Abstract
It is well known in literature that further stages of flow separation and vortex breakdown around wings can be able to cause stall of wings. These formations must be investigated carefully for new plane types. However, some limited studies are available, especially on lambda wing for high angles of attack. In this study, effect of angle of attack on flow characteristics and vortex breakdown around a lambda wing is investigated with a constant Reynolds number of 10000. Computational fluid dynamic analysis is used and results of high angles of attack of the wing are given up to 450 which are not available in literature. Open water channel simulation is used. Vortex breakdown initially begins at an angle of 170 and it almost reaches to tip of wing when angle of attack is equal to 250. Vortices get stronger at further increments of angle of attack and they become to nearly equal length of wing at 450. Rounding effect of leading edges is investigated for decreasing vortex magnitudes. Streamline, particle injection, iso-value of vortices and location of stagnation points are given, and they are discussed in detail.
Highlights
The usage of unmanned combat air vehicles (UCAVs) creates a new field of study on the investigation of flow characteristics around specific wing geometries
Vortex breakdown occurs after the flow separation on the wing by increasing angle of attack [6] has a dominant effect [4,5] on flight conditions and must be examined
In this study, flow characteristics around a lambda wing are observed and vortex breakdown is investigated under various angles of attack, especially up to 45°
Summary
The usage of unmanned combat air vehicles (UCAVs) creates a new field of study on the investigation of flow characteristics around specific wing geometries. Vortex breakdown occurs after the flow separation on the wing by increasing angle of attack [6] has a dominant effect [4,5] on flight conditions and must be examined. Pashilkar [32] investigates a surface pressure model for observing aeroelastic responses of delta wing for high angles of attack conditions. When active control is [40] used, vortex ring formations occur Another application of perturbations on wings [42] prevents large-scale separation zone along the wing at high angle of attack. New type of lambda wing geometry is investigated for observation of flow characteristics and vortex breakdown, especially for high angles of attack.
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