On the separation of the unsteady laminar boundary layer

Moore, F. K.

doi:10.1007/978-3-642-45885-9_23

Cited by 81 publications

(55 citation statements)

References 3 publications

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“…In the same year, Sears (1956) made an assumption that the unsteady separation point was characterized by the simultaneous vanishing of the shear and of the velocity at a point within the boundary layer as seen by an observer in a coordinate system convected with the separation velocity. Two years later, Moore (1958), while investigating a steady flow over a moving wall, arrived at a model analogous to that for unsteady separation. He stated, "for a slowly moving wall separation occurs when, at some point in the boundary layer, the profile velocity and shear simultaneously vanish".…”

Section: Flow Separationmentioning

confidence: 99%

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

Rediniotis¹

2004

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the tir gathering and maintaining the data needed, and completing and reviewing the collection of information. Send commenjs regi of information, including suggestions for reducing the burden, PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)Texas Engineering Experiment Station Texas A&M University CoUege Station Texas 77843-3141 This work presents an investigation of synthetic jet actuation for separation control over wings/airfoils, in steady and unsteady flows, the development of hi^-power, compact synthetic jet actuators (SJA) for flow separation control, the modelmg and control of such actuators and the modeling and control of the resulting SJA-controUed aerodynamics and wing/airfoil, respectively. The developed actuator is compact enough to fit in the interior of a NACA0015 profiled wing with a chord of 0.375 m. Test bench experiments showed that the multi-piston actuator array was capable of producing exit velocities of up to 90 m/s for an actuator frequency of 130 Hz. The actuator was placed in a NACA 0015 wmg and tested m a wmd tunnel. An experimental investigation into the effects of a synthetic jet actuator on the performance of the wing, in steady flow, is described. Emphasis is placed on the capabilities of the actoator to control the separation of the flow over the wing at high angles of attack. The investigation included the use of force balance measurements, on -surface flow visualization with oil and tufts, off-surface flow vBualizations with smoke, surface pressure distribution measurements and wake surveys. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)USAF

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Section: Flow Separationmentioning

confidence: 99%

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

Rediniotis¹

2004

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“…Returning to the boundary layer problem, non-small oscillations of the freestream (but still limited to non-reversing freestreams) have been tackled by Moore (1951Moore ( ), (1957 and Pedley (1972) for regions close to the leading edge of the plate, and i t is again found that the flow is Blasius like. Lin (1956), Gibson (1957) and Pedley (1972) studied the far downstream region, and found the flow takes on a double structure similar to that observed in the analogous small amplitude case.…”

Section: Introductionmentioning

confidence: 99%

The response of a laminar boundary layer in supersonic flow to small-amplitude progressive waves

Duck

1990

J. Fluid Mech.

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In this paper the effect of a small-amplitude progressive wave on the laminar boundary layer on a semi-infinite flat plate, due to a uniform supersonic free-stream flow is considered. The perturbation to the flow caused by the wave divides into two streamwise zones. In the first, relatively close to the leading edge of the plate, on a transverse scale comparable with the boundary-layer thickness, the perturbation flow is described by a form of the unsteady linearized compressible boundary-layer equations. In the free stream, this component of flow is governed by the wave equation, the solution of which provides the outer velocity conditions for the boundary layer. This boundary-layer system is solved numerically, and also the asymptotic structure in the far downstream limit is studied. This reveals a breakdown and a subsequent second streamwise zone, where the flow disturbance is predominantly inviscid. The two zones are shown to match in a proper asymptotic sense.

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“…The agreement between the values obtained by using the correlations (28) and (29) and the LES results is better then 10% for the whole range of considered Reynolds numbers. Obviously, the asymptotic limit cases are also included in the above set.…”

Section: Archival Correlations For Mean Heat Transfermentioning

confidence: 55%

“…the rotating disk) changes the separation condition. Then, the two-dimensional separation criterion ∂u ∂z d = 0 (11) at the wall has to be replaced by the so-called MRS-criterion [28][29][30][31] ∂u ∂z = 0 at regions with vanishing velocity u = 0 (12) satisfied normally within the flow domain. The separated flow is usually unsteady, and the laminar boundary layer theory does not offer an efficient approach for calculating the flow [28].…”

Section: Problem Formulamentioning

confidence: 99%

Heat transfer from a rotating disk in a parallel air crossflow

Wiesche

2007

International Journal of Thermal Sciences

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On the separation of the unsteady laminar boundary layer

Cited by 81 publications

References 3 publications

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

Synthetic Jet Actuation - Modeling, Actuator Development and Application to Separation Control

The response of a laminar boundary layer in supersonic flow to small-amplitude progressive waves

Heat transfer from a rotating disk in a parallel air crossflow

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