Diagnostic calculations of airframe-radiated noise

Hayden, Richard E.; Kadman, Y.; Bliss, Donald B.; Africk, Steven A.

doi:10.2514/6.1975-485

Cited by 6 publications

(1 citation statement)

References 2 publications

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“…The low energy constituent of the boundary layer is trapped in the separation bubble in the vicinity of the boat-tail region of the heat shield. Thus, the flow oscillations and the possible separation zones along the heat shield introduce yet another serious concern in the form of aeroacoustic noise [4], [5]. The maximum acoustic field for such a payload shroud is observed during the transonic phase of the flight with the high dynamic pressure conditions on the vehicle.…”

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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Section: Introductionmentioning

confidence: 99%