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The influence of transition onset location on the performance of shock control bumps

Published online by Cambridge University Press:  27 January 2016

S. C. McIntosh  and
N. Qin
S. C. McIntosh
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
N. Qin*
Affiliation:
Department of Mechanical Engineering, University of Sheffield, Sheffield, UK
*
n.qin@sheffield.ac.uk
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Abstract

In order to investigate the robustness of three dimensional bumps on shock control for natural laminar-flow wings, the impact of transition onset location on the overall performance of the shock control device was studied. For a ramp bump, a moderate ramp start angle θr =4° was found to effectively fix the location of the leading leg of the shock lambda, decreasing chord-wise movement in the main shock position resulting from variations in transition onset location. With increasing transition onset length from xtrans =0% chord to 45% chord, little influence was found regarding the overall performance of the shock control device but a down-stream movement of the secondary leg of the shock lambda in a range about 3% chord was observed. Change in the boundary-layer displacement thickness due to varying transition onset locations was identified as the primary mechanism responsible for this secondary shock leg movement.

Type
Research Article
Information
The Aeronautical Journal , Volume 117 , Issue 1196 , October 2013 , pp. 1037 - 1051
Copyright
Copyright © Royal Aeronautical Society 2013 

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