonation-driven shock tunnel (LHDst). 52nd Aerospace sciences meeting, AIAA-2014-1012

  • Jules K, Carbonaro M, Zemsch S (1995) Application of pressure sensitive paint in hypersonic flows. NASA-TM-106824

  • Kuchiishi S, Watanabe S, Nakakita K, Koyama T, Ueda S, Itoh K (2003) Comparative heat flux measurements between three hypersonic test facilities at NAL. 33rd AIAA fluid dynamics conference and exhibit, AIAA-2003-4254

  • Kurits I, Lewis MJ (2009) Global temperature-sensitive paint system for heat transfer measurements in long-duration hypersonic flows. J Thermophys Heat Transf 23:256–266. doi:10.2514/1.39926

    Article  Google Scholar 

  • Kuriki T, Sakaue H, Imamura O, Suzuki K (2010) Temperature-cancelled AA-PSP for hypersonic compression corner flows. 48th AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition, AIAA 2010-673

  • Liu T, Sullivan JP (2005) Pressure and temperature sensitive paints. Springer, New York

    Google Scholar 

  • Liu T, Cai Z, Lai J, Rubal J, Sullivan JP (2010) Analytical method for determining heat flux from temperature-sensitive-paint measurements in hypersonic tunnels. J Thermophys Heat Transf 24:85–94. doi:10.2514/1.43372

    Article  Google Scholar 

  • Liu T, Wang B, Rubal J, Sullivan JP (2011) Correcting lateral heat conduction effect in image-based heat flux measurements as an inverse problem. Int J Heat Mass Transf 54:1244–1258

    Article  MATH  Google Scholar 

  • Morita K, Suzuki K, Imamura O, Sakaue H (2011) Temperature-cancelled anodized-aluminum pressure sensitive paint for hypersonic wind tunnel application. 41st AIAA fluid dynamics conference and exhibit, AIAA-2011-3724

  • Nagai H, Ohmi S, Asai K, Nakakita K (2008) Effect of temperature-sensitive-paint thickness on global heat transfer measurement in hypersonic flow. J Thermophys Heat Transf 22:373–381. doi:10.2514/1.34152

    Article  Google Scholar 

  • Nakakita K, Asai K (2002) Pressure-sensitive paint application to a wing-body model in a hypersonic shock tunnel. 22nd AIAA aerodynamic measurement technology and ground testing conference, AIAA 2002-2911. doi:10.2514/6.2002-2911

  • Nakakita K, Yamazaki T, Asai K, Teduka N, Fuji A, Kameda M (2000) Pressure sensitive paint measurement in a hypersonic shock tunnel. 21st AIAA aerodynamic measurement technology and ground testing conference, AIAA 2000-2523. doi:10.2514/6.2000-2523

  • Nakakita K, Osafune T, Asai K (2003) Global heat transfer measurement in a hypersonic shock tunnel using temperature-sensitive. 41st Aerospace sciences meeting and exhibit, AIAA-2003-0743

  • Pandey A, Gregory JW (2016) Frequency-response characteristics of polymer/ceramic pressure-sensitive paint. AIAA J 54:174–185. doi:10.2514/1.J054166

    Article  Google Scholar 

  • Peng D, Jensen CD, Juliano TJ, Gregory JW, Crafton J, Palluconi S, Liu T (2013) Temperature-compensated fast pressure-sensitive paint. AIAA J 51:2420–2431. doi:10.2514/1.J052318

    Article  Google Scholar 

  • Robinson M, Hannemann K (2006) Short duration force measurements in impulse facilities. 25th AIAA aerodynamic measurement technology and ground testing conference, AIAA 2006-3439

  • Sakaue H (2003) Anodized aluminum pressure sensitive paint for unsteady aerodynamic applications. Ph.D. dissertation, Purdue University

  • Sakaue H, Matsumura S, Schneider SP, Sullivan JP (2002) Anodized aluminum pressure sensitive paint for short duration testing. 22nd AIAA aerodynamic measurement technology and ground testing conference, AIAA-2002-2908

  • Watkins AN, Buck GM, Leighty BD, Lipford WE, Oglesby DM (2009) Using pressure- and temperature-sensitive paint on the aftbody of a capsule vehicle. AIAA J 47:821–829. doi:10.2514/1.37258

    Article  Google Scholar 

  • Yang L, Erdem E, Zare-Behtash H, Kontis K, Saravanan S (2012a) Pressure-sensitive paint on a truncated cone in hypersonic flow at incidences. Int J Heat Fluid Flow 37:9–21. doi:10.1016/j.ijheatfluidflow.2012.05.004

    Article  Google Scholar 

  • Yang L, Zare-Behtash H, Erdem E, Kontis K (2012b) Investigation of the double ramp in hypersonic flow using luminescent measurement systems. Exp Therm Fluid Sci 40:50–56. doi:10.1016/j.expthermflusci.2012.01.032

    Article  Google Scholar 

Download references

Acknowledgements

This work was supported by the young faculty start-up fund from Shanghai Jiao Tong University, National Natural Science Foundation of China (NSFC No. 11502144) and funding from Gas Turbine Research Institute of Shanghai Jiao Tong University. The authors appreciate the assistance from Mr. Hongyi Shao during the heat flux calculation.

Author information

Authors and Affiliations

  1. Gas Turbine Research Institute/School of Mechanical Engineering, Shanghai Jiao Tong University, 800 Dongchuan Rd., Shanghai, 200240, China

    Di Peng, Lingrui Jiao & Yingzheng Liu

  2. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, 29 Yudao Street, Nanjing, 210016, China

    Zhijun Sun & Yunsong Gu

Authors
  1. Di Peng
    View author publications

    You can also search for this author in PubMed Google Scholar

  2. Lingrui Jiao
    View author publications

    You can also search for this author in PubMed Google Scholar

  3. Zhijun Sun
    View author publications

    You can also search for this author in PubMed Google Scholar

  4. Yunsong Gu
    View author publications

    You can also search for this author in PubMed Google Scholar

  5. Yingzheng Liu
    View author publications

    You can also search for this author in PubMed Google Scholar

Corresponding author

Correspondence to Yingzheng Liu.

Rights and permissions

Reprints and permissions

About this article

Check for updates. Verify currency and authenticity via CrossMark

Cite this article

Peng, D., Jiao, L., Sun, Z. et al. Simultaneous PSP and TSP measurements of transient flow in a long-duration hypersonic tunnel. Exp Fluids 57, 188 (2016). https://doi.org/10.1007/s00348-016-2280-z

Download citation

  • Received:

  • Revised:

  • Accepted:

  • Published:

  • DOI: https://doi.org/10.1007/s00348-016-2280-z

Keywords

Search

Navigation