Flow Control By Pulsed Jet In A Highly Bended S-Duct

Eric, Guenther-Gleason; Leplat, Michel; Monnier, Jean CLaude; Delva, Jérôme

doi:10.2514/6.2012-3250

Cited by 23 publications

(35 citation statements)

References 9 publications

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“…In this line, there is no evidence of any separation whatever the case. PIV results presented in [16] confirm the fact that the flow is attached in the continuous blowing case and that a very small separation bubble may exist in the 525 Hz case (the distance of the first PIV point to the wall being too high to draw definitive conclusion on this point). More generally, the fact that the flow is essentially reattached in the controlled cases suggests that the remaining total pressure losses in the AIP are mainly due to secondary flows.…”

Section: Article In Advance / Garniersupporting

confidence: 87%

“…2, where the background grid is used to evidence the curvature of the duct surface. This grid is shown with every four points of the grid used for the computations of [16]. The actuators are directed toward the symmetry plane.…”

Section: B Actuator Characteristicsmentioning

confidence: 99%

“…It allows following the aperture of the actuator, and the associated signal will be used in the following as a reference signal for phase averages. Following the specifications coming from a previous numerical study [16], nozzles with a throat diameter equal to 0.94 mm and an output diameter of 1 mm were manufactured and integrated on the model with pitch α and skew β angle respectively equal to 30 and 75 deg. The latter angle denotes a rotation around the normal n) to the surface at the actuator position and the former angle to a rotation around a vector perpendicular to the plane defined by the vector normal to the surface and the vector tangent to the surface turned by the second angle.…”

Section: B Actuator Characteristicsmentioning

confidence: 99%

“…The preliminary computational fluid dynamics (CFD) study that helped to define the duct geometry and specify the actuators characteristics has already been presented in [16]. Moreover, the attempts to perform PIV in this duct have been detailed in the aforementioned reference.…”

Section: Introductionmentioning

confidence: 99%

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Flow Control by Pulsed Jet in a Curved S-Duct: A Spectral Analysis

Garnier

2015

AIAA Journal

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This paper presents an experiment of flow control by supersonic pulsed jets in a very aggressive S-duct typical of modern fighter aircraft engine inlet ducts. The Mach number in the aerodynamic interface plane ranges from 0.2 to 0.4, which is realistic from an application point of view. It was shown that, with continuous blowing, the flow could be fully reattached. The sensitivity of the distortion coefficient to the jet frequency was also clearly evidenced. Surprisingly, it is recommended to avoid actuating the jets at the natural frequencies present in the separated zone of the uncontrolled flow. Besides, it is observed that pulsed jets actuation increases the unsteady flow distortion. Furthermore, in the uncontrolled flow, a lateral movement of the structures associated with high total pressure losses in the aerodynamic interface plane was highlighted. Nomenclature c = velocity of sound, m∕s D 1 = inflow section diameter, mm D 2 = exit section diameter, mm d = jet diameter, mm d a = average duct diameter, mm Ef = spectral density of power, Pa 2 ∕Hz f = frequency, Hz H = offset of the outlet section with respect to the inflow section, mm L = jet stroke length, m L duct = distance from the bell mouth to the translating plug, mm L sep = separation length estimated from the pressure distribution, mm Ma = averaged Mach number in the aerodynamic interface plane Ma 1= isentropic Mach number in the inflow section P dyn = dynamic pressure in the inflow section, Pa Pi = stagnation pressure in the aerodynamic interface plane, Pa Pi 0 = external atmospheric stagnation pressure, Pa Ps 1 = inlet static pressure, Pa Q d = duct mean mass flow rate, g∕s Q dyn = dynamic pressure in the aerodynamic interface plane, Pa Q j = total jet mean mass flow rate, g∕s T = forcing period, s (t, r, n) = frame of reference local to the jets U 1 = velocity in the inflow section, m∕s x, y, z = longitudinal, vertical, and spanwise directions (respectively), mm α = jet pitch angle, deg β = jet skew angle, deg η = duct mean efficiency Φ = angle along the duct circumference, deg <> = operator that denotes an averaging on the 40 pressure sensors in the aerodynamic interface plane

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Section: Article In Advance / Garniersupporting

confidence: 87%

Section: B Actuator Characteristicsmentioning

confidence: 99%

Section: B Actuator Characteristicsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Flow Control by Pulsed Jet in a Curved S-Duct: A Spectral Analysis

Garnier

2015

AIAA Journal

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“…This is associated with a loss in total pressure in the lower sector of the AIP [3,11,12]. However, it was demonstrated by Berens et al [13] that time averaged data can be misleading, and the use of Delayed Detached…”

Section: Fig 1 S-duct Geometry Definitionmentioning

confidence: 99%