Hypersonic flow past a spherically blunted nose cone: a computational study

Narayan, Ashish; Narayanan, S.; Kumar, Rajkishor; Kumar, Chintoo Sudhiesh; Jagadeesh, G.

doi:10.1504/pcfd.2020.106410

Cited by 6 publications

(1 citation statement)

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“…When the disc diameter was small, the drag coefficient maintained a descending tendency as aerospike length went up, and vice versa. Narayan et al [19] carried out a comparison of different blunt ratios and semivertex angles and concluded that the shock detachment distance was linearly correlated to the bluntness ratio. In addition, when the blunt ratio and semivertex angle became small, the drag coefficient would follow suit.…”

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confidence: 99%

Dynamic Drag Reduction Effects of Aerospikes and Aerodisks

Han

Liu

Yang

et al. 2021

International Journal of Aerospace Engineering

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In order to investigate the dynamic characteristics of blunt aircraft mounted with aerospikes and aerodisks in large-amplitude force-pitching, the Roe spatial scheme and the lower-upper symmetric Gauss-Seidel (LU-SGS) method with dual time step are employed for discretization of unsteady Navier-Stokes (N-S) equations. A parametric investigation on the flow fields is conducted by altering the pitching period, aerospike length, and aerodisk diameter consequently via a variable-controlling procedure. Dynamic characteristics of aerodynamic drag as well as the visualization of unsteady flow fields are achieved, and the results show that the aerodynamics of hypersonic aircraft under the condition of large-amplitude force-pitching vibration have hysteresis characteristics affected by periods of force-pitching vibration. In addition, when changing aerospike length and aerodisk diameter, the variation tendency of drag reduction efficiency is determined by the pitching angle of the oscillation process.

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confidence: 99%

Dynamic Drag Reduction Effects of Aerospikes and Aerodisks

Han

Liu

Yang

et al. 2021

International Journal of Aerospace Engineering

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Effects of blowing upon dynamic stability of blunt nosed re entry vehicles pitching in hypersonic flow

Khalid,

Juhany

2023

Aeronaut. j.

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Blowing is often used to alleviate the intense heating rates on blunt noses of hypersonic vehicles. This flow efflux at the leading edge transforms the flow field in the blunt-nose regions with implications on the dynamic stability of the vehicles. As a demonstrative exercise, the flow fields past blunt-nosed and truncated-nosed conical bodies under blowing and no-blowing conditions were perturbed to obtain the unsteady effects using the shock expansion method to recover the unsteady pressure coefficient. Static and pitching moment derivatives were then duly obtained by integrating the differential of the unsteady pressure coefficient with respect to the pitch angle (α) or the pitch rate ( $\dot \theta $ ) together with the moment arm with reference to the centre of gravity. The results obtained for blunt-nose and truncated conical bodies show a noticeable drop in dynamic stability. Even when the flow is transformed from a tangential blowing at the shoulder of the blunt-nosed vehicle shows some degradation in dynamic stability.

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