Using Computational Fluid Dynamics and Experiments to Design Sweeping Jets for High Reynolds Number Cruise Configurations

Jones, Gregory S.; Milholen, William E.; Fell, Jared S.; Webb, Sandy; Cagle, Christopher M.

doi:10.2514/6.2016-3311

Cited by 8 publications

(2 citation statements)

References 23 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Likewise, the sweeping jet velocity is not uniformly distributed at the exit 20 due to the diamond splitter as shown from hot-wire measurements in Figure 23. While the peak velocities of the sweeping jet actuators are comparable to the steady jet actuators the overall authority or average velocity of the sweeping jet actuators on the flap is approximately 50% of the steady jet actuators.…”

Section: Actuators In Quiescent Flowmentioning

confidence: 97%

A Discrete and Distributed Steady Blowing Application on a High Reynolds Number Semispan Supercritical Wing Configuration

Jones

Milholen

Chan

et al. 2018

2018 AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

The FAST-MAC circulation control model was modified to test an array of steady and unsteady actuators at realistic flight Reynolds numbers in the National Transonic Facility at the NASA Langley Research Center. Previous experiments in the FAST-MAC test series used a fullspan tapered slot, and that configuration is used as a baseline for performance and weight flow requirements. The goal of the latest experiment was to reduce the weight flow required to achieve comparable performance established by the baseline FAST-MAC data. Thirty-nine interchangeable actuator cartridges of various designs were mounted into the FAST-MAC model where the exiting jet was directed over a 15% chord simple hingedflap. These two types of actuators were fabricated using rapid prototype techniques and their design performance was optimized for a transonic cruise configuration having a 0° flap deflection. The steady actuators were found to provide an off-design drag reduction of 5.5%, nearly equaling the drag reduction of the fullspan tapered slot configuration, but with a 69% weight flow reduction. This weight flow savings is similar to the sweeping jet actuators, but with better drag performance.

show abstract

Section: Actuators In Quiescent Flowmentioning

confidence: 97%

A Discrete and Distributed Steady Blowing Application on a High Reynolds Number Semispan Supercritical Wing Configuration

Jones

Milholen

Chan

et al. 2018

2018 AIAA Aerospace Sciences Meeting

Self Cite

View full text Add to dashboard Cite

show abstract

“…This motivates the current study of sweeping jets operating at cruise Mach numbers greater than 0.8 (i.e., in the compressible regime). 9 Direct quantitative measurements of supersonic (highly compressible) sweeping jets are limited, and no internal velocity measurements of a supersonic sweeping jet have been reported. 1 Such measurements are particularly difficult in this internal flow because probes would block the flow and optical methods like particle image velocimetry (PIV) and Rayleigh scattering suffer from interference from laser light scattering off of windows and surfaces or seed particles adhering to surfaces (for PIV).…”

Section: Introductionmentioning

confidence: 99%

Femtosecond Laser Tagging Characterization of a Sweeping Jet Actuator Operating in the Compressible Regime

Peters

Miles

Burns

et al. 2016

32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference

Self Cite

View full text Add to dashboard Cite

A sweeping jet (SWJ) actuator operating over a range of nozzle pressure ratios (NPRs) was characterized with femtosecond laser electronic excitation tagging (FLEET), single hotwire anemometry (HWA) and high-speed/phase-averaged schlieren. FLEET velocimetry was successfully demonstrated in a highly unsteady, oscillatory flow containing subsonic through supersonic velocities. Qualitative comparisons between FLEET and HWA (which measured mass flux since the flow was compressible) showed relatively good agreement in the external flow profiles. The spreading rate was found to vary from 0.5 to 1.2 depending on the pressure ratio. The precision of FLEET velocity measurements in the external flow field was poorer (≈25 m/s) than reported in a previous study due to the use of relatively low laser fluences, impacting the velocity fluctuation measurements. FLEET enabled velocity measurements inside the device and showed that choking likely occurred for NPR ≥ 2.0, and no internal shockwaves were present. Qualitative oxygen concentration measurements using FLEET were explored in an effort to gauge the jet's mixing with the ambient. The jet was shown to mix well within roughly four throat diameters and mix fully within roughly eight throat diameters. Schlieren provided visualization of the internal and external flow fields and showed that the qualitative structure of the internal flow does not vary with pressure ratio and the sweeping mechanism observed for incompressible NPRs also probably holds for compressible NPRs.

show abstract

Numerical investigation on flow mechanism in a supersonic fluidic oscillator

Sang

Shan

Zhang

et al. 2021

Chinese Journal of Aeronautics

View full text Add to dashboard Cite

Using Computational Fluid Dynamics and Experiments to Design Sweeping Jets for High Reynolds Number Cruise Configurations

Cited by 8 publications

References 23 publications

A Discrete and Distributed Steady Blowing Application on a High Reynolds Number Semispan Supercritical Wing Configuration

A Discrete and Distributed Steady Blowing Application on a High Reynolds Number Semispan Supercritical Wing Configuration

Femtosecond Laser Tagging Characterization of a Sweeping Jet Actuator Operating in the Compressible Regime

Numerical investigation on flow mechanism in a supersonic fluidic oscillator

Contact Info

Product

Resources

About