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Title

Optimisation of Trapped Vortex Cavity for Airfoil Separation Control

Year: 1401
COI: JR_JAFM-15-1_016
Language: EnglishView: 54
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Authors

C. Panigrahi - Department of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram, Kerala, ۶۹۵۵۴۷, India
R. Chawla - Department of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram, Kerala, ۶۹۵۵۴۷, India
M. T. Nair - Department of Aerospace Engineering, Indian Institute of Space Science and Technology, Thiruvananthapuram, Kerala, ۶۹۵۵۴۷, India

Abstract:

The effects of a Trapped Vortex Cavity (TVC) on the aerodynamic performance of a NACA ۰۰۲۴ airfoil at a constant angle of attack (AoA) of ۱۴◦ were investigated in this study. It was observed that mass suction (MFR) was required to stabilise the vortex within the cavity segment. Lift to drag ratio (L/D) and MFR were chosen as performance objectives, along with a fully attached flow constraint (flow separation at X/c ≥ ۹۵% ). Parametric analysis was carried on the baseline airfoil with and without suction and compared to the airfoil with TVC with and without suction. It was observed that L/D increases as MFR increases for a baseline airfoil, and flow separation is delayed at high suction values (MFR = ۰.۲ kg/s). The TVC modifies the pressure distribution on the baseline airfoil when MFR is applied to the cavity section and there is a significant increase in lift; thus, L/D increases and flow separation is delayed. A lower value of MFR = ۰.۰۸ kg/s is sufficient to stabilise the vortex and improve the efficiency of the TVC airfoil. The findings of these parametric studies were used to do a multi-objective optimisation using a genetic algorithm to attain the desired cavity shape while achieving the largest L/D and the lowest MFR (that is proportional to the power required for control) with a fully attached flow constraint. It was found that mass suction and cavity shape both had an equal influence on flow control. The Pareto optimal front yielded a series of optimum designs. One of them was subjected to an off-design analysis in order to validate its performance at other incidences. It was observed that it performs better than the baseline airfoil, with an improved L/D and an increase in stall angle from ۱۰◦ to ۱۴◦.

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Paper COI Code

This Paper COI Code is JR_JAFM-15-1_016. Also You can use the following address to link to this article. This link is permanent and is used as an article registration confirmation in the Civilica reference:

https://civilica.com/doc/1361783/

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Panigrahi, C. and Chawla, R. and Nair, M. T.,1401,Optimisation of Trapped Vortex Cavity for Airfoil Separation Control,https://civilica.com/doc/1361783

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  • Adkins, R. (۱۹۷۵). A short diffuser with low pressure loss. ...
  • De Gregorio F, F. G. (۲۰۰۸). Flow control on a ...
  • Donelli, R., F. De Gregorio and P. Iannelli (۲۰۱۰). Flow ...
  • Donelli, R., P. Iannelli, S. Chernyshenko, A. Iollo and L. ...
  • Donelli, R. S., P. Iannelli, E. Iuliano and D. De ...
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  • Lasagna, D., R. Donelli, F. De Gregorio and G. Iuso ...
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  • Rossiter, J. (۱۹۶۴). Wind-tunnel experiments on the flow over rectangular ...
  • Rowley, C., T. Colonius and A. Basu (۲۰۰۱). On self-sustained ...
  • Rowley, C., V. Juttijudata and D. Williams (۲۰۰۵). Cavity flow ...
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