Aerodynamic design of a hypersonic body with a constant adverse pressure gradient

Shope, Frederick L.; Spinetti, Robert

doi:10.2514/6.1991-3319

Cited by 4 publications

(1 citation statement)

References 2 publications

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“…1). The flared after-body was designed following the methodology of Shope [17] such that the surface pressure of the forecone was approximately doubled by the end of the flare. The overall dimensions were chosen so that the model used as much of the core flow as available with the Mach 7 nozzle [1].…”

Section: Methodsmentioning

confidence: 99%

Transition-Length Predictions for Hypersonic Flows with an Adverse Pressure Gradient

Convery-Brien¹,

Raghunath²,

Mee³

2020

Australasian Fluid Mechanics Conference (AFMC)

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A better estimate of the transition length can greatly increase the efficiency of thermal protection systems in hypersonic flying vehicles. Recent efforts have been made to fit models to experimental data available in the literature for different types of facilities, flow conditions and model geometries with zero pressure gradient. Experimental results from new transition experiments on a flared cone are compared with predictions from these models. The model predicts the transition length quite well. Due to the model's sensitivity to spot initiation rate, the predictions of the transition length when transition started well within the flared portion of the cone do not agree with the predictions as well.

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Section: Methodsmentioning

confidence: 99%

Transition-Length Predictions for Hypersonic Flows with an Adverse Pressure Gradient

Convery-Brien¹,

Raghunath²,

Mee³

2020

Australasian Fluid Mechanics Conference (AFMC)

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Direct numerical simulations of hypersonic boundary-layer transition for a flared cone: fundamental breakdown

2019

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Direct numerical simulations (DNS) were carried out to investigate the laminar–turbulent transition for a flared cone at Mach 6 at zero angle of attack. The cone geometry of the flared cone experiments in the Boeing/AFOSR Mach 6 Quiet Tunnel (BAM6QT) at Purdue University was used for the simulations. In the linear regime, the largest integrated spatial growth rates ($N$-factors) for the primary instability were obtained for a frequency of approximately $f=300~\text{kHz}$. Low grid-resolution simulations were carried out in order to identify the azimuthal wavenumber that led to the strongest growth rates with respect to the secondary instability for a fundamental and subharmonic resonance scenario. It was found that for the BAM6QT conditions the fundamental resonance is much stronger compared to the subharmonic resonance. Subsequently, for the case which led to the strongest fundamental resonance onset, detailed investigations were carried out using high-resolution DNS. The simulation results exhibit streamwise streaks of very high skin friction and of high heat transfer at the cone surface. Streamwise ‘hot’ streaks on the flared cone surface were also observed in the experiments carried out at the BAM6QT facility using temperature sensitive paint. The presented findings provide strong evidence that the fundamental breakdown is a dominant and viable path to transition for the BAM6QT conditions.

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The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers

Kimmel

1997

Journal of Fluids Engineering

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Boundary layer transition was measured in zero, favorable, and adverse pressure gradients at Mach 8 using heat transfer. Models consisted of 7° half angle forecones 0.4826 m long, followed by flared or ogive aft bodies 0.5334 m long. The flares and ogives produced constant pressure gradients. For the cases examined, favorable pressure gradients delay transition and adverse pressure gradients promote transition, but transition zone lengths are shorter in favorable pressure gradient. Results of the effect of adverse pressure gradient on transition zone lengths were inconclusive.

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Aerodynamic design of a hypersonic body with a constant adverse pressure gradient

Cited by 4 publications

References 2 publications

Transition-Length Predictions for Hypersonic Flows with an Adverse Pressure Gradient

Transition-Length Predictions for Hypersonic Flows with an Adverse Pressure Gradient

Direct numerical simulations of hypersonic boundary-layer transition for a flared cone: fundamental breakdown

The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers

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