Abstract
Experimental and numerical studies were carried out to evaluate the effect of vortex generator on a small cylindrical protrusion at Mach number 2.0. The experiments were performed using the supersonic blow down wind tunnel on different heights of cylindrical protrusion with vortex generator placed ahead of them. The upstream and downstream flow around the cylindrical protrusion is influenced by vortex generator as is observed using both visualization and pressure measurement techniques. Numerical studies using three dimensional steady implicit formulations with standard k-ω turbulence model was performed. Results obtained through the present computation are compared with the experimental results at Mach 2.0. Good agreements between computation and experimental results have been achieved. The results indicate that the aerodynamic drag acting on cylindrical protrusion can be reduced by adopting vortex generator.
Article PDF
Similar content being viewed by others
Avoid common mistakes on your manuscript.
References
J.C. Westkaemper, “Turbulent Boundary Layer Separation ahead of Cylinders,” AIAA Journal, vol. 6, No. 7, July 1968, pp. 1352–1355.
R. Sedney, “Visualization of Boundary Layer Flow Patterns around Protuberances Using an Optical-Surface Indicator Technique,” Physics of Fluids, vol. 15, No. 12, December 1972, pp. 2439–2441.
R. Sedney, “A Survey of the Effects of Small Protuberances on Boundary-Layer Flows,” AIAA Journal, vol. 11, No. 6, June 1973, pp. 782–792.
J. H. Mashburn, “Turbulent Boundary Layer Separation Ahead of Cylindrical Protuberances in Supersonic Flow,” ARL-TR-69-17, August 1969.
R. Sedney, C. W. Kitchens, “Separation ahead of Protuberances in Supersonic Turbulent Boundary Layers,” AIAA Journal, vol. 15, No. 4, April 1977, pp. 546–552.
S. Li, Y. Shi, and Y. Chen, “The Effects of the Short Protuberance on Interactive Flowfield at Hypersonic Speed,” AIAA Paper 95-1829-CP, 13th AIAA Applied Aerodynamics conference, Baltimore, MD, June 1995, pp. 548–555.
P.V. Hahn and A. Frendi. “Interaction of Three-Dimensional Protuberances with a Supersonic Turbulent Boundary Layer,” AIAA Journal, vol. 51, No. 7 (2013), pp. 1657–1666.
B.H. Anderson, J. Tinapple, L. Surber, “Optimal Control of Shock Wave Turbulent Boundary Layer Interactions Using Micro-Array Actuation,” AIAA Paper 2006-3197, 3rd Flow Control Conference, San Francisco, USA, June 2006.
H. Babinsky, “Understanding Micro-Ramp control for Shock Boundary Layer Interaction,” US Air Force Research Lab., Ohio, USA, Rept. AFRL-SR-AR-TR-08-0074, January 2008.
F.K. Lu, A.J. Pierce, Y. Shih, C. Liu, and Q. Li, “Experimental and Numerical Study of Flow Topology Past Micro Vortex Generators,” AIAA 2010-4463, 40th Fluid Dynamics Conference and Exhibit, Chicago, USA, July 2010.
E. Loth, and S. Lee, “Understanding Micro-Ramp Control for Shock Boundary Layer Interactions,” US Air Force Research lab., Ohio, USA, Rept. AFRL-SR-AR-TR-08-0145, July 2008.
A. J. Pierce, Q. Li, Y. Shih, F. K. Lu, and Q. Liu, “Interaction of Micro-vortex Generator Flow with Ramp-Induced Shock/Boundary-Layer Interactions,” AIAA 2011-32, 49th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Orlando, Florida.
D.S. Galbraith, M.C. Galbraith, M. G. Turner, P.D. Orkwis, and A. Apyan, “Preliminary Numerical Investigation of a Mach 3 Inlet Configuration with and without Aspiration and Micro-Ramps,” AIAA 2010–1095, 48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida, Jan 2010.
Vignesh Ram, P.S., “Flow Field Investigation around Cylindrical Protrusion with Vortex Generator,” Master’s Thesis, BIT Mesra, India, 2011.
Author information
Authors and Affiliations
Rights and permissions
About this article
Cite this article
Vignesh Ram, P.S., Setoguchi, T. & Kim, H.D. Effects of vortex generator on cylindrical protrusion aerodynamics. J. Therm. Sci. 25, 7–12 (2016). https://doi.org/10.1007/s11630-016-0828-0
Received:
Published:
Issue Date:
DOI: https://doi.org/10.1007/s11630-016-0828-0