Part 1: The Wind Tunnel Model Design and Fabrication of Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft

Jameson, Kristina K.; Marshall, P. David; Golden, Rory; Paciano, Eric N.; Englar, Robert J.; Gaeta, Richard; Paterson, Jay; Mason, Dave

doi:10.2514/6.2011-1306

Cited by 12 publications

(11 citation statements)

References 5 publications

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“…The conceptual designs considered for this project and the decision process that lead to the selected configuration adapted for the AMELIA wind tunnel model are discussed in Ref. 3. The external experimental techniques that were employed during the test, along with the large-scale wind tunnel test facility are covered in great detail.…”

Section: Introductionmentioning

confidence: 99%

Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft Wing Tunnel Test and Experimental Results Overview

Jameson

Marshall

Ehrmann

et al. 2013

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

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A collaboration between California Polytechnic Corporation with GeorgiaTech Research Institute (GTRI) and DHC Engineering worked on a NASA NRA to develop predictive capabilities for the design and performance of Cruise Efficient, Short Take-Off and Landing (CESTOL) subsonic aircraft. The work presented in this paper gives details of a large scale wind tunnel effort to validate predictive capabilities for this NRA for aerodynamic and acoustic performance during takeoff and landing. The model, Advanced Model for Extreme Lift and Improved Aeroacoustics (AMELIA), was designed as a 100 passenger, N+2 generation, regional, cruise efficient short takeoff and land (CESTOL) airliner with hybrid blended wing-body with circulation control. AMELIA is a 1/11 scale with a corresponding 10 ft wing span. The National Full-Scale Aerodynamic Complex (NFAC) 40 ft by 80 ft wind tunnel was chosen to perform the large-scale wind tunnel test. The NFAC was chosen because both aerodynamic and acoustic measurements will be obtained simultaneously, the tunnel is large enough that the 2 downwash created by the powered lift did not impinge on the tunnel walls, and the schedule and cost fit into Cal Poly's time frame and budget. Several experimental measurement techniques were used to obtain the necessary data to validate predictive codes being developed as apart of this effort: along with the traditional forces and moments measurements, stationary microphones were used to obtain far-field acoustic measurements including a 48 element phased array, the Fringe-Image Skin Friction (FISF) technique was used to measure the global skin friction on the wing, surface mounted steady and unsteady pressure transducers were used to obtain local pressure distributions over the model, and oil and smoke flow visualization techniques were employed to understand the effects of the powered lift system in AMELIA. The paper gives a brief summary of AMELIA's performance for variable tunnel speed, momentum mass flow, engine simulator height, and angle of attack.

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Section: Introductionmentioning

confidence: 99%

Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft Wing Tunnel Test and Experimental Results Overview

Jameson

Marshall

Ehrmann

et al. 2013

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

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“…The AMELIA CESTOL model an d test program were described by Jameson et a l 3 Development of th e propul sion confi gurati on and CC W des ign was described by Gaeta et a1 4 . F igure 1 shows a cut-away drawing of tb e 10 ft (3 .048 m) span model and blade support adaptor.…”

Section: Description Of Th E Wind Tunnel Modelmentioning

confidence: 99%

AMELIA CESTOL Test: Acoustic Characteristics of Circulation Control Wing with Leading- and Trailing-Edge Slot Blowing

Horne

Burnside

2013

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

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Aeroacoustic measurements of the 11 % scale full-span AMELIA CESTOL model with leading-and trailing-edge slot blowing circulation control (CCW) wing were obtained during a recent test in the Arnold Engineering Development Centel' 40-by SO-Ft. Wind Tunnel at NASA Ames Research Center, Sound levels and spectra were acquired with seven in-flow microphones and a 4S-element phased microphone array for a variety of vehicle configurations, CCW slot flow rates, and forward speeds, COITections to the meaSUI'emel1ts and processin g al'e in progress, however the data from selected configurations presented in this report conlil'm good measurement quality al1d dynamic range over the test conditions, Array beamform maps at 40 kts tunnel speed show that the trailing edge flap so urce is dominant for most frequencies at flap angles of O· and 60°, The overall sound level for the 60° flap was similar to tbe 0° flap for most slot blowing rates forward of 90° incidence, but was louder by up to 6 dB fOI' downstream angles, At 100 kts, the in-flow microphone levels were louder than the sensor self-noise fOI' the highel' blowing rates, while passive and active background noise suppression methods for the microphone array revealed source levels as much as 20 dB lowel' than observed with the in-flow microphones, NomenclatureLift coeffic ient, L / (q*S) CCW slow momentum coefficient, (m*V j ) / (q*S) Circul ati on contro l wing Cross-spectra l matrix Lift, Ib r Slot mass fl ow rate, Ibm / s Overa ll sound pressure level, dB re 20,6 Pa Freestream dynamic pressure, Ib r / ft2 Radi a l di stance fi'o m model aco ustic center to sensor, inches Wing planfo rm reference area, ft 2 CCW s lot j et veloc ity, ft / s E mi ssion ang le relati ve to model aco ustic center, 0 = 0° for upstream emission

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“…As research transitioned from Phase 1 to Phase (Table 1.3). For further discussion of the wind tunnel model design decisions the reader is referred to Reference [8]. (near slots and plenums) and aluminum was used for many of the larger body panels.…”

Section: The Amelia Configurationmentioning

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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Part 1: The Wind Tunnel Model Design and Fabrication of Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft

Cited by 12 publications

References 5 publications

Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft Wing Tunnel Test and Experimental Results Overview

Cal Poly's AMELIA 10 Foot Span Hybrid Wing-Body Low Noise CESTOL Aircraft Wing Tunnel Test and Experimental Results Overview

AMELIA CESTOL Test: Acoustic Characteristics of Circulation Control Wing with Leading- and Trailing-Edge Slot Blowing

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

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