An advanced hypervelocity aerophysics facility - A ground-based flight-test range

Witcofski, R. D.; Scallion, W. I.; Carter, D. J.; Courter, Robert W.

doi:10.2514/6.1991-296

Cited by 9 publications

(2 citation statements)

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“…2 The proposed facility would be used primarily to study phenomena associated with hypervelocity aeroballistics and aerothermodynamics. The NASA study identified three existing technologies that have a reasonable probability for success: electromagnetic rail guns, ram/scram accelerators, and two-stage light gas guns.…”

Section: Literature Review Backgroundmentioning

confidence: 99%

Numerical simulation of the blast-wave accelerator

1996

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A concept for propelling a projectile to hypervelocities is described, and the feasibility is demonstrated by numerical simulations. In theory, the concept employs imploding blast waves to accelerate a projectile as it travels down a launch tube. The launch tube can be open to the atmosphere or sealed and maintained at some low pressure to minimize internal drag. The launch tube has a liner that contains a suitable explosive or energetic material. The explosive is configured with inert annular rings to prevent upstream detonation. A suitable trigger detonates each explosive ring sequentially as the projectile passes. The resulting blast wave causes an elevated pressure on the afterbody of the projectile. The acceleration continues until the projectile exits the launch tube.

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Section: Literature Review Backgroundmentioning

confidence: 99%

Numerical simulation of the blast-wave accelerator

1996

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“…Equations (1)(2)(3)(4)(5)(6)(7)(8)(9) have been scaled such that in the f ( f-+ 0) the postshock pressure, density, and velocities are all 0(1) quantities. The lengths have been scaled by the reaction zone length.…”

Section: C=h•mentioning

confidence: 99%

Comparisons of numerical and exact solutions for oblique detonationswith structure

Powers

Grismer

1991

22nd Fluid Dynamics, Plasma Dynamics and Lasers Conference

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Numerical predictions of the two-dimensional, inviscid, supersonic, reactive flow of a calorically perfect ideal gas over a straight wedge are compared with the predictions of a linear asymptotic model valid in the hypersonic limit. Solution features predicted by the asymptotic model include a curved shock attached to the wedge tip, a reaction layer parallel to the shock, and a vorticity layer parallel to the wedge surface. For sufficiently high Mach number and heat release, the numerical model predicts similar behavior, and the differences in the predictions of the two methods are of the same order of magnitude as the inherent error of the asymptotic method. As heat release is lowered and Mach number held constant, apparent numerical artifacts obscure features predicted by the asymptotic method. The results suggest that the asymptotic solution has utility as a benchmark to verify the predictions of many high-speed, multidimensional, reacting flow codes.

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The Ram Accelerator: Review of Experimental Research Activities in the U.S.

Bruckner

Knowlen

2016

Hypervelocity Launchers

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An advanced hypervelocity aerophysics facility - A ground-based flight-test range

Cited by 9 publications

References 0 publications

Numerical simulation of the blast-wave accelerator

Numerical simulation of the blast-wave accelerator

Comparisons of numerical and exact solutions for oblique detonationswith structure

The Ram Accelerator: Review of Experimental Research Activities in the U.S.

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