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Investigating the Impact of Coupled High-Lift Devices on Natural Laminar Flow Airfoils
Investigating the Impact of Coupled High-Lift Devices on Natural Laminar Flow Airfoils
상세정보
- 자료유형
- 학위논문 서양
- 최종처리일시
- 20260209102930
- ISBN
- 9798314843376
- DDC
- 629.1
- 서명/저자
- Investigating the Impact of Coupled High-Lift Devices on Natural Laminar Flow Airfoils
- 발행사항
- [Sl] : University of Illinois at Urbana-Champaign, 2023
- 발행사항
- Ann Arbor : ProQuest Dissertations & Theses, 2023
- 형태사항
- 219 p
- 주기사항
- Source: Dissertations Abstracts International, Volume: 86-11, Section: B.
- 주기사항
- Advisor: Ansell, Phillip J.
- 학위논문주기
- Thesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2023.
- 초록/해제
- 요약A set of experiments were conducted on the S207 airfoil at the University of Illinois at Urbana-Champaign in order to study the influence of coupled high-lift devices on the performance of a natural laminar flow airfoil in high-lift conditions, such as takeoff and landing. Both computational and experimental analyses were used to characterize the influence of three different high-lift devices, morphed leading edges, aft element deflection, and active flow control through embedded fluidic oscillators. A genetic algorithm was developed to design a set of blunted and drooped leading edge geometries, using MSES to evaluate the performance of the morphed geometries. Additionally, OVERFLOW was used to perform a sensitivity analysis on the placement and frequency of the fluidic oscillators embedded into the slotted natural laminar flow airfoil. A series of four wind tunnel experiments were used to validate the computational results and further investigate the influence of the coupled high-lift devices on the on- and off-body flow field. Testing of the model was performed at Re=1.2x106 and Re=1.4x106. Surface pressure force data was collected across four sets of experiments. The first three experiments individually focused on analyzing the three different high-lift devices, morphed leading edges, aft element deflection, and active flow control, at Re=1.4x106. The fourth experiment focused on evaluating the performance of select configurations at Re=1.2x106. Results from these experiments were used to select configurations of interest to further investigate with stereo-PIV and oil flow visualization. Stereo-PIV data were collected at Re=1.4x106 and focused on four configurations near stall to investigate the influence of the coupled high-lift devices on the off-body flow structures forming over the upper surface of the aft element. Oil flow visualization was run at Re=1.2x106 and images were taken for four configurations pre- and post-stall to further characterize the influence of the three coupled high-lift devices.Morphed leading edges were identified as a viable alternative to more common leading edge devices, such as a Krueger flap or leading edge slat. The genetic algorithm was able to generate multiple viable morphed geometries and the performance of the geometries were experimentally validated. Each morphed geometry led to an increase of ΔCl,max=0.5−0.7 compared to the baseline geometry. Drooping the leading edge was found to have a larger influence on the lift of the airfoil, while blunting the leading edge was found to have a larger influence on the boundary layer health. The combination of blunting and drooping the leading edge led to a morphed geometry that both improved the performance of the airfoil and generated a more favorable pressure gradient along the leading edge compared to the standard geometry. This changed the stall behavior of the slotted natural laminar flow airfoil from a leading edge stall to a trailing edge stall.Aft element deflection further increased the performance of the S207 airfoil, leading to Cl,max 3 when coupled with morphed leading edge geometries. Lift increased as the aft element was deflected to 15°, but diminishing returns were observed at higher deflections. As the aft element was deflected, regions of separation were observed to form on the upper surface of the aft element.Active flow control elements were embedded into the aft element and the internal geometry of the fluidic oscillators were sized to produce a frequency that targets shear layer instabilities in the flow. Oscillatory actuation was observed to reduce separation on the aft element, reduce the size of the airfoil wake, and slightly increase the lift of the airfoil. In the ranges tested, up to Cμ=1.0, no diminishing effectiveness of active flow control from the fluidic oscillators was observed. Embedded fluidic oscillators were found to produce a similar improvement in performance as that of a simple flap on the aft element.
- 일반주제명
- Aerospace engineering
- 일반주제명
- Physics
- 일반주제명
- Energy
- 일반주제명
- Fluid mechanics
- 기타저자
- University of Illinois at Urbana-Champaign Aerospace Engineering
- 기본자료저록
- Dissertations Abstracts International. 86-11B.
- 전자적 위치 및 접속
- 로그인 후 원문을 볼 수 있습니다.
MARC
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■0820 ▼a629.1
■1001 ▼aColletti, Christopher R.
