Overview of Recent Circulation Control Modeling Activities at Cal Poly

Marshall, P. David; Jameson, Kristina K.

doi:10.2514/6.2010-348

Cited by 12 publications

(7 citation statements)

References 39 publications

(33 reference statements)

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“…= Reynolds number t, 0 = stagnation property R 2 = coefficient of determination ∞ = freestream property Acronyms AMELIA = advanced model for extreme lift and improved aeroacoustics CCW = circulation control wing CESTOL = cruise efficient, short take-off and landing CNPR = core nozzle pressure ratio, (P 0 ) core /P ∞ FISF = fringe imaging skin friction FNPR = fan nozzle pressure ratio, (P 0 ) fan /P ∞ HPA = high pressure air LE = leading edge LEIB = leading edge inboard plenum LEOB = leading edge outboard plenum NFAC = National Full-Scale Aerodynamics Complex NPR = nozzle pressure ratio, (P 0 ) plenum /P ∞ STOL = short take-off and landing TE = trailing edge TEIB = trailing edge inboard plenum TEOB = trailing edge outboard plenum TPS = turbine propulsion simulator…”

Section: Nomenclaturementioning

confidence: 99%

STOL Performance of Cal Poly's AMELIA

Lichtwardt

Paciano

Marshall

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Results from Cal Poly's recent wind tunnel test in the 40-by 80-foot test section at the National Full-Scale Aerodynamics Complex (NFAC) at NASA Ames Research Center are presented. AMELIA, the Advanced Model for Extreme Lift and Improved Aeroacoustics, is the first full-span cruise efficient short takeoff and landing (CESTOL) model incorporating leading-and trailing-edge blowing wing circulation control and over-the-wing mounted turbine propulsion simulators (TPS) to date. Testing of the 10 foot span model proved successful and was the result of a 5-year NASA Fundamental Aeronautics Program Research Announcement. All of the results associated with Cal Poly's effort will be available in an open-source validation database with the goal of advancing the state-of-the-art in prediction capabilities for modeling aircraft with next generation technologies, focusing on NASA's N+2 generation goals. The model's modular design allowed for testing of 4 major configurations. Results from all configurations are presented. Test data shows drastic improvements in performance are obtained when incorporating leading edge blowing. Wing stall can be delayed to more than 25° angle of attack at lift coefficients exceeding six. Without the introduction of leading edge blowing to increase boundary layer momentum and maintain flow attachment around the leading edge, STOL performance suffers. Similar runs for trailing edge-only blowing show a reduction in maximum lift coefficient to three with stall occurring at zero angle of attack. Testing at multiple engine pylon heights allowed for the highly coupled propulsion and flow control system to be characterized.

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Section: Nomenclaturementioning

confidence: 99%

STOL Performance of Cal Poly's AMELIA

Lichtwardt

Paciano

Marshall

et al. 2013

51st AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Additionally, flow visualization images are presented for comparison with CFD results. As a whole, this thesis should be considered a supplement to the many documents that detail the AMELIA wind tunnel test and Cal Poly, GTRI, and NASA's effort to develop a next-generation, regional, CESTOL airliner that abides by the N+2 metrics(see References [33,11,34]).…”

Section: Chapter 6 Conclusionmentioning

confidence: 99%

Qualitative Methods Used to Develop and Characterize the Circulation Control System on Cal Poly's AMELIA

Paciano¹

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The circulation control system onboard Cal Poly's Advanced Model for Extreme Lift and Improved Aeroacoustics was a critical component of a highly complex wind tunnel model produced in order to fulfill the requirements of a NASA Research Announcement awarded to David Marshall of the Aerospace Engineering Department. The model was based on a next generation, 150 passenger, regional, cruise efficient, short takeoff and landing concept aircraft that achieved high lift through circulation control wings and over-the-wing mounted engines. The wind tunnel model was 10-ft in span, used turbine propulsion simulators, and had a functioning circulation control system driven from tunnel supplied high pressure air. Wind tunnel test results will be compiled into an open-source database intended for validation of predictive tools whose purpose is to advance the stateof-the-art in predictive capabilities for the next generation aircraft configurations. The model's circulation control system produced highly directional, nonuniform flow, and required significant modification in order to generate flow suitable for representation in predictive software. The effort and methods used to generate uniform flow along the circulation control slots is detailed herein. Additionally the results of the system characterization are presented and include a thorough analysis of the slot height, the wing symmetry, and total pressure at the circulation control jet exit. These datasets are intended to aid in making adjustments to the simulation such that it accurately reflects the condition at which the model was tested. Many flow visualization results from the wind tunnel test are also presented to serve as a medium of comparison for results from predictive tools. Oil flow visualization was conducted at many test conditions and provides insight to AMELIA's surface flow in blown and unblown regions. Of particular interest were streamlines at the wingblend, which exhibited some outboard turning, and streamlines iv on the lower surface where the leading edge stagnation point was investigated. Smoke flow visualization was also utilized to explore the flowfield. The deflection of a individual streamline, under the influence of a changing discharge coefficient was investigated along with the discharge coefficients effect on the extended flowfield. Collectively, the images depict the massive augmentation of the flowfield caused by the presence of the circulation control wing. v ACKNOWLEDGMENTS This research effort was sponsored by NASA's Subsonic Fixed Wing Program, NASA Research Announcement contract #NNL07AA55C. Thank you to Craig Hange and Clif Horne for serving as technical monitors on this project. Mike Rogers and Bob Lockyer also deserve a special thanks for their enthusiastic support throughout the project. Dr. Marshall, this has been one of the most fulfilling experiences of my life and I have you to thank for that. I greatly appreciate all of the opportunities you've provided me. Thank You. Dr. Jameson, I have learned a lot from you, especially whe...

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“…The project focuses on the design and wind tunnel test of a low-noise, cruise efficient, short take-off and landing (CESTOL) airliner that will improve prediction methods and technologies that can enable lower noise, emissions, and fuel burn [2]. The literature is well documented with publicly available research efforts focused on circulation control testing intended for CFD validation [4,5,6,7,8,9].…”

Section: T Eob Trailing Edge Outboardmentioning

confidence: 99%

An Experimental Investigation of the STOL Performance of Cal Poly's AMELIA in the NFAC

Lichtwardt¹

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Overview of Recent Circulation Control Modeling Activities at Cal Poly

Cited by 12 publications

References 39 publications

STOL Performance of Cal Poly's AMELIA

STOL Performance of Cal Poly's AMELIA

Qualitative Methods Used to Develop and Characterize the Circulation Control System on Cal Poly's AMELIA

An Experimental Investigation of the STOL Performance of Cal Poly's AMELIA in the NFAC

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