Numerical and experimental analyses of the vortical flow around the SACCON configuration

Schütte, Andreas; Hummel, Dietrich; Hitzel, Stephan M.

doi:10.2514/6.2010-4690

Cited by 63 publications

(40 citation statements)

References 5 publications

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“…Its leading edge radius transforms from sharp at the apex, to round at the body wing junction and back to sharp towards the tip [2,3,4]. Experience for the influence of round leading edges on vortical flow is generally available for delta wings [1].…”

Section: List Of Symbolsmentioning

confidence: 98%

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Vortical flow prediction for the design of a wind tunnel experiment with a pitching lambda wing

Wiggen

Voß

2014

CEAS Aeronaut J

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The IWEX wind tunnel model (Instationäres Wirbelexperiment, German for: Unsteady Vortex Experiment) was developed to study vortical flow at static and oscillating angles of attack. Numerical computations were performed beforehand to study important aerodynamic aspects. The focus of this paper is on those results that were affecting the design of the model. The experimental concept of a new test rig, wind tunnel walls and the new half wing model is briefly described. The lambda wing has a purely round leading edge with a constant nose radius to chord ratio of 0.5 %. The flow characteristics of the main vortex, generated at the nose of the main wing, and the smaller tip vortex are specified. The inboard motion of the main vortex with increasing angle of attack and the consequences for the load distribution are described. The free stream Mach number range of the test envelope is from 0.3 to 0.7. Therefore, transonic effects, especially shock-vortex interactions triggering vortex development, had to be analyzed for a safe design of the model. A peniche was designed to minimize the differences of the flow character compared to reference results of the model without wind tunnel walls. The effects of corner separation and displacement are specified at different stages of the iterative process. Finally, basic results for a pitching motion are discussed, based on global and distributed coefficients.

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Section: List Of Symbolsmentioning

confidence: 98%

“…For the presented studies, the Spalart-Almaras one-equation turbulence model was used [9]. Former investigations for the validation of the numerical methods have shown that the best agreement results from the comparison with the experimental data have been achieved with this turbulence model [4].…”

Section: Modeling and Grid Influencesmentioning

confidence: 98%

Vortical flow prediction for the design of a wind tunnel experiment with a pitching lambda wing

Wiggen

Voß

2014

CEAS Aeronaut J

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“…This regression method is applied in the frequency domain using Eqs. (12) and (13). Specific application of this method is described in Refs.…”

Section: B Parameter Estimation Using Two-step Linear Regressionmentioning

confidence: 99%

“…Experimentalists within the AVT-161 team conducted dynamic wind-tunnel tests on SACCON undergoing forced oscillation in pitch, roll, and yaw to measure the dynamic stability and aerodynamic characteristics 3,8 . Other team members ran parallel dynamic computational studies following a similar approach of modeling SACCON undergoing pitch, roll, and yaw oscillation with their respective CFD tools 4,[7][8][9][10][11][12][13][14] 11,14,15 . Since the authors plan to contribute to the AVT-161 follow-on effort, this paper is reporting on a preliminary exploratory study to investigate the aerodynamic modeling of SACCON from wind tunnel data and NASA CFD predictions of aerodynamic responses to linear and nonlinear flows over a range of conditions.…”

Section: Introductionmentioning

confidence: 99%

System Identification Applied to Dynamic CFD Simulation and Wind Tunnel Data

Murphy

Klein

Frink

et al. 2011

AIAA Atmospheric Flight Mechanics Conference

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Demanding aerodynamic modeling requirements for military and civilian aircraft have provided impetus for researchers to improve computational and experimental techniques. Model validation is a key component for these research endeavors so this study is an initial effort to extend conventional time history comparisons by comparing model parameter estimates and their standard errors using system identification methods. An aerodynamic model of an aircraft performing one-degree-of-freedom roll oscillatory motion about its body axes is developed. The model includes linear aerodynamics and deficiency function parameters characterizing an unsteady effect. For estimation of unknown parameters two techniques, harmonic analysis and two-step linear regression, were applied to roll-oscillatory wind tunnel data and to computational fluid dynamics (CFD) simulated data. The model used for this study is a highly swept wing unmanned aerial combat vehicle. Differences in response prediction, parameters estimates, and standard errors are compared and discussed.

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“…The mesh is constructed with an O topology and thirteen blocks. The geometry of the case is based on the information provided in Schütte et al [53] and Tormalm and Schmidt [26]. We analyze the flow around the UCAV using a RANS flow solver [47] with a Spalart-Allmaras turbulence model [54].…”

Section: Saccon Ucav: Test Case Descriptionmentioning

confidence: 99%

Computing Stability Derivatives and Their Gradients for Aerodynamic Shape Optimization

Mader

Martins

2014

AIAA Journal

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Numerical and experimental analyses of the vortical flow around the SACCON configuration

Cited by 63 publications

References 5 publications

Vortical flow prediction for the design of a wind tunnel experiment with a pitching lambda wing

Vortical flow prediction for the design of a wind tunnel experiment with a pitching lambda wing

System Identification Applied to Dynamic CFD Simulation and Wind Tunnel Data

Computing Stability Derivatives and Their Gradients for Aerodynamic Shape Optimization

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