Numerical Spoiler Wake Investigations at the Borders of the Flight Envelope

Geisbauer, Sven

doi:10.2514/6.2011-3811

Cited by 5 publications

(4 citation statements)

References 25 publications

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“…It is therefore important to note that robustness or usability of steady methods no longer seem to impede their application within the entire flight envelope. 5 On the other hand, it is also clear that despite the growing role of CFD in the industrial design process there is still a lack of confidence when it comes to flight conditions with significantly separated flows. 6 As a consequence, the impact of turbulence modeling and the discretization approach is still subject to ongoing research, requiring validation data.…”

Section: Introductionmentioning

confidence: 99%

Towards the Investigation of Unsteady Spoiler Aerodynamics

Geisbauer

Löser

2017

35th AIAA Applied Aerodynamics Conference

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Aircraft configurations with deployed control surfaces are increasingly in the limelight of aerodynamic investigations using high-fidelity based Computational Fluid Dynamics to possibly reduce the conservatism in the design process. So far, most applications focus on static control surface deflections. To close the gap towards future simulations of entire flight maneuvers, including gust encounters, the dynamic motion of the control surfaces and their transient impact on the aircraft configuration need to be taken into account. Hence, extending the application range of its flow solver TAU is of strategic interest for the Institute of Aerodynamics and Flow Technology of the German Aerospace Center (DLR). To support these numerical activities DLR developed a wind tunnel model with an active spoiler. In collaboration with German-Dutch Wind Tunnels, the aerodynamic performance of this model has been examined in two wind tunnel campaigns in 2016, focusing on static and dynamic spoiler deflections. The present paper gives an overview on the motivation of this work and highlights the experimental setup as well as exemplary results. The data will later be used to further validate the DLR flow solver TAU.

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Section: Introductionmentioning

confidence: 99%

Towards the Investigation of Unsteady Spoiler Aerodynamics

Geisbauer

Löser

2017

35th AIAA Applied Aerodynamics Conference

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“…Thus, it is specifically suited for detached or vortical flows. Its implementation in TAU revealed promising results for transport aircraft configurations as presented in several DLR publications [32][33][34] . Besides the SARC, it was therefore applied as well to compare the influence and the potential advantages of the two more advanced models over the standard SA and SST models.…”

Section: Iiib the Dlr Tau Codementioning

confidence: 85%

Validation of the Flow Topology Around Several Airdrop Cargo Configurations at Static Conditions

Geisbauer

Bier

Kirz

et al. 2013

31st AIAA Applied Aerodynamics Conference

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A numerical study was carried out to assess the interference effects between the wake of a transport aircraft and several generic cargo bodies during the early stage of an airdrop scenario. DLR carried out extensive wind tunnel airdrop investigations between 2006 and 2012. Based on the experimental data and preceding numerical simulations distinct positions of the trajectory being subject to strong interference effects were statically reproduced. The flow field around the bodies was experimentally investigated using stereoscopic Particle Image Velocimetry and compared to steady and unsteady Reynoldsaveraged Navier-Stokes (RANS) computations. The latter were carried out using the unstructured DLR TAU code. The primary focus is to assess the suitability, accuracy and the limitations of RANS methods in such challenging flow conditions. Therefore, the influence of several turbulence models was investigated and compared to experimental field velocity data. In addition, an exemplary unsteady RANS simulation was conducted to highlight the differences to the steady approach. Although deviations in the wake of the bodies were observed, the qualitative agreement between the steady simulations and experiment was very good. Quantitatively, however, the steady approach leaves room for further improvements. The gap to the experimental data could partially be reduced in applying unsteady RANS methods.

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“…From this study, it was found that as the spoiler is deflected, the change in lift between the airfoil with the spoiler compared to that without a spoiler increases, highlighting the spoiler's effectiveness. There have also been numerous computational and experimental studies [9][10][11][12][13][14][15][16][17][18][19] investigating the effect of spoiler position, spoiler deflection angle, and spoiler chord on the aerodynamic characteristics of different airfoil geometries. Mashud et al [9] investigated a NACA2415 airfoil equipped with spoilers located at 0.5C, 0.6C, 0.7C, 0.8C, and 0.9C to determine the spoiler's effectiveness.…”

Section: Introductionmentioning

confidence: 99%

“…Lee et al [10] investigated experimentally the flow field of an airfoil with the deflected spoiler at low speed and found that the base pressure behind the spoiler changes rapidly with the angle of attack, and the location of the hinge bubble depends on the boundary layer characteristics, angle of attack, and spoiler deflections. Furthermore, Kalkanis [11], Geisbauer [12], and Alhawwary et al [13] analyzed numerically (using a discrete vortex method, an in-house steady RANS solver, and a higher-order spectral difference method, respectively) the flow-fields around an airfoil with a deflected spoiler, in which the pressure distribution, spoiler wake, and vortex-shedding behavior were investigated. They found that the typical vortex shedding behavior of a spoiler was similar to that of bluff body shedding.…”

Section: Introductionmentioning

confidence: 99%

A Novel Reverse Hinge Spoiler for Flight Loads Control

Ajaj

Djidjeli

2022

Designs

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This paper presents the reverse hinge spoiler, a novel spoiler concept, for flight load control. The reverse hinge spoiler is a control surface mounted on the upper surface of the wing. Unlike conventional hinged spoilers that are hinged at their front and rotate forward toward the leading edge of the wing, the proposed spoiler concept is hinged at its rear and rotates backward toward the trailing edge of the wing. The aerodynamic performance of the proposed spoiler is compared and contrasted with that of a conventional hinged spoiler for different flight conditions and hinge locations using the two-dimensional Reynolds-Averaged Navier–Stokes (RANS) with the k-omega SST turbulence model-based computational fluid dynamic solver. The results show that the proposed spoiler results in a larger increase in drag and a sharper reduction in the lift for a wide range of spoiler angles and flight conditions. Reversing the spoiler is found to cause a higher adverse pressure gradient in front of the spoiler compared to a conventional spoiler, as it ‘traps’ more flow, thereby increasing drag and reducing lift.

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Numerical Spoiler Wake Investigations at the Borders of the Flight Envelope

Cited by 5 publications

References 25 publications

Towards the Investigation of Unsteady Spoiler Aerodynamics

Towards the Investigation of Unsteady Spoiler Aerodynamics

Validation of the Flow Topology Around Several Airdrop Cargo Configurations at Static Conditions

A Novel Reverse Hinge Spoiler for Flight Loads Control

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