Abstract
| Original language | English |
|---|---|
| Pages (from-to) | 68-78 |
| Number of pages | 11 |
| Journal | Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering |
| Volume | 234 |
| Issue number | 1 |
| Early online date | 15 Apr 2019 |
| DOIs | |
| Publication status | Published - 1 Jan 2020 |
| Externally published | Yes |
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Stabilization of crossflow instability with plasma actuators : linearized navier stokes simulations. / Kang, Kean Lee; Ashworth, Richard; Mughal, Shahid.
In: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Vol. 234, No. 1, 01.01.2020, p. 68-78.Research output: Contribution to journal › Special issue
TY - JOUR
T1 - Stabilization of crossflow instability with plasma actuators
T2 - linearized navier stokes simulations
AU - Kang, Kean Lee
AU - Ashworth, Richard
AU - Mughal, Shahid
PY - 2020/1/1
Y1 - 2020/1/1
N2 - This paper describes work carried out within the European Union (EU)-Russia Buterfli project to look at the control of transition-causing “target” stationary cross flow vortices, by the use of distributed plasma actuation to generate sub-dominant “killer” modes. The objective is to use the “killer” modes to control the “target” modes through a non-linear stabilizing mechanism. The numerical modelling and results are compared to experimental studies performed at the TsAGI T124 tunnel for a swept plate subject to a favorable pressure gradient flow. A mathematical model for the actuator developed at TsAGI was implemented in a linearized Navier Stokes (LNS) solver and used to model and hence predict “killer” mode amplitudes at a measurement plane in the experiment. The LNS analysis shows good agreement with experiment, and the results are used as input for non-linear PSE analysis to predict the effect of these modes on crossflow transition. Whilst the numerical model indicates a delay in transition, experimental results indicated an advance in transition rather than delay. This was determined to be due to actuator induced unsteadiness arising in the experiment, resulting in the generation of travelling crossflow disturbances which tended to obscure and thus dominate the plasma stabilized stationary disturbances.
AB - This paper describes work carried out within the European Union (EU)-Russia Buterfli project to look at the control of transition-causing “target” stationary cross flow vortices, by the use of distributed plasma actuation to generate sub-dominant “killer” modes. The objective is to use the “killer” modes to control the “target” modes through a non-linear stabilizing mechanism. The numerical modelling and results are compared to experimental studies performed at the TsAGI T124 tunnel for a swept plate subject to a favorable pressure gradient flow. A mathematical model for the actuator developed at TsAGI was implemented in a linearized Navier Stokes (LNS) solver and used to model and hence predict “killer” mode amplitudes at a measurement plane in the experiment. The LNS analysis shows good agreement with experiment, and the results are used as input for non-linear PSE analysis to predict the effect of these modes on crossflow transition. Whilst the numerical model indicates a delay in transition, experimental results indicated an advance in transition rather than delay. This was determined to be due to actuator induced unsteadiness arising in the experiment, resulting in the generation of travelling crossflow disturbances which tended to obscure and thus dominate the plasma stabilized stationary disturbances.
U2 - 10.1177/0954410019842033
DO - 10.1177/0954410019842033
M3 - Special issue
VL - 234
SP - 68
EP - 78
JO - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
JF - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
SN - 0954-4100
IS - 1
ER -