Advertisement

Shock-Wave Boundary-Layer Interaction Control on a Compression Corner Using Mechanical Vortex Generators

  • C. Manisankar
  • S. B. Verma
  • C. Raju

Introduction

Shock-wave boundary-layer interactions (SWBLI) are prevalent in many supersonic applications, e.g., over deflected flaps, fore-body ramp corners, on leading edges where the bow shock from the vehicle nose interferes, along axial compression corners inside air-inlets, shock reflection and crossing-shock interactions in the inlets etc. The adverse pressure gradient across the interaction shock can cause separation of the incoming boundary-layer leading to increased aerodynamic drag, heat transfer and unsteady pressure loads. Much of the early work over forward-facing steps [1], un-swept compression ramp flows [2-4] and in interactions induced by blunt fins [5], circular cylinders and sharp fins at angle of attack [6] was focused on understanding the dynamic/unsteady behavior of these interactions. It has been observed that the flow in these interactions in unsteady if the pressure ratio across the oblique shock is such that the mass of the fluid reversed at the reattachment point does not balance the scavenged fluid from the separated region [7-8]. As a result, the separated region “breathes” and during one half of pulse, mass is injected into it while during the other half it is ejected out resulting into an unsteady mass exchange.

Keywords

Separation Bubble Wall Pressure Streamwise Vortex Pressure Sensitive Paint Separation Shock 
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.
    Kistler, A.L.: Fluctuating Wall Pressure Under Separated Supersonic Flow. Journal of Acoustical Society of America 36, 543–550 (1964)CrossRefGoogle Scholar
  2. 2.
    Dolling, D.S., Murphy, M.T.: Unsteadiness of the Separation Shock Wave Structure in a Supersonic Compression Ramp Flowfield. AIAA Journal 21(12), 1628–1634 (1983)CrossRefGoogle Scholar
  3. 3.
    Muck, K.C., Andreopoulos, J., Dussuage, J.P.: Unsteady Nature of Shock-Wave/Boundary- Layer Interactions. AIAA Journal 26(2), 179–187 (1988)CrossRefGoogle Scholar
  4. 4.
    Verma, S.B.: Experimental Study of Flow Unsteadiness in a Mach 9 Compression Ramp Interaction Using a Laser Schlieren System. Measurement Science and Technology Journal 14, 989–997 (2003)CrossRefGoogle Scholar
  5. 5.
    Dolling, D.S., Bogdonoff, S.M.: An Experimental Investigation of the Unsteady Behavior of Blunt Fin-Induced Shock Wave Turbulent Boundary Layer Interaction, AIAA Paper 81-1287Google Scholar
  6. 6.
    Dolling, D.S., Brusniak, L.: Separation Shock Motion in Fin, Cylinder, and Compression Ramp-Induced Turbulent Interactions. AIAA Journal 27(6), 734–742 (1989)CrossRefGoogle Scholar
  7. 7.
    Maull, D.J.: Hypersonic Flow over Axially Symmetric Spiked Bodies. Journal of Fluid Mechanics 4, 584–592 (1960)MathSciNetCrossRefGoogle Scholar
  8. 8.
    Charwat, A.F., Dewey, C.F., Roos, J.N., Hitz, J.A.: Investigation of Separated Flows, Part II; Flow in Cavity and Heat Transfer. Journal of Aeronautical Sciences 28(7), 513–527 (1961)zbMATHGoogle Scholar
  9. 9.
    Dolling, D.S.: Fifty Years of Shock-Wave/Boundary-Layer Interaction Research: What Next? AIAA Journal 39(8), 1517–1531Google Scholar
  10. 10.
    McCormick, StateD.C.: Shock-Boundary layer interaction control with low-profile vortex generators (SBVGs) and passive cavity. AIAA Paper 92-0064Google Scholar
  11. 11.
    Babinsky, H.: Makinson, and Morgan: Micro-vortex Generator Flow Control for Supersonic Engine Inlets. AIAA Paper 2007-0521, 0521 (2007)Google Scholar
  12. 12.
    Szwabe, R.: Shock Wave Induced Separation Control by Streamwise Vortices. Journal of Thermal Sciences 14(3), 249–253 (2005)CrossRefGoogle Scholar
  13. 13.
    Blinde, P.L., Humble, R.A., Oudheusden, B.W., Scarano, F.: Effects of Micro-Ramps on a Shock Wave/Turbulent Boundary Layer Interactio. Shock Waves 19, 507–520 (2009)CrossRefGoogle Scholar
  14. 14.
    Bur, R., Coponet, D., Carpels, Y.: Separation Control by Vortex Generators Devices in a Transonic Channel Flow. Shock Waves (2009)Google Scholar
  15. 15.
    Raju, C., Vishwanath, P.R.: Pressure-Sensitive Paint Measurements in a Blowdown Wind Tunnel. Journal of Aircraft 42(4) (July-August 2005)Google Scholar

Copyright information

© Springer-Verlag Berlin Heidelberg 2012

Authors and Affiliations

  • C. Manisankar
    • 1
  • S. B. Verma
    • 1
  • C. Raju
    • 1
  1. 1.CSIR-National Aerospace Laboratories, Experimental Aerodynamics DivisionBangaloreIndia

Personalised recommendations