A new forced oscillation capability for the Transonic Dynamics Tunnel

Piatak, David J.; Cleckner, Craig S.

doi:10.2514/6.2002-171

Cited by 14 publications

(6 citation statements)

References 5 publications

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“…This data set was obtained twelve years ago during checkout testing of the new TDT OTT model support system and was therefore not the primary focus of a computational research project. Some data is available in graphical form, 10 but it is viewed as obscure enough to serve as the basis for a semi-blind test case. AePW analysts were not given the experimental data prior to the workshop.…”

Section: Benchmark Supercritical Wing Computational Resultsmentioning

confidence: 99%

“…The second configuration utilized the NASA Benchmark Supercritical Wing (BSCW), which was tested in the TDT in 2000. 10 This data set was acquired for a rigid rectangular planform similar to the RSW that was sidewall-mounted to a large splitter plate assembly and oscillated in pitch via the TDT Oscillating Turntable (OTT), exhibiting a strong shock-induced separated flow at a moderate angle of attack. The third configuration considered for AePW extended the unsteady aerodynamic prediction to a weakly-coupled aeroelastic test case involving a more complex geometry: the HIgh REynolds Number AeroStructural Dynamics (HIRENASD) configuration.…”

Section: Introductionmentioning

confidence: 99%

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FUN3D Analyses in Support of the First Aeroelastic Prediction Workshop

Chwalowski

Heeg

2013

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

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This paper presents the computational aeroelastic results generated in support of the first Aeroelastic Prediction Workshop for the Benchmark Supercritical Wing (BSCW) and the HIgh REynolds Number AeroStructural Dynamics (HIRENASD) configurations and compares them to the experimental data. The computational results are obtained using FUN3D, an unstructured grid Reynolds-averaged Navier-Stokes solver developed at NASA Langley Research Center. The analysis results for both configurations include aerodynamic coefficients and surface pressures obtained for steady-state or static aeroelastic equilibrium (BSCW and HIRENASD, respectively) and for unsteady flow due to a pitching wing (BSCW) or modally-excited wing (HIRENASD). Frequency response functions of the pressure coefficients with respect to displacement are computed and compared with the experimental data. For the BSCW, the shock location is computed aft of the experimentallylocated shock position. The pressure distribution upstream of this shock is in excellent agreement with the experimental data, but the pressure downstream of the shock in the separated flow region does not match as well. For HIRENASD, very good agreement between the numerical results and the experimental data is observed at the mid-span wing locations.

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Section: Benchmark Supercritical Wing Computational Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

FUN3D Analyses in Support of the First Aeroelastic Prediction Workshop

Chwalowski

Heeg

2013

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

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“…Models may be oscillated sinusoidally at constant or varying frequencies, be subjected to a step input, or undergo user-defined motions. It is anticipated that unsteady pressure measurements due to precisely controlled model motions will provide valuable data for CFD correlation and aircraft design with respect to unsteady aerodynamic/aeroelastic phenomena [71]. Figure 1 highlights key components of the OTT.…”

Section: Oscillating Turntable (Ott)mentioning

confidence: 99%

“…To this end, experiments designed to measure the unsteady aerodynamic response of various configurations provide significant and valuable information [64,71,86,99]. Experimental results are compared to various types of numerical analyses (such as CFD) to provide insight into the underlying physics of the problem.…”

Section: Introductionmentioning

confidence: 99%

Identification of Nonlinear Aeroelastic Systems Based on the Volterra Theory: Progress and Opportunities

Silva

2005

Nonlinear Dyn

178

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The identification of nonlinear aeroelastic systems based on the Volterra theory of nonlinear systems is presented. Recent applications of the theory to problems in computational and experimental aeroelasticity are reviewed. Computational results include the development of computationally efficient reduced-order models (ROMs) using an Euler/Navier-Stokes flow solver and the analytical derivation of Volterra kernels for a nonlinear aeroelastic system. Experimental results include the identification of aerodynamic impulse responses, the application of higher-order spectra (HOS) to wind-tunnel flutter data, and the identification of nonlinear aeroelastic phenomena from flight flutter test data of the active aeroelastic wing (AAW) aircraft.

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“…For the pitching oscillations one of the key features of the TDT, its forced oscillation system known as the Oscillating Turntable (OTT) 7 , was used. The OTT utilizes a powerful rotary hydraulic actuator, rated for 495000 inlbf, and a digital Proportional, Integral, Derivative, Feed forward (PIDF) control system to position and oscillate models.…”

Section: Test Facilitymentioning

confidence: 99%