■24510▼aInvestigating the Impact of Coupled High-Lift Devices on Natural Laminar Flow Airfoils
■260 ▼a[Sl]▼bUniversity of Illinois at Urbana-Champaign▼c2023
■260 1▼aAnn Arbor▼bProQuest Dissertations & Theses▼c2023
■300 ▼a219 p
■500 ▼aSource: Dissertations Abstracts International, Volume: 86-11, Section: B.
■500 ▼aAdvisor: Ansell, Phillip J.
■5021 ▼aThesis (Ph.D.)--University of Illinois at Urbana-Champaign, 2023.
■520 ▼aA set of experiments were conducted on the S207 airfoil at the University of Illinois at Urbana-Champaign in order to study the influence of coupled high-lift devices on the performance of a natural laminar flow airfoil in high-lift conditions, such as takeoff and landing. Both computational and experimental analyses were used to characterize the influence of three different high-lift devices, morphed leading edges, aft element deflection, and active flow control through embedded fluidic oscillators. A genetic algorithm was developed to design a set of blunted and drooped leading edge geometries, using MSES to evaluate the performance of the morphed geometries. Additionally, OVERFLOW was used to perform a sensitivity analysis on the placement and frequency of the fluidic oscillators embedded into the slotted natural laminar flow airfoil. A series of four wind tunnel experiments were used to validate the computational results and further investigate the influence of the coupled high-lift devices on the on- and off-body flow field. Testing of the model was performed at Re=1.2x106 and Re=1.4x106. Surface pressure force data was collected across four sets of experiments. The first three experiments individually focused on analyzing the three different high-lift devices, morphed leading edges, aft element deflection, and active flow control, at Re=1.4x106. The fourth experiment focused on evaluating the performance of select configurations at Re=1.2x106. Results from these experiments were used to select configurations of interest to further investigate with stereo-PIV and oil flow visualization. Stereo-PIV data were collected at Re=1.4x106 and focused on four configurations near stall to investigate the influence of the coupled high-lift devices on the off-body flow structures forming over the upper surface of the aft element. Oil flow visualization was run at Re=1.2x106 and images were taken for four configurations pre- and post-stall to further characterize the influence of the three coupled high-lift devices.Morphed leading edges were identified as a viable alternative to more common leading edge devices, such as a Krueger flap or leading edge slat. The genetic algorithm was able to generate multiple viable morphed geometries and the performance of the geometries were experimentally validated. Each morphed geometry led to an increase of ΔCl,max=0.5−0.7 compared to the baseline geometry. Drooping the leading edge was found to have a larger influence on the lift of the airfoil, while blunting the leading edge was found to have a larger influence on the boundary layer health. The combination of blunting and drooping the leading edge led to a morphed geometry that both improved the performance of the airfoil and generated a more favorable pressure gradient along the leading edge compared to the standard geometry. This changed the stall behavior of the slotted natural laminar flow airfoil from a leading edge stall to a trailing edge stall.Aft element deflection further increased the performance of the S207 airfoil, leading to Cl,max 3 when coupled with morphed leading edge geometries. Lift increased as the aft element was deflected to 15°, but diminishing returns were observed at higher deflections. As the aft element was deflected, regions of separation were observed to form on the upper surface of the aft element.Active flow control elements were embedded into the aft element and the internal geometry of the fluidic oscillators were sized to produce a frequency that targets shear layer instabilities in the flow. Oscillatory actuation was observed to reduce separation on the aft element, reduce the size of the airfoil wake, and slightly increase the lift of the airfoil. In the ranges tested, up to Cμ=1.0, no diminishing effectiveness of active flow control from the fluidic oscillators was observed. Embedded fluidic oscillators were found to produce a similar improvement in performance as that of a simple flap on the aft element.
■590 ▼aSchool code: 0090.
■650 4▼aAerospace engineering
■650 4▼aPhysics
■650 4▼aEnergy
■650 4▼aFluid mechanics
■653 ▼aHigh-lift devices
■653 ▼aNatural laminar flow
■653 ▼aActive flow control
■653 ▼aFluidic oscillators
■653 ▼aMorphed leading edges
■653 ▼aGenetic algorithm
■690 ▼a0538
■690 ▼a0204
■690 ▼a0605
■690 ▼a0791
■71020▼aUniversity of Illinois at Urbana-Champaign▼bAerospace Engineering.
■7730 ▼tDissertations Abstracts International▼g86-11B.
■790 ▼a0090
■791 ▼aPh.D.
■792 ▼a2023
■793 ▼aEnglish
■85640▼uhttp://www.riss.kr/pdu/ddodLink.do?id=T17366032▼nKERIS▼z이 자료의 원문은 한국교육학술정보원에서 제공합니다.
