Calculation of the three-dimensional flow field in supersonic inlets at angle of attack using a bicharacteristic method with discrete shock wave fitting

Vadyak, J.; Hoffman, Joe D.; Bishop, A. R.

doi:10.2514/6.1979-379

Cited by 4 publications

(1 citation statement)

References 3 publications

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“…For the numerical studies on high speed inlet operability due to the angle of attack with boundary layer bleed, no work has been reported. Vadyak et al [13] made the rst computation of the ow eld of a mixed compression inlet with angle of attack using the method of characteristics with shock tting. Due to their numerical solver limitation, they did not take into account the wall boundary layer and boundary layer bleed.…”

Section: Introductionmentioning

confidence: 99%

Numerical simulation of HSCT inlet operability with angle of attack

Zha

Knight

Smith

et al. 1997

33rd Joint Propulsion Conference and Exhibit

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A High Speed Civil Transport (HSCT) inlet at Mach 2 and angle of attack is simulated by using a 3D Navier-Stokes solver with the Baldwin-Lomax algebraic turbulence model. An extrapolation uniform mass bleed boundary condition for the slot bleed is successfully employed. For zero angle of attack and critical operation, the pressure distribution agrees well with the experiment. The location and intensity of the terminal shock, total pressure recovery are accurately computed. The angle of attack to cause the inlet unstart is accurately predicted. The mesh renement results are presented.

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Section: Introductionmentioning

confidence: 99%

Numerical simulation of HSCT inlet operability with angle of attack

Zha

Knight

Smith

et al. 1997

33rd Joint Propulsion Conference and Exhibit

View full text Add to dashboard Cite

show abstract

Improved Calculation of High Speed Inlet Flows: Part I. Numerical Algorithm

Knight

1981

AIAA Journal

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Calculation of High-speed Inlet Flows Using the Navier-Stokes Equations

Knight¹

1981

Journal of Aircraft

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A numerical code has been developed to calculate the flowfield in two-dimensional high-speed inlets using the Navier-Stokes equations. Arbitrary inlet geometries may be treated, with variable bleed on the ramp and cowl surfaces. Turbulence is incorporated through an algebraic turbulent eddy viscosity. The code has been applied to the calculation of the flow in a simulated high-speed inlet operating at a Mach number of 2.5 and Reynolds number of 1.4 xlO 7 based on inlet length. Two different bleed schedules were considered, which differed principally in the extent of bleed in the vicinity of the shock-turbulent boundary interactions on the ramp surface. The computed results are compared with detailed measurements of the ramp and cowl static pressures, and boundary-layer pitot profiles. The agreement with the experimental data is generally good, although the experimental data display evidence of three dimensionality over a portion of the inlet flowfield. Nomenclaturem = bleed mass flux =p w v w (m<0 for bleed) p = static pressure p p = pitot pressure p t -total pressure «. = friction velocity =Vr vv /p vv v w = bleed velocity at wall x,y,z = Cartesian coordinates y' = distance normal to wall y' m -height of computational sublayer Af, Arj = mesh spacing in f and 77 directions 60 = reference boundary-layer thickness for relaxation model 6 = boundary-layer thickness e = turbulent eddy viscosity f, 17 = transformed coordinates X = relaxation length v = kinematic viscosity p = density T = shear stress Subscripts oo = evaluated upstream of body w = evaluated at wall

show abstract

Calculation of the three-dimensional flow field in supersonic inlets at angle of attack using a bicharacteristic method with discrete shock wave fitting

Cited by 4 publications

References 3 publications

Numerical simulation of HSCT inlet operability with angle of attack

Numerical simulation of HSCT inlet operability with angle of attack

Improved Calculation of High Speed Inlet Flows: Part I. Numerical Algorithm

Calculation of High-speed Inlet Flows Using the Navier-Stokes Equations

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