Investigation of the vortex flow over a 76/60-deg double delta wing at 20 deg incidence

Verhaagen, N.G.

doi:10.2514/6.1991-3208

Cited by 4 publications

(2 citation statements)

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“…2, and Verhaagen and Maseland in Ref. 3. The experiments indicate that the interaction process and breakdown of the strake and wing vortices depend on the angle of attack, the shape of the leading-edge cross section and the leading-edge kink angle.…”

Section: Introductionmentioning

confidence: 80%

“…In order to keep the measured velocities within the calibration of the 5HP, o weld data were acquired at a freestream velocity U 1 of 18 m/sec ( Re = 0.5 M ). Earlier experiments indicated that the velocities in the vortex core can reach v alues of up to three times U 1 [3]. The 5HP was mounted on a ve degree-of-freedom traverse (xyz-translation, pitch and yaw) with four degrees under computer control.…”

Section: Floweld Surveysmentioning

confidence: 99%

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A study of the vortex flow over a 76/40-deg double-delta wing

Verhaagen¹,

Jenkins²,

Kern³

et al. 1995

33rd Aerospace Sciences Meeting and Exhibit

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Section: Introductionmentioning

confidence: 80%

Section: Floweld Surveysmentioning

confidence: 99%

A study of the vortex flow over a 76/40-deg double-delta wing

Verhaagen¹,

Jenkins²,

Kern³

et al. 1995

33rd Aerospace Sciences Meeting and Exhibit

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Vortical Structures over a Generic Tailless Chined Forebody–Delta Wing

Rojas Carvajal,

Kumar Guha,

Amitay

2024

AIAA Journal

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The flowfield over a model having a chined forebody and a simple delta wing was investigated experimentally using oil flow visualizations and stereoscopic particle image velocimetry at a mean chord-based Reynolds number of [Formula: see text], angles of attack of 20 and 30 deg, and yaw angles of 0 and 5 deg. The flowfield over the model exhibited pairs of leading-edge vortices similar to those around a double-delta wing, except for the influence of the fuselage, where the chine vortex followed the curvature. The development and interaction of the two vortices were measured and analyzed. It was found that increasing the angle of attack resulted in wakelike vortices, whereas increasing the yaw angle yielded a wakelike vortex on the windward side and a jetlike vortex on the leeward side. The interaction of the windward side vortex with the physical barrier of the forebody surface was observed to greatly affect its behavior and the interaction downstream. In some configurations, the merged vortex exhibited a breakdown. The flowfield and the vortex dynamics under various conditions are discussed in detail to provide insight into manipulating the flowfield using physics-based flow control.

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