DLR TAU Simulations for the Second AIAA Sonic Boom Prediction Workshop

Kirz, Jochen; Rudnik, Ralf

doi:10.2514/6.2017-3253

Cited by 7 publications

(3 citation statements)

References 15 publications

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“…The flow is considered two-dimensional so that the complexity of threedimensional phenomena is neglected. Furthermore, the flow is regarded inviscid, since the Reynolds number excides 10 6 for the selected freestream Mach number range (Mach 4 to 7) [10,11]. Those simplifications are deemed sufficient to capture the main aspects of the flow, i.e.…”

Section: Cfd Methodology and Validationmentioning

confidence: 99%

A novel technique for hypersonic vehicle control

et al. 2019

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A novel control technique is investigated for hypersonic aerial vehicles. The technique is based on the use of active shock bumps (SBs) as a form of control device. The SBs deflect to create shockwaves on–demand, at specific locations around the aerial vehicle. As a result, a force is applied on the aerial vehicle, which in turn is used to provide the necessary moment for pitch and roll manoeuvres. In this work, a preliminary aerodynamic analysis of the SB device technique is made by means of CFD. For this purpose, and taking the large corresponding Reynolds numbers of the flow into consideration, the two–dimensional Euler equations are solved. A parametric investigation is carried out, by examining the effect of key parameters, namely the Mach number (M) and device deflection angle (δSB) on the produced force acting on the vehicle, serving as a proof of concept. Using a specific interpolation method, the resultant force is presented as a function of the Mach number and the device deflection angle, on three–dimensional charts, where the effect of each parameter is shown (force–Mach–deflection maps). Furthermore, a preliminary feasibility study is performed, including a kinematic analysis and some key material considerations. Additionally, a kinetic analysis is also conducted to secure the dynamic rigidity of the actuating mechanism and provide an initial estimation concerning weight and basic geometrical parameters of the SB mechanism components.

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Section: Cfd Methodology and Validationmentioning

confidence: 99%

A novel technique for hypersonic vehicle control

et al. 2019

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“…The research in low boom supersonic designs is today augmented by Multidisciplinary Design Analysis and Optimization (MDAO) techniques, improved sound prediction and propagation methods, as well as high fidelity CFD modeling [5]. Despite the use of these advanced techniques, the implementation of quick low fidelity design tools, which employ analytical and semi-empirical methods, can be used to evaluate potential designs with significantly reduced computational costs.…”

Section: Introductionmentioning

confidence: 99%

Parametric investigation of the aerodynamic and acoustic performance of a low-boom supersonic airliner

Bliamis

Papadopoulos

Yakinthos

2023

J. Phys.: Conf. Ser.

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In the present work, a parametric design study in the conceptual design phase of a low-boom supersonic airliner (LBSSA) is presented. The low-boom constraint is of great importance to the near future supersonic airliners, in order for them to be certified for overland operation, but is also usually associated with a penalty in their aerodynamic performance (e.g. increased drag) and subsequently a higher fuel consumption. In this work, a dedicated low-fidelity design tool for the conceptual and early preliminary design of a LBSSA is developed which includes both Class-I and Class-II weight calculations. The design tool is also capable of predicting the aircraft’s aerodynamic performance in both the subsonic and supersonic cruise segments of its mission. The aerodynamic behavior of the LBSSA is then compared against the results obtained from high fidelity Computational Fluid Dynamics (CFD) modeling. Regarding the acoustic behavior of the LBSSA, Carlson’s simplified method is employed, which is based on the equivalent area distribution of the aircraft, in order to provide representative trends and results in the conceptual design phase. Finally, the contribution of the examined design parameters, in the aerodynamic and acoustic performance of the resultant LBSSA is presented and clear trends are indicated.

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“…This paper presents results submitted to SBPW2 for all four nearfield cases. (Results from other participants are published in [4][5][6] and high-level summaries are published in [3,7].) The vehicles for the nearfield portion are shown in Fig.…”

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confidence: 99%

Cart3D Simulations for the Second AIAA Sonic Boom Prediction Workshop

Anderson

Aftosmis

Nemec

2019

Journal of Aircraft

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Simulation results are presented for all test cases prescribed in the Second AIAA Sonic Boom Prediction Workshop. An inviscid, embedded-boundary Cartesian-mesh flow solver is used to compute "boom carpets"-pressure signatures at a range of specified distances and off-track angles. To accelerate the process, each boom carpet is automatically decomposed into several independent meshes, computed in parallel. Each mesh uses output-based mesh adaptation to affordably obtain credible results. This paper discusses improved Cartesian meshing strategies for boom prediction, including Mach alignment, azimuthal alignment, high-aspect-ratio cells, and adaptation functional weighting. The resulting nearfield signatures generally exhibit good convergence with mesh refinement. For an independent evaluation of our results, this study introduces a local error estimation procedure that highlights regions of the signatures most sensitive to mesh refinement. Results are also presented for the two atmospheric propagation test cases, which investigate the effects of atmospheric profiles on ground noise. Propagation is handled with an augmented Burgers' equation method (NASA's sBOOM), and ground noise metrics are compared.

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DLR TAU Simulations for the Second AIAA Sonic Boom Prediction Workshop

Cited by 7 publications

References 15 publications

A novel technique for hypersonic vehicle control

A novel technique for hypersonic vehicle control

Parametric investigation of the aerodynamic and acoustic performance of a low-boom supersonic airliner

Cart3D Simulations for the Second AIAA Sonic Boom Prediction Workshop

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