Post-stall flow control on an airfoil using localized jet actuators

He, Yanyu; Kralt, Linda D.

doi:10.2514/6.2000-408

Cited by 6 publications

(6 citation statements)

References 7 publications

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“…In the recent years a large amount of numerical computations and simulations has been produced in the area of flow separation control over lifting surfaces via synthetic jet actuators (Donovan et al, 1998, Hassan and Munts, 2000, He and Krai, 2000, and He et al, 2001. Another application of synthetic jet technology is the control of the aerodynamic performance of lifting surfaces through fluidic modifications of their apparent aerodynamic shape , Honohan et al, 2000, Parekh and Glezer, 2000.…”

Section: Synthetic Jet Actuators (Sjas)mentioning

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: Synthetic Jet Actuators (Sjas)mentioning

confidence: 99%

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

Rediniotis¹

2004

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“…To help reduce experimental costs, computational fluid dynamics (CFD) are being used to predict these complex flows and to provide detailed pressure and force and moment data. There have been several recent numerical studies [8,9] of flow separation control witii syntiietic jet actuators. He and Rral [8] have used Reynolds-averaged Navier-Stokes (RANS) to study the effect of jet location and jet-forcing frequency on the lift and drag forces on an airfoil.…”

Section: Introductionmentioning

confidence: 99%

“…There have been several recent numerical studies [8,9] of flow separation control witii syntiietic jet actuators. He and Rral [8] have used Reynolds-averaged Navier-Stokes (RANS) to study the effect of jet location and jet-forcing frequency on the lift and drag forces on an airfoil. The jet actuator was shown to increase the time-averaged lift but also increased the amplitude of oscillation.…”

Section: Introductionmentioning

confidence: 99%

Unsteady Numerical Simulations of Subsonic Flow over a Projectile with Jet Interaction

Sahu

2003

41st Aerospace Sciences Meeting and Exhibit

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Public rqjorting burden for this collection of infonnarion is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining flie data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information including suggestions for reducing the burden, to Department of Defense, Washington Headquarters Services, Directorate for Informahon Operations and Reports (0704-01 Sg), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Re^wndents should be aware that notwithManding any other provision of law, no person shall be subject to any pmalty for failing to comply with a collection of * information if It docs not display a currently valid OMB control number.iplay a currently PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)May 2003 ARL-TR-297510. SPONSOR/MONITOR'S ACRONYM{S) SPONSOR/MONITOR'S REPORT NUMBER(S) DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution is unlimited. SUPPLEMENTWY NOTES ABSTRACTThis report describes a computational study undertaken to consider the aerodynamic effect of synthetic jets as a means to provide the control authority needed to maneuver a projectile at low subsonic speeds. The time-accurate Navier-Stokes computational technique has been used to obtain numerical solutions for the unsteady jet interaction flow field for a projectile at a subsonic speed, Mach = 0.11, and several angles of attack from 0° to 4°. Qualitative flow field features show the interaction of the timedependent jet with the free stream flow. Numerical results show the effect of the Jet on the flow field, surface pressures and aerodynamic coefficients. Unsteady numerical results have been obtained for a two-dimensional jet flow and compared with experimental data for validation. The same unsteady jet modeling technique h^ been applied to a subsonic projectile. These numerical results are being assessed to determine if synthetic jets can be used to provide the control authority needed for maneuvering munitions to hit the targets with precision.

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“…To help reduce experimental costs, computational fluid dynamics (CFD) is being used to predict these complex flows and provide detailed pressure, and force and moment data. There have been several recent numerical studies (He andKral 2000, Lee andGoldstein 2000) of flow separation control using synthetic jet actuators. He and Kral (2000) have used Reynolds-Averaged Navier -Stokes (RANS) to study the effect of jet location and jet forcing frequency on the lift and drag forces on an airfoil.…”

Section: Introductionmentioning

confidence: 99%

Unsteady CFD modeling of micro-adaptive flow control for an axisymmetric body

Sahu

Heavey

2006

International Journal of Computational Fluid Dynamics

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This paper describes a computational study undertaken, as part of a grand challenge project, to consider the aerodynamic effect of micro-adaptive flow control as a means to provide the divert authority needed to maneuver a projectile at a low subsonic speed. A time-accurate Navier -Stokes computational technique has been used to obtain numerical solutions for the unsteady micro-jet-interaction flow field for the axisymmetric projectile body at subsonic speeds, Mach ¼ 0.11 and 0.24 and angles of attack, 0-48. Numerical solutions have been obtained using both Reynolds-Averaged Navier -Stokes (RANS) and a hybrid RANS/Large Eddy Simulation (LES) turbulence models. Unsteady numerical results show the effect of the jet on the flow field and the aerodynamic coefficients, in particular the lift force. This research has provided an increased fundamental understanding of the complex, three-dimensional (3D), time-dependent, aerodynamic interactions associated with micro-jet control for yawing spin-stabilized munitions.

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Post-stall flow control on an airfoil using localized jet actuators

Cited by 6 publications

References 7 publications

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

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

Unsteady Numerical Simulations of Subsonic Flow over a Projectile with Jet Interaction

Unsteady CFD modeling of micro-adaptive flow control for an axisymmetric body

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