Pressure fluctuations underlying attached and separated supersonic turbulent boundary layers and shock waves

Coe, C. F.; Chyu, W. J.; Dods, J. B.

doi:10.2514/6.1973-996

Cited by 58 publications

(44 citation statements)

References 8 publications

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“…Historically, the structural behavior to these different sources has been considered separately. In the first class of problems, the quasi-static panel response (Kontinos, 1997;Culler et al, 2009), and dynamic instabilities (McNamara et al, 2005;Mei et al, 1999;Culler et al, 2009) has been studied by modeling the boundary layer loads and other external acoustic excitations: (1) as a random in time, and uniform in space acoustic load (Przekop and Rizzi, 2006;Spottswood et al, 2010), (2) using semi-empirical models (Maestrello, 1969;Hwang et al, 2009;Hambric et al, 2004;Coe and Chyu, 1972;Wu and Maestrello, 1995), and (3) using high-fidelity Computational Fluid Dynamics (CFD) simulations (Frendi, 1997(Frendi, , 2004. There are limitations of each of these approaches.…”

mentioning

confidence: 99%

Response of skin panels to combined self- and boundary layer-induced fluctuating pressure

Deshmukh

Culler

Miller

et al. 2015

Journal of Fluids and Structures

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mentioning

confidence: 99%

Response of skin panels to combined self- and boundary layer-induced fluctuating pressure

Deshmukh

Culler

Miller

et al. 2015

Journal of Fluids and Structures

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“…i+½,j,k are defined as blend in of first and third differences The adaptive coefficients, ε (2) and ε (4) are…”

Section: Artificial Dissipationmentioning

confidence: 99%

“…In the present computation the values of κ (2) and κ (4) are constants, taken equal to 1/4 and 1/256, respectively. The dissipative operators in the r are defined in a similar manner.…”

Section: Artificial Dissipationmentioning

confidence: 99%

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Computation of Aerodynamic load on Protuberance over Satellite Launch Vehicle at Supersonic Speed

Mehta¹

2016

SJET

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This paper presents numerical simulations to compute the aerodynamic load on protuberance for a typical launch vehicle. Surface pressure coefficients over the satellite launch vehicle are computed by solving axisymmetric time-dependent compressible Euler equations. The governing fluid flow equations are discretized in spatial coordinates employing a finite volume approach, which reduces the equations to semi-discretized ordinary differential equations. Temporal integration is performed using multi-stage Runge-Kutta time stepping scheme. A local time-step is used to achieve steady state solution. The novelty of the current numerical scheme is to block the grid corresponding to the protuberance. The entire flow field around the protuberance is analyzed with the help of Mach contour plots. The numerical scheme captures all the essential flow field features of high speed flow such as a shock wave in front of the protuberance and expansion fan on the shoulder and wake flow behind the protuberance. The numerical results are validated with experimental data in heat shield region of the launch vehicle for free stream Mach number 1.2, 1.6 and 2.0. The pressure distributions on the protuberance are required to maintain the structural integrity of the launch vehicle. Keywords: Aerodynamic, CFD, Compressible flow, Satellite launch vehicle. INTRODUCTIONThe satellite launch vehicle has protuberance of varying geometrical shape and size to accommodate many components outside the core of the rocket. Computations of pressure coefficients as function of freestream Mach number during the ascent trajectory over the protuberance are essential in order determine the size and spacing of fasteners and underlying support structure. The presence of protuberance drastically alters flow field in the vicinity of the protuberance. Moreover, it also creates a local bow shock wave formation ahead of the protuberance.

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“…8), , , and Serafini (ref. 18 27) carried out experiments in the turbulent boundary layer at supersonic speeds up to Mach number 3.5. The pressure field investigation of separated flow in the boundary layer due to a step or interacting oscillating incident shock wave has been performed by Speaker and Ailman (ref.…”

Section: Introductionmentioning

confidence: 99%

Surface Pressure Fluctuations in Hypersonic Turbulent Boundary Layers

1975

Aeroacoustics: Fan, STOL, and Boundary Layer Noise; Sonic Boom; Aeroacoustics Instrumentation

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The surface pressure fluctuations on a flat-plate model at hypersonic Mach numbers of 5.2, 7.4 and 10.4 with an attached turbulent boundary layer were measured using flush mounted small piezoelectric sensors. A high frequency resolution of the pressure field was achieved using specially designed small piesoelectric sensors (dia. -0.5 mm) that had a good frequency response well above 300 KHz. The RMS pressures and non-dimensional energy spectra for all above Mach numbers are presented. The convective velocities, obtained from space-time correlation considerations are equal to 0.7 U«,. The results indicate th^ RMS pressures vary from 5 to 25 percent of the mean static pressures. The ratios of RMS pressure to dynamic pressure are less than the universally accepted subsonic value of 6*10~3. The ratio decreases in value as the Mach number or the dynamic pressure is increased. The ratio of RMS pressure to wall shear stress for Mach number 7.4 satisfies 1 5 p/r w < 3.

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Pressure fluctuations underlying attached and separated supersonic turbulent boundary layers and shock waves

Cited by 58 publications

References 8 publications

Response of skin panels to combined self- and boundary layer-induced fluctuating pressure

Response of skin panels to combined self- and boundary layer-induced fluctuating pressure

Computation of Aerodynamic load on Protuberance over Satellite Launch Vehicle at Supersonic Speed

Surface Pressure Fluctuations in Hypersonic Turbulent Boundary Layers

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