A Navier-Stokes solution for a bulbous payload shroud

Purohit, Sharad C.

doi:10.2514/3.25852

Cited by 13 publications

(6 citation statements)

References 15 publications

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“…In the boat-tail region, a local separation results, due to sharp discontinuity in the longitudinal of the payload shroud. The regions of flow separation impose additional complexity to aerodynamic and structural design aspects [9] - [13]. The complex flowfield at the transonic speeds is also observed during the experimental investigation of the bulbous heat shield.…”

Section: Introductionmentioning

confidence: 93%

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Unsteady Flowfield Characteristics Over Blunt Bodies at High Speed

Mehta¹

2014

Computational and Numerical Simulations

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Section: Introductionmentioning

confidence: 93%

“…This algebraic model, which utilizes the vorticity distribution to determine the scale lengths, has been extensively used in conjunction with the Reynolds-averaged Navier-Stokes equations [13,32,33].…”

Section: Axisymmetric Fluid Dynamics Equationsmentioning

confidence: 99%

Unsteady Flowfield Characteristics Over Blunt Bodies at High Speed

Mehta¹

2014

Computational and Numerical Simulations

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“…Our earlier attempt* 5 ' was aimed at simulating the flowfield along the bulbous heat shield for a higher subsonic flow. In addition to locating the supersonic pocket, a terminal shock Paper No 1469. and the shock induced separation, we were successful in identifying the large separation zones in the boat-tail region.…”

Section: Introductionmentioning

confidence: 99%

Supersonic flow simulation for a boat-tailed heat shield

Purohit

1987

Aeronaut. j.

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Summary For a 15° boat-tailed heat shield or payload shroud, the unsteady, compressible Navier-Stokes equations are numerically solved. For a Reynolds number of the order of one million and for four different freestream Mach numbers, the time integration is performed for 64 x 30 grid computational domain. The entire flow-field is analysed to delineate the gross dominant characteristics. It is observed that the flow in the boat-tail region is completely attached for Mach number 2·47 and beyond whereas it is separated for lower Mach numbers. A comparison between the numerical solutions and the available experimental results is provided and, for incipient flow separation conditions, an evaluation of unsteady surface pressure data is presented.

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“…The boattail angle is 15 degrees measured clockwise from the axis with reference to the oncoming flow direction. For the blunt nosed cone, the inclination at the forebody junction is 20 degree and the total length of the shroud from the stagnation point to the boattail end is 2.594 D. These subscale dimensions are chosen after considering the blockage and compatibility condition with the model system support of wind tunnel [13]. In order to initiate the numerical simulation of flow along the heat shield, the physical space is discretized into nonuniform spaced grid points.…”

Section: Model and Grid Arrangementmentioning

confidence: 99%

“…Purohit [13] has analyzed a typical bulbous heat shield using Mac Cormack's explicit scheme in conjunction with an algebraic turbulence model for a freestream Mach number of 0.80. It is observed experimentally [1] for the bulbous heat shield that the wall pressure fluctuations, moderate at first for freestream Mach number 0.75, become more and more intense as the shock recedes in the separated zone that follows it.…”

Section: Introductionmentioning

confidence: 99%

Wall pressure fluctuations over a bulbous heat shield of a satellite launch vehicle

Mehta

1999

Acta Mechanica

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Summary. Unsteady compressible Reynolds-averaged Navie>Stokes equations are solved for computing the ftowfield over a bulbous beat shield of a satellite launch vehicle at free stream Mach number of 0.95 and 1.20 and at zero angle of incidence. A time-dependent computation is carried out employing a multistage Runge-Kutta time-stepping in conjunction with a finite volume discretization. Closure of these equations is achieved using the Baldwin-Lomax turbulence model. Comparisons are made with the experimental results such as schlieren picture and surface pressure distribution. They are found in good agreement. Numerical analysis is used to determine the characteristics of the fluctuating surface pressure at transonic and supersonic speeds. Standard deviations, higher moments, histograms, and spectrum of pressure and sound pressure level of fluctuating pressure are analyzed in the separated region of the boattail of the heat shield. High frequency components of pressure amplitude and sound pressure levels are found to be dominate at supersonic Mach number as compared to transonic Mach number.

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A Navier-Stokes solution for a bulbous payload shroud

Cited by 13 publications

References 15 publications

Unsteady Flowfield Characteristics Over Blunt Bodies at High Speed

Unsteady Flowfield Characteristics Over Blunt Bodies at High Speed

Supersonic flow simulation for a boat-tailed heat shield

Wall pressure fluctuations over a bulbous heat shield of a satellite launch vehicle

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