A theoretical and experimental investigation of the compressible laminar wake behind a long slender cylinder.

Au, Robert H.; Berger, Stanley A.

doi:10.2514/3.4800

Cited by 2 publications

(3 citation statements)

References 11 publications

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“…(6) and (7) that the initial profiles [E_qs. (4) and (5)] are recovered for * = 0, that u(x~oo)^h(x=oo) = 0 and it, /z(>=±oo) = 0, and that u, h(y\P) = u, h(-y\\/P), as expected. Furthermore, in the limit of large x the solutions reduce to the familiar asymptotic form for laminar wakes, which do not contain P and depend only on the similarity variable y/ldx.…”

supporting

confidence: 55%

“…Furthermore, in the limit of large x the solutions reduce to the familiar asymptotic form for laminar wakes, which do not contain P and depend only on the similarity variable y/ldx. Since experimental data with P^O are unavailable, a minimum validity check of these formulas should be their ability to reproduce, in the limit P=l, the classical twodimensional wake solution found originally by Goldstein 3 and subsequently verified independently by Au and Berger, 4 Zeiberg and Kaplan, 5 and others. 6 Indeed, for the case of symmetry there is good mutual agreement among these theories, including the present one.…”

mentioning

confidence: 96%

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The two-dimensional laminar wake with initial asymmetry

Demetriades

1983

AIAA Journal

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A FREQUENT problem in laser cavity flows, airfoil aerodynamics, and similar two-dimensional fluid problems is the mixing of two identical uniform, compressible streams past a sharp trailing edge (TE) of a partition, on one side of which the laminar boundary layer is thicker than it is on the other. Since the streams are identical, this configuration resembles an ordinary two-dimensional wake; however, the disparity in the boundary-layer thicknesses is bound to introduce asymmetries in the flow, especially beyond but near the trailing edge. The distance beyond the latter over which such asymmetries persist is of significance, especially if no restrictions are placed on the flow Mach number M e and the temperature ratio T w /T oe of the solid partition relative to the stagnation temperature of the stream. This Note aims at presenting formulas valid for such an asymmetric wake for any M e and T w /T oe and any degree of asymmetry introduced via the ratio P=6 } /6 2 , where 0 is the boundary-layer momentum thickness at the trailing edge and subscripts 7 and 2 refer to the two sides of the partition.

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confidence: 55%

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confidence: 96%

The two-dimensional laminar wake with initial asymmetry

Demetriades

1983

AIAA Journal

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“…Thus the present experimental investigation of far wakes behind two-dimensional slender bodies covering the flow regime from the wake neck downstream to the linear far wake has been carried out to provide local mean-flow data for comparison with stability theory 30 and laminar wake analyses. 28 ' 31~33 Complete tabulated data are available in Ref. 34 for use in this comparison.…”

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confidence: 99%

Experimental investigation of far wakes behind two-dimensional slender bodies at M sub infinity equals 6

Batt

Kubota

1969

AIAA Journal

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An experimental investigation has been conducted at M^ = 6 to determine mean flow properties for far wakes behind several two-dimensional slender bodies at zero angle of attack. The adiabatic wall configurations tested included a flat-plate model and two 20° wedge models which differed by a factor of two in base height. The effect of wall temperature was examined by cooling the larger wedge model to a temperature of about two tenths of the freestream stagnation temperature. Freestream Reynolds numbers were varied from 50,000 to 200,000 per in. for each of these four configurations. Profile measurements of total temperature and Pitot pressure were combined with centerline static pressures to determine completely the far-wake flowfield from the wake neck downstream to the linear far wake. The effect of transition on mean flow properties was determined. Comparison of laminar wake data for adiabatic wall models with linear wake theory was favorable. Maximum centerline pressures in the far wake for all configurations were generally 10% higher than the freestream pressure. For the cold wall wedge the maximum centerline enthalpy for all cases occurred two base heights downstream of the model base and was triple the magnitude of the freestream enthalpy. The decay rate of enthalpy was "small" when the far wake was laminar.

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A theoretical and experimental investigation of the compressible laminar wake behind a long slender cylinder.

Cited by 2 publications

References 11 publications

The two-dimensional laminar wake with initial asymmetry

The two-dimensional laminar wake with initial asymmetry

Experimental investigation of far wakes behind two-dimensional slender bodies at M sub infinity equals 6

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