Numerical Investigations of Flow Separation on the AVT-183 53 Degree Swept Diamond Wing Configuration

Daniel, D.; Malloy, Donald J.; Reasor, Daniel A.; Morris, Craig C.

doi:10.2514/6.2015-0066

Cited by 5 publications

(5 citation statements)

References 7 publications

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“…An example is shown in Fig. 62 from Daniel et al (118) , with CFD predictions from the Kestrel code (119) and experimental results from Hoevelmann (120,121) . The left portion is an example where the incipient separation matched between computation and experiment, and the correlation is very good for the entire wing.…”

Section: Three-dimensional Flows Blunt-leading-edge Vortices Singlementioning

confidence: 99%

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The discovery and prediction of vortex flow aerodynamics

Luckring

2019

Aeronaut. j.

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High-speed aircraft often develop separation-induced leading-edge vortices and vortex flow aerodynamics. In this paper, the discovery of separation-induced vortex flows and the development of methods to predict these flows for wing aerodynamics are reviewed. Much of the content for this article was presented at the 2017 Lanchester Lecture and the content was selected with a view towards Lanchester’s approach to research and development.

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Section: Three-dimensional Flows Blunt-leading-edge Vortices Singlementioning

confidence: 99%

“…The right portion is for a lower angle-of-attack where the prediction of incipient separation did not match the experimental location, and the correlation of wing pressures is degraded, especially as regards to . Daniel et al (118) .…”

Section: Three-dimensional Flows Blunt-leading-edge Vortices Singlementioning

confidence: 99%

The discovery and prediction of vortex flow aerodynamics

Luckring

2019

Aeronaut. j.

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“…These data sets are used for the relevant CFD comparisons. [15][16][17][18][19][20][21][22] In this section, the short term repeatability of the single W/T runs is considered. Overall, the short term repeatability of the W/T measurements is found to be very good, both for the aerodynamic forces and moments as well as for the steady surface pressures.…”

Section: B Short Term Repeatabilitymentioning

confidence: 99%

“…In the present paper, the force and the steady surface pressure measurements from the first W/T campaign are regarded, while the Stereo PIV, the hot-wire and the unsteady surface pressure measurements undertaken within the other W/T campaigns are regarded in a related paper by Hövelmann et al 14 In the context of the present task group AVT-183, the obtained W/T results are also considered as comparison data for the numerous numerical computations that are available. [15][16][17][18][19][20][21][22] Beyond that, the conducted W/T investigations provide in general an extensive experimental data base for overall CFD validation, which focus on smooth surface separation with consecutive leading-edge vortex formation at a moderately swept, low aspect ratio wing with rounded leading-edge contour.…”

Section: Introductionmentioning

confidence: 99%

Leading-Edge Roughness Effects on the Flow Separation Onset of the AVT-183 Diamond Wing Configuration (Invited)

Hövelmann

Knoth

Breitsamter

2015

53rd AIAA Aerospace Sciences Meeting

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Experimental investigations on a 53 • leading-edge sweep diamond wing configuration with rounded leading-edge contour as part of the NATO Science and Technology Organization (STO) task group AVT-183 (Applied Vehicle Technology panel) are presented. The results obtained in a low speed wind tunnel facility include aerodynamic forces and moments and steady surface pressures. Special emphasis is laid on the effects of different leading-edge roughness, which is applied in the experimental analyses to ensure turbulent boundary layer characteristics on the entire diamond wing surface. The results show that the flow separation onset and the emerging leading-edge vortex are very sensitive to the roughness height applied to the diamond wing leading-edge. Both reasonably-tripped and over-tripped cases are obtained compared to the free transition case, which is discussed in detail. Moreover, comprehensive analyses on both the short term and the long term repeatability of the related cases are presented. Based on this analysis, one specific leadingedge roughness is defined as the target flow case, which provides the baseline for the flow field investigations and general CFD validation within the task group AVT-183.

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“…In the context of the task group AVT-183, the obtained W/T results are also considered as comparison data for numerical computations. [9][10][11][12][13][14][15][16] Beyond that, the conducted W/T investigations provide in general an extensive experimental data base for overall CFD validation.…”

Section: Introductionmentioning

confidence: 99%

Experimental Analyses on the Flow Field Characteristics of the AVT-183 Diamond Wing Configuration (Invited)

Hövelmann

Grawunder

Buzica

et al. 2015

53rd AIAA Aerospace Sciences Meeting

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Comprehensive experimental flow field investigations are presented on a 53 • leadingedge sweep diamond wing configuration with rounded leading-edge contour as part of the NATO Science and Technology Organization (STO) task group AVT-183 (Applied Vehicle Technology panel). The results obtained in a low speed wind tunnel facility depict the mean and turbulent flow field characteristics that are mainly dominated by a smooth surface separation with subsequent leading-edge vortex formation. Both Stereo Particle Image Velocimetry and Hot-Wire Anemometry are applied to detect the emerging flow phenomena in several chord-wise sections including near-wall data. Details of the leading-edge vortex onset and progression are analyzed and discussed. Over almost the entire length of its existence, the leading-edge vortex is characterized by retarded axial flow, showing thus vortex bursting tendencies. The corresponding turbulent fluctuations show maxima close to the evolution of the leading-edge vortex and decrease towards the trailing-edge. The obtained flow phenomena are thereby significant for the AVT-183 diamond wing configuration with its smooth surface separation due to the rounded leading-edge contour. Based on the derived flow field characteristics, a high-quality data set suitable for general CFD validation is provided.

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Numerical Investigations of Flow Separation on the AVT-183 53 Degree Swept Diamond Wing Configuration

Cited by 5 publications

References 7 publications

The discovery and prediction of vortex flow aerodynamics

The discovery and prediction of vortex flow aerodynamics

Leading-Edge Roughness Effects on the Flow Separation Onset of the AVT-183 Diamond Wing Configuration (Invited)

Experimental Analyses on the Flow Field Characteristics of the AVT-183 Diamond Wing Configuration (Invited)

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