Leading-edge bluntness effects in high enthalpy, hypersonic compression corner flow

Mallinson, S. G.; Gai, S. L.; Mudford, N. R.

doi:10.2514/3.13392

Cited by 14 publications

(4 citation statements)

References 25 publications

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“…[3][4][5] In order to reduce aerodynamic resistance, an extremely sharp wing leading edge is required and a radius with a magnitude of millimeters is commonly employed. [6][7][8] In contrast to traditional subsonic and supersonic conditions, since the speed of hypersonic aircraft has been raised significantly, high temperature becomes one of the vital features, as most of the kinetic energy of the high speed airflow, just outside the sharp local structure, transforms into internal energy. 9 This is the result of a strong action of compression, friction and viscous dissipation, and it makes heat flux transmitted into the leading edge becomes intense.…”

Section: Introductionmentioning

confidence: 98%

RETRACTED: Thermal protection mechanism of heat pipe in leading edge under hypersonic conditions

Wang

et al. 2015

Chinese Journal of Aeronautics

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Section: Introductionmentioning

confidence: 98%

RETRACTED: Thermal protection mechanism of heat pipe in leading edge under hypersonic conditions

Wang

et al. 2015

Chinese Journal of Aeronautics

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“…Studies related to bluntness effects on pressure, skin-friction and heat transfer in both attached and separated flows have also been conducted, for example, Bertram (1954), Bertram & Henderson (1958), Cheng et al. (1961), Holden (1971), Stollery (1972), and in recent years, Mason & Lee (1994), Smith & Khorrami (1994), Mallinson, Gai & Mudford (1996), Marini (1998), Borovoy, Skuratov & Struminskaya (2008), Borovoy et al. (2014), John & Kulkarni (2014), Khraibut, Gai & Neely (2019) and Mallinson, Mudford & Gai (2020).…”

Section: Introductionmentioning

confidence: 99%

“…Later, Mallinson et al. (1996) and Khraibut et al. (2019) analysed bluntness effects using this same parameter.…”

Section: Introductionmentioning

confidence: 99%

Wall temperature and bluntness effects on hypersonic laminar separation at a compression corner

2021

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“…The value of βb is above 0.1 indicating a viscous-dominated regime, while the other cases with βb below 0.1 showing a blunt-dominated regime. [25][26] The separation point xs and reattachment point xr vary with the impingement point xi, as shown in Fig. 17.…”

Section: Swbli Near a Convex Corner Downstream Of A Flat Plate Witmentioning

confidence: 98%

Leading Edge Bluntness Effects on Shock Wave/Boundary Layer Interactions Near a Convex Corner

Yang²

2015

20th AIAA International Space Planes and Hypersonic Systems and Technologies Conference

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The cowl shock/ingested forebody boundary layer interaction is usually encountered near the hypersonic inlet shoulder, a convex corner, and sometimes causes the inlet to unstart. The bluntness of the forebody leading edge also affects the downstream convex corner flow, and that should be carefully considered to improve the inlet performance. A twodimensional inlet with a sharp leading edge and a series of blunt leading edges at Mach 5 were numerically studied. The relative positions of the cowl shock and the convex corner were changed to reveal the characteristics of the shock wave/boundary layer interactions with the corner expansion wave interference. Flow patterns and the distributions of surface pressure, heat flux, and friction coefficient involved were thoroughly studied. The results indicate that the boundary layer is even thicker and the flow is easier to separate when the bluntness of the leading edge increases. The variation trends of the separation extent with a sharp leading edge agree reasonably well with the estimations on the basis of inviscid analysis. However, the inviscid formulas established in the sharp leading edge case are not suitable for the blunt leading edge cases. With the aid of viscous simulations, it is found that the upstream effect of the corner extend a little farther and the dimensionless relative position range that can largely reduce the separation narrows with the increasing of the leading edge bluntness. To take into account the nonuniform flow in the boundary layer, a rapid calculation method of the incident shock (B. L.) was established. It is shown that the shock (B. L.) impinges on the corner can minimize the separation in the sharp leading edge case. However, the shock (B. L.) has to move downstream to minimize the separation when the leading edge is blunt. NomenclatureC * = Chapman-Rubensin constant, (µ/µ∞)(T∞/T) CD = drag coefficient of a hemicylinder cp = specific heat capacity of air at constant pressure d1 = distance between the convex corner and the first demarcation point of the inviscid shock impingement d2, d2', d2" = distance between the convex corner and the second demarcation point of the inviscid shock impingement d3 = distance between the convex corner and the third demarcation point of the inviscid shock impingement dn = diameter of the blunt leading edge Ls, Lsx = separation bubble length along the wall and along the x-axis, respectively Ma = Mach number M1, M2 = Mach number upstream and downstream of the incident shock, respectively M3 = Mach number downstream of the reflected shock at the flat plate Mc = Mach number downstream of the corner expansion M∞ = freestream Mach number p∞ = freestream static pressure q = heat flux rate Rn = radius of the blunt leading edge Re = Reynolds number 2 St = Stanton number, St = q/[ρ∞U∞cp (T0-Tw)] T0, T∞, Tw = Total temperature, freestream temperature, and wall temperature, respectively U∞ = freestream flow velocity x = x-axis coordinate xc = distance from the convex corner to the leading edge of the flat plate xi, xr,...

show abstract

Leading-edge bluntness effects in high enthalpy, hypersonic compression corner flow

Cited by 14 publications

References 25 publications

RETRACTED: Thermal protection mechanism of heat pipe in leading edge under hypersonic conditions

RETRACTED: Thermal protection mechanism of heat pipe in leading edge under hypersonic conditions

Wall temperature and bluntness effects on hypersonic laminar separation at a compression corner

Leading Edge Bluntness Effects on Shock Wave/Boundary Layer Interactions Near a Convex Corner

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