Experimental Unsteady Pressures at Flutter on the Supercritical Wing Benchmark Model

Dansberry, Bryan E.; Durham, Michael H.; Bennett, Robert M.; Rivera, José A.; Silva, Walter A.; Wieseman, Carol D.; Turnock, David L.

doi:10.2514/6.1993-1592

Cited by 24 publications

(12 citation statements)

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“…Experimentally determined flutter points are available for comparison with the results of simulation. Example plots shown in Figure 23, were produced using previously published data [37]. The figure shows the frequency response functions (between pressure and wing rotation) at the flutter condition.…”

Section: Experimental Datamentioning

confidence: 99%

Ongoing Fixed Wing Research within the NASA Langley Aeroelasticity Branch

Bartels

Chwalowski

Funk

et al. 2015

33rd AIAA Applied Aerodynamics Conference

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The NASA Langley Aeroelasticity Branch is involved in a number of research programs related to fixed wing aeroelasticity and aeroservoelasticity. These ongoing efforts are summarized here, and include aeroelastic tailoring of subsonic transport wing structures, experimental and numerical assessment of truss-braced wing flutter and limit cycle oscillations, and numerical modeling of high speed civil transport configurations. Efforts devoted to verification, validation, and uncertainty quantification of aeroelastic physics in a workshop setting are also discussed. The feasibility of certain future civil transport configurations will depend on the ability to understand and control complex aeroelastic phenomena, a goal that the Aeroelasticity Branch is well-positioned to contribute through these programs. NomenclatureAePW Aeroelastic Prediction Workshop AoA angle of attack ASE aeroservoelastic BSCW Benchmark Supercritical Wing CFD computational fluid dynamics CRM Common Research Model DMCS distributed multiple control surfaces EBF 3 electron beam freeform fabrication FEM finite element method FGM functionally graded materials FRF frequency response function FUN3D unstructured CFD software developed at NASA LaRC GVT ground vibration test LCO limit cycle oscillation LES large eddy simulation OTT oscillating turntable PAPA pitch and plunge apparatus RANS Reynolds-averaged Navier-Stokes ROM reduced order model SUGAR Subsonic Ultra Green Aircraft Research TBW truss-braced wing TDT Transonic Dynamics Tunnel ZONA51 oscillatory supersonic lifting surface theory 1 Aerospace Engineer, Aeroelasticity Branch, AIAA Senior Member.

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Section: Experimental Datamentioning

confidence: 99%

Ongoing Fixed Wing Research within the NASA Langley Aeroelasticity Branch

Bartels

Chwalowski

Funk

et al. 2015

33rd AIAA Applied Aerodynamics Conference

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“…[2] The test cases for the AePW are based on two wind tunnel experiments of the BSCW that were Unforced pressure distributions are also available for these flow conditions. Table 2 summarizes the second AePW cases, and figure 2 (taken from Ref.…”

Section: The Benchmark Supercritical Wing (Bscw)mentioning

confidence: 99%

“…The first experiment is a flutter test, in which the rigid wing was suspended from a pitch and plunge apparatus (PAPA), simulating two degrees-of-freedom flutter[2]. The BSCW was tested for flutter in air and in R-12 gas.…”

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confidence: 99%

Flow Simulations for the Second Aeroelastic Prediction Workshop Using the EZNSS Code

Raveh

2016

34th AIAA Applied Aerodynamics Conference

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The paper presents numerical simulations that were performed with the EZNSS flow solver for the second Aeroelastic Prediction Workshop (AePW). The reference test cases for the AePW are based on two wind tunnel experiments of the Benchmark Supercritical Wing (BSCW), including a flutter test, and forced excitation tests. Three cases were adressed, at different transonic flow conditions: Two cases at lower Mach numbers of 0.7, 3 • angle of attack (AoA), and 0.74, 0 • AoA, and one more physically compex case at Mach 0.85, 5 • AoA. The cases were analyzed with the EZNSS code, using several computational setups and turbulence models. The simulations were able to predict accurately the flutter response and the response to prescribed motion at the lower Mach number. The higher Mach number case, which involves a strong shock, separated flow behind the shock, and some flow unsteadiness, was more challenging. In the static analysis, different turbulence models yielded different upper-surface shock positions, and none of the models were able to capture accurately the pressure recovery behind the shock. However, the unsteady aerodynamic response to prescribed pitch motion was simulated with good correlation to the wind tunnel data. The paper also presents flutter predictions based on unsteady aerodynamic reduced-order modeling (ROM) thus validating and assessing the efficiency of the ROM, and the flutter prediction methodology. 1 Downloaded by FLORIDA INSTITUTE OF TECHNOLOGY on June 25, 2016 | http://arc.aiaa.org |

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“…The BSCW was tested in the NASA Transonic Dynamics Tunnel (TDT) 16 as part of the Benchmark Models Program (BMP) 17,18,19 on a Pitch and Plunge Apparatus (PAPA) and later as a testbed for hardware checkout of the Oscillating TurnTable (OTT) system. 8 The model is shown mounted in the wind tunnel during testing on the OTT, Figure 2.…”

Section: Wind Tunnel Model and Facilitymentioning

confidence: 99%

Experimental data from the Benchmark SuperCritical Wing wind tunnel test on an oscillating turntable

Heeg

Piatak

2013

54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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The Benchmark SuperCritical Wing (BSCW) wind tunnel model served as a semi-blind testcase for the 2012 AIAA Aeroelastic Prediction Workshop (AePW). The BSCW was chosen as a testcase due to its geometric simplicity and flow physics complexity. The data sets examined include unforced system information and forced pitching oscillations. The aerodynamic challenges presented by this AePW testcase include a strong shock that was observed to be unsteady for even the unforced system cases, shock-induced separation and trailing edge separation. The current paper quantifies these characteristics at the AePW test condition and at a suggested benchmarking test condition. General characteristics of the model's behavior are examined for the entire available data set.

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Experimental Unsteady Pressures at Flutter on the Supercritical Wing Benchmark Model

Cited by 24 publications

References 0 publications

Ongoing Fixed Wing Research within the NASA Langley Aeroelasticity Branch

Ongoing Fixed Wing Research within the NASA Langley Aeroelasticity Branch

Flow Simulations for the Second Aeroelastic Prediction Workshop Using the EZNSS Code

Experimental data from the Benchmark SuperCritical Wing wind tunnel test on an oscillating turntable

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