Unsteady Pressure Measurements on a Biconvex Airfoil in a Transonic Oscillating Cascade

Shaw, L. M.; Boldman, D. R.; Buggele, A. E.; Buffum, Daniel H.

doi:10.1115/1.3239885

Cited by 19 publications

(6 citation statements)

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“…There are no shock waves at high subsonic inlet Mach numbers (about 0.95) when transonic stall flutter occurred in their study [1]. Shwa et al [2] demonstrates that the energy from shock wave oscillations is not strong enough to induce the transonic stall flutter based on a shock wave motion model. On the other hand, unsteady shock oscillation rather than blade stall was found to be the driving mechanism for flutter instability in a transonic fan [3].…”

Section: Introductionmentioning

confidence: 79%

Stall Flutter Simulation of a Transonic Axial Compressor Stage Using a Fully Coupled Fluid-Structure Interaction

Gan

Zha

2017

55th AIAA Aerospace Sciences Meeting

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In this paper, numerical simulation of stall flutter for full annulus NASA Stage 35 is conducted using a fully coupled fluid/structure interaction. Time accurate compressible 3D Navier-Stokes equations with Spalart-Allmaras turbulence model are solved with a system of 5 decoupled structural modal equations in a fully coupled manner. The 3rd order WENO scheme for the inviscid flux and 2nd order central difference for the viscous terms are used to accurately capture the interactions of the fluid and structure. Delayed detached eddy simulation is also applied to predict the flow induced vibration at near and stall conditions for comparison. The mechanism and aerodynamic damping behavior causing the stall flutter are analyzed. The effect of rotor stator interaction on the onset of flutter is studied. The fully coupled FSI simulation shows that Stage 35 has stall flutter at rotating stall.

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Section: Introductionmentioning

confidence: 79%

Stall Flutter Simulation of a Transonic Axial Compressor Stage Using a Fully Coupled Fluid-Structure Interaction

Gan

Zha

2017

55th AIAA Aerospace Sciences Meeting

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“…The facility, NASA Transonic Flutter Cascade (TFC), has been described in detail in Buffum et al (1996), Boldman and Buggele (1978), and Shaw et al (1986). The facility is a linear cascade of nine blades.…”

Section: Test Facility Upgradementioning

confidence: 99%

Intermittent Flow Regimes in a Transonic Fan Airfoil Cascade

Lepicovsky¹,

McFarland²,

Chima³

et al. 2004

The International Journal of Rotating Machinery

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A study was conducted in the NASA Glenn Research Center (NASA-GRC) linear cascade on the intermittent flow on the suction surface of an airfoil section from the tip region of a modern low aspect ratio fan blade. Experimental results revealed that, at a large incidence angle, a range of transonic inlet Mach numbers exist where the leading-edge shock-wave pattern was unstable. Flush-mounted, high-frequency response pressure transducers indicated large local jumps in the pressure in the leading edge area, which generates large intermittent loading on the blade leading edge. These measurements suggest that for an inlet Mach number between 0.9 and 1.0, the flow is bi-stable, randomly switching between subsonic and supersonic flows. Hence, it appears that the change in overall flow conditions in the transonic region is based on the rate of switching between two stable flow states rather than on the continuous increase of the flow velocity. To date, this flow behavior has only been observed in a linear transonic cascade. Further research is necessary to confirm this phenomenon occurs in actual transonic fans and is not the by-product of an endwall restricted linear cascade.

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“…These shock-induced oscillations and aerodynamic instabilities produced flutter and aero-acoustic vibrations that were deemed detrimental for the vehicle. 21–23 Several experimental and numerical studies reveal that various parameters like Mach number, Reynolds number, time taken by the shock oscillations, and air humidity affect the unsteady behavior of shock wave. 24–26…”

Section: Passive Flow Control Techniquesmentioning

confidence: 99%

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

Rashid

Nawaz

Maqsood

et al. 2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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Typical challenges of supersonic flight include wave drag, acoustic signature, and aerodynamic heating due to the formation of shock waves ahead of the vehicle. Efforts in the form of sleek aerodynamic designs, better propulsion systems, and the implementation of passive and active techniques are generally adopted to achieve a weaker shock wave system. Shock reduction can improve flight range, reduce fuel consumption, and provide thermal protection of the forebody region. This paper briefly reviews shock reduction techniques, including passive, active, and hybrid flow control. Airfoil shape optimization, mechanical spike, and forebody cavities are studied as passive flow control approaches. For active flow control, developments in the area of opposing jets and energy deposition are explored. The combination of active and passive flow control and the hybrid flow techniques are discussed in the end. The discussions include the principle of operation, physics of fluid behavior, and overall contribution to flight stability characteristics. The implications in the usage of these technologies, along with potential gaps, are also identified. This comprehensive review can serve as the basis for contemporary solutions to realize sustainable supersonic travel for the aviation industry.

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Unsteady Pressure Measurements on a Biconvex Airfoil in a Transonic Oscillating Cascade

Cited by 19 publications

References 1 publication

Stall Flutter Simulation of a Transonic Axial Compressor Stage Using a Fully Coupled Fluid-Structure Interaction

Stall Flutter Simulation of a Transonic Axial Compressor Stage Using a Fully Coupled Fluid-Structure Interaction

Intermittent Flow Regimes in a Transonic Fan Airfoil Cascade

Review of wave drag reduction techniques: Advances in active, passive, and hybrid flow control

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