Hypersonic Flow Along Two Intersecting Planes

Cresci, Robert J.

doi:10.21236/ad0633949

Cited by 9 publications

(4 citation statements)

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“…942-949. 32 Vigneron, Y.C., Rakich, J.V., and Tannehill, J.C., "Calculation of Supersonic Viscous Flow over Delta Wings with Sharp Subsonic Leading Edges," AIAA Paper 78-1137, July 1978. 33 Newsome, R.W., "A Comparison of Euler and Navier-Stokes Solutions for Supersonic Flow over a Conical Delta Wing," AIAA Paper 85-0111, Jan. 1985.…”

Section: Future Prospectsmentioning

confidence: 99%

“…The axial transformation is specified by (32) where A and B are parameters used to fit the transformation, subscript T denotes the physical location about which the transformation is centered, and £ is equal to the number of axial grid locations. The radiaf transformation is…”

Section: Coordinate Transformationmentioning

confidence: 99%

“…The axial transformation is identical to that used for the cylindrical coordinate system, [Eq. (32)]. The y-coordinate transformation is specified by <*(x,y) -(T) -1 < a < 1…”

Section: Coordinate Transformationmentioning

confidence: 99%

“…(32)(33)(34), is related to the location in physical space, relative to the central point of the interpolating cube, by AC = C Ax, AT] * T) Ax + T) Ar + TuA9, A4> = <j> n A9 (40) x…”

Section: Interpolationmentioning

confidence: 99%

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Numerical Methods for Engine-Airframe Integration

Murthy¹,

Paynter²

1986

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Section: Future Prospectsmentioning

confidence: 99%

Section: Coordinate Transformationmentioning

confidence: 99%

“…The axial transformation is identical to that used for the cylindrical coordinate system, [Eq. (32)]. The y-coordinate transformation is specified by <*(x,y) -(T) -1 < a < 1…”

Section: Coordinate Transformationmentioning

confidence: 99%

“…(32)(33)(34), is related to the location in physical space, relative to the central point of the interpolating cube, by AC = C Ax, AT] * T) Ax + T) Ar + TuA9, A4> = <j> n A9 (40) x…”

Section: Interpolationmentioning

confidence: 99%

See 2 more Smart Citations

Numerical Methods for Engine-Airframe Integration

Murthy¹,

Paynter²

1986

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Supersonic interference flow along the corner of intersecting wedges.

Charwat

Redekopp

1967

AIAA Journal

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Hypersonic interaction along a rectangular corner

et al. 1969

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An investigation of the behavior of the three-dimensional hypersonic flow along intersecting planes has been conducted, considering both the viscous and inviscid flows and their mutual interaction. The experimental program involves measurements of surface pressures and heat-transfer rates in the vicinity of a 90° corner. The local forces and shear stresses can be obtained thereby, yielding some information on the nature of the three-dimensional boundary-layer behavior in this region. Pilot pressure contours are also obtained and utilized in the determination of the complex intersecting shock pattern in the corner. The test data was obtained at a freestream Mach number of 11.2 and a Reynolds number of 1.5 X 10 4 /in. A theoretical analysis of the corner flow was obtained by the development of a set of equations valid throughout the boundary layer, shock wave structure, and inviscid core as previously proposed by Rubin for two-dimensional and axisymmetric flows. This analysis has been shown to be valid in the continuum merged layer and in the viscous interaction regions downstream. The theory is extended here to the three-dimensional corner configuration. Where applicable, the theoretical solutions were compared to the experiments and very good agreement was found to exist over the entire spectrum of flow variables. Nomenclatureheat-transfer coefficient H = stagnation enthalpy ft = coefficient of thermal conductivity L = yM m z /Re m = reference length M = Mach number p -pressure q -surface heat transfer rate Re x = pux/p, -Reynolds number based on x Re m = POO^OO/MOO = freestream unit Reynolds number St -Qw/pu m (Haa ~ HW) = Stanton number T = temperature u = u/u^ -nondimensional velocity in the x direction u = physical velocity in the x diiection v = v/Uo>8 = nondimensional velocity in the y direction v = physical velocity in the y direction V = x/Moo 2 = rarefaction parameter w = w/u m 8 = nondimensional velocity in the z direction w = physical velocity in the z direction x = x/L = nondimensional x coordinate x = physical coordinate in the streamwise direction y = 3/8 = nondimensional y coordinate y = physical coordinate along vertical surface normal to x axis z s = two-dimensional shock displacement thickness z = z/~b = nondimensional z coordinate z = physical coordinate along horizontal surface normal to x axis 7 = ratio of specific heats 8 = (l/7 1/2 Moo) = reference number Aerospace Engineering. Associate AIAA. t NASA Trainee. § Research Fellow. 8' = physical boundary-layer thickness 8 = 8L = reference length f = z/z s = z coordinate normalized with respect to the shock layer thickness P = density M = coefficient of viscosity a-= Prandtl number T = ^(bufby) = shear stress M M *(C/Re 0 rameter _)!/2 _ viscous-inviscid interaction paSubscripts e s t w Z -> oo 2 -D = conditions external to boundary layer = stagnation conditions = Pitot conditions = conditions evaluated at the surface = flat plate conditions = freestream conditions = conditions behind a normal shock Superscript (") = physical flow variables

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Hypersonic Flow Along Two Intersecting Planes

Cited by 9 publications

References 0 publications

Numerical Methods for Engine-Airframe Integration

Numerical Methods for Engine-Airframe Integration

Supersonic interference flow along the corner of intersecting wedges.

Hypersonic interaction along a rectangular corner

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