Abstract
In this study, the flowfield produced by tangential leading-edge blowing on a rounded leading-edge 60-deg delta wing at high angle of attack is investigated computationally by solving the thin-layer Navier-Stokes equations. Steady-state flowHelds are calculated for various angles of attack, with and without the presence of tangential leading-edge blowing. The numerical grid is generated using algebraic grid generation and various interpolation and blending techniques. The jet emanates from a slot with linearly varying thickness, and is introduced into the flowfield using the concept of an actuator plane, thereby not requiring resolution of the jet slot geometry. The Baldwin-Lomax algebraic turbulence model is used to provide turbulent closure. The computational results are compared with those of experiments. The effectiveness of blowing as a rolling moment control mechanism to extend the envelope of controllabili ty is illustrated at different angles of attack. The saturation effect of increased blowing is captured well in the computations. Control reversal noted in similar experimental studies is also observed in the computations.
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