Forebody Geometry Effects on the Flow of a Blunt-Nose Projectile at High Alpha

Lopera, Javier; Ng, Tammy; Patel, Mitesh; Stucke, Russ

doi:10.2514/1.31783

Cited by 12 publications

(4 citation statements)

References 38 publications

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“…The randomness of the vortex pattern was inhibited by perturbation; hence, the measurement of side-force was determinate and highly repeatable. Similar observations were reported by Lopera and Terry (2007) by using a strake (3 mm high and 5 mm long) attached on a blunt nose. These additional units exhibited relatively large physical sizes and unexpectedly induced the local flow separation.…”

Section: Introductionsupporting

confidence: 88%

Investigation on asymmetric flow over a blunt-nose slender body at high angle of attack

Wang

et al. 2017

Fluid Dyn. Res.

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The asymmetric vortices over a blunt-nose slender body are investigated experimentally and numerically at a high angle of attack (AoA, α=50°) and a Reynolds number of Re D =1.54×10 5 on the basis of an incoming freestream velocity and diameter (D) of the model. A micro-perturbation in the form of a hemispherical protrusion with a radius of r=0.012D is introduced and attached on the nose of the slender body to control the behavior of the asymmetric vortices. Given the predominant role of micro perturbation in the asymmetric vortex pattern, a square wave, which is singly periodic, is observed for side-force variation by setting the circumferential angle (θ) of the micro perturbation from 0°to 360°. The asymmetric vortex pattern and the corresponding side force are manageable and highly dependent on the location of perturbation. The flow structure over the blunt-nose slender body is clarified by building a physical model of asymmetric vortex flow structure in a regular state at a high AoA (α=50°). This model is divided into several regions by flow structure development along the model body-axis, i.e., inception region at x/D3.0, triple-vortex region at 3.0x/D6.0, four-vortex region at 6.0x/D8.5, and five-vortex region at 8.5x/D12. The model reveals a complicated multi-vortex system. The associated pressure distributions and flow characteristics are discussed in detail.

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Section: Introductionsupporting

confidence: 88%

Investigation on asymmetric flow over a blunt-nose slender body at high angle of attack

Wang

et al. 2017

Fluid Dyn. Res.

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“…Fig. 14 presented the oil surface visualization at the nose tip in the absence of a perturbation based on the oil surface visualization technology used by Lopera [ 40 ] in analyzing the asymmetric flow over a slender body, and the separation lines were highlighted in red. Based on the characteristics of the open- and close-type separation discussed by Wang [ 24 ], for B = 0, 1.25, and 1.5, the left and right separation lines were separated at the nose tip.…”

Section: Resultsmentioning

confidence: 99%

Investigation of periodic characteristics of perturbed flow over a slender body

Zhao

Wang

2023

Heliyon

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“…14,15) In particular, for the strategic demand of an air-to-air missile, the study about the free-to-roll motion of a blunt-nosed slender body configuration has become a hot topic in recent years. Two studies 16,17) have found that the mechanism of forebody asymmetric vortices over a blunt nose is different from that over a pointed nose. Moreover, this configuration normally includes multiple sets of wings from nose to tail, such as strips, wings, and tail rudders.…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Free-to-Roll Motion of a Blunt-Nosed Slender Body Configuration

Zhao

WANG

2022

Trans. Japan Soc. Aero. S Sci.

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Aircraft with a blunt-nosed slender body configuration exhibit free-to-roll motion during maneuvering flight. The separation vortex on the forebody and the wing parameters are the two key factors affecting this motion. A blunt-nosed slender body configuration normally includes multiple sets of wings, which enhances the complexity of the roll motion. The strips, narrow wings, and tail rudders are installed at different axial locations on the blunt-nosed body to study the influence of wings on the roll motion. Wind tunnel experiments are conducted to investigate the motion at Reynolds number Re D = 1.54 © 10 5 , which is based on the coming freestream velocity and diameter of the blunt-nosed body. Free-to-roll motion and aerodynamic forces are measured by the free-to-roll sting support and force balance, respectively. The free-toroll motion is first described and divided into six regions based on the motion characteristics at 0°¯¡ ¯55°. The strips, narrow wings, and tail rudders are removed to investigate the effect of the wings on the roll motion. The major control performance of strips, narrow wings, and tail rudders on motion in each angle-of-attack (AOA) region are discussed in detail. The experimental results indicate that the coupling between asymmetric flow and tail rudders leads to different characteristics of free-to-roll motion at different AOAs. The asymmetric flow is closely related to the strips, narrow wings and AOA.

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Forebody Geometry Effects on the Flow of a Blunt-Nose Projectile at High Alpha

Cited by 12 publications

References 38 publications

Investigation on asymmetric flow over a blunt-nose slender body at high angle of attack

Investigation on asymmetric flow over a blunt-nose slender body at high angle of attack

Investigation of periodic characteristics of perturbed flow over a slender body

Experimental Investigation of Free-to-Roll Motion of a Blunt-Nosed Slender Body Configuration

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