An Experimental Investigation of Turbulent Transonic Viscous-Inviscid Interactions

Alber, Irwin E.; Bacon, John W.; Masson, Bruce S.; Collins, Donald J.

doi:10.2514/3.50501

Cited by 34 publications

(12 citation statements)

References 10 publications

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“…The broken lines marked in figure 3(b) correspond to a number of (analytically determined) predicted limits for the onset of incipient separation, including that proposed by Inger (1976) (which also appeared on Delery's plot, see figure 1), Nussdorfer (1956) and Alber et al (1973). All of the limits shown in figure 3(b) are in reasonable agreement at low Re but exhibit different trends and thus diverge as Re increases.…”

Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 54%

“…Inger's theory, in contrast, which takes both effects into account to some extent, actually predicts a slight decrease in the value of M ∞ required for separation with increasing H i0 . The criteria of Nussdorfer (1956) and Alber et al (1973) do not incorporate H i0 or Re at all and, therefore, show no variation with separation limits of M ∞ = 1.3 and 1.33, respectively. Crucially though, while some predicted limits are perhaps better than others, none of them can explain the considerable scatter observed in experimental data.…”

Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 99%

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Corner effect and separation in transonic channel flows

et al. 2011

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An investigation into parameters affecting separation in normal shock wave/boundary layer interactions (SBLIs) has been conducted. It has been shown that the effective aspect ratio of an experimental facility (defined as δ * /tunnel width) is a critical factor in determining when shock-induced separation will occur. Experiments examining M ∞ = 1.4 and 1.5 normal shock waves in a wind tunnel with a small rectangular cross-section have been performed and show that a link exists between the extent of shock-induced separation on the tunnel centre-line and the size of corner-flow separations. In tests where the corner-flows were modified ahead of the shock (through suction and vortex generators), the extent of separation around the tunnel centre-line was seen to vary significantly. These observations are attributed to the way corner flows modify the three-dimensional shock-structure and the impact this has on the magnitude of the adverse pressure gradient experienced by the tunnel wall boundary layers.

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Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 54%

Section: Review Of Factors Affecting Separation In Normal Sblismentioning

confidence: 99%

Corner effect and separation in transonic channel flows

et al. 2011

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“…(16) also vanish, producing a singularity. The singularity is removed by expressing the displacement thickness 6* in terms of U T , 6,, and U e through the definition 6*= \ (l-pu/p e u e )-(r/r w )dy j o (17) The result is differentiated with respect to x, producing a third equation, A 3I (U T ) x +A 32 d ix +A 33 (U e ) x +A 34 d; = B 3 (18) where the A 3j and B 3 are functions of U T , <5,, and U e . Like the coefficients A n and A 2] , the coefficient A 31 also vanishes when £/ T =0.…”

Section: Equations Solvedmentioning

confidence: 99%

Calculation of Separated Turbulent Flows on Axisymmetric Afterbodies Including Exhaust Plume Effects

Kuhn

1980

AIAA Journal

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A calculative method is presented for turbulent boundary-layer, inviscid flow interactions for axisymmetric configurations of the type used for isolated nozzle afterbody models. The method is applicable to flows with subsonic freestreams, including slightly supercritical flows, and to bodies with high-pressure exhaust plumes or solid plume simulators. Integral boundary-layer and plume entrainment methods are coupled iteratively with a finite-difference inviscid flow method through a boundary-layer plume displacement thickness. Results are presented which indicate that the procedure provides an accurate engineering prediction method for boattail flowfield with moderately underexpanded exhaust flows and for bodies with solid plume simulators.M Nomenclature = coefficients, Eqs. (16), (18), and (28) = term, Eqs. (16), (18), and (32) = HwT eo /n e9 T w -skin-friction coefficient = maximum body diameter = transformed shape factor, Eq. (19) = entrainment fraction, Eqs. (22) and (23) = reference length = Mach number = pressure = radius -T t /T te -\ = functional forms of 5 defined in Eqs. (24-26) = root-mean-square error, Eq. (2) = temperature = transverse curvature factor in Eq. (12), 2L/r 2 w = transformed X, Y velocity components = wake velocity defined in Eq . ( 1 3) = friction velocity, Eq . ( 1 4) -x, r velocity components = functional forms of u defined in Eq. (22) = transformed coordinates = physical coordinates defined in Fig. 3 = location of separation point, Fig. 1 = location of minimum velocity, Fig. 4 = transformed coordinate [Eq. (15)] r = )o (r/L)dy = eddy viscosity factor, T/n(du/dy) -ratio of specific heats = transformed boundary-layer thickness = displacement thickness = half-angle of conical displacement surface = molecular viscosity Subscripts 0 = undisturbed freestream c = inviscid core of exhaust jet e = boundary-layer edge 7 = inviscid flow j = conditions in exhaust nozzle t = stagnation conditions V = viscous flow w = conditions on a solid surface or at the inviscid jet boundary ( ) x = differentiation with respect to x

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“…It there fore seems that u e (x )6 (x) and C f (x) are lon ical choices for the parameters of the velocity profile. Now for incompressible turbulen t non-separated boundary layers , i t i s well kno w n tha t [13] have shown that this pr ofile can be modified to account for compressibility , and Alber et al . [13] and Kuhn and N ielsen [2 -3 ] have shown that the profile can be modified to include both reverse flow and a lam inar sublayer.…”

Section: Choice Of V E L O C I T Y P R O F I Lementioning

confidence: 99%

“…Alber et al [13] have presented measurements made in a two-dimensional transonic s e p a r a t i n g boundary layer…”

mentioning

confidence: 99%

Development of a Method for Predicting Subsonic Turbulent Separating Boundary Layers.

Gerhart¹,

Chima²

1978

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An Experimental Investigation of Turbulent Transonic Viscous-Inviscid Interactions

Cited by 34 publications

References 10 publications

Corner effect and separation in transonic channel flows

Corner effect and separation in transonic channel flows

Calculation of Separated Turbulent Flows on Axisymmetric Afterbodies Including Exhaust Plume Effects

Development of a Method for Predicting Subsonic Turbulent Separating Boundary Layers.

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