Analysis of Single Hole Simulated Battle Damage on a Wing Using Particle Image Velocimetry

Almond, Mathew T.; Render, P. M.; Walker, Donald G.

doi:10.2514/6.2015-2573

Cited by 2 publications

(5 citation statements)

References 9 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…As was noted by Almond et al (20) , the bulk of the jet mass flow exits through the rear of the hole, with a velocity ratio of around 0.13 and 0.3 for the 2° and 8° cases, respectively, measured in the centre of the jet. This velocity ratio is low compared with the majority of JICF applications and would be classed as a weak case.…”

Section: Results and Analysissupporting

confidence: 62%

“…PIV tests have been performed at all angles between 2° and 8°, and no distinct switch in flow pattern was seen. When comparing the velocity ratio found in Almond et al (20) with JICF literature, all incidence angles from the battle damage studies should produce ‘weak’ jet features. However, large effects on aerodynamic performance are seen throughout the incidence range, particularly above 2° incidence.…”

Section: Results and Analysismentioning

confidence: 91%

“…PIV data have been used to identify several features of the flowfield produced by simulated battle damage (20) . More specifically, it has been used to describe the flow features on the upper surface of a wing, with particular interest to the areas above and behind the hole.…”

Section: Results and Analysismentioning

confidence: 99%

“…It was shown by Almond et al (20) that, with a battle damaged wing, the jet does not exit the full area of the hole, but the jet vertical velocity cross-section is biased towards the rear. The velocity ratio was also found to be low (<0.3).…”

Section: Introductionmentioning

confidence: 99%

“…Gopalan et al (19) classify a low velocity ratio ( V R ) as <2; however, they performed experiments down to V R = 0.5. For comparison, a battle damaged wing showing ‘strong’ characteristics (i.e., large effects on lift/drag performance and large spanwise effects seen in flow visualisation studies) can have a velocity ratio as low as 0.22, increasing to around 0.3 at higher incidence angles (20) . This suggests that even at high incidence angles, the flow characteristics of the jet are of the weak jet type, using the JICF nomenclature, even though large effects can be seen in the aerodynamic performance and on the surface flow.…”

Section: Introductionmentioning

confidence: 99%

See 4 more Smart Citations

Investigation of the flowfield induced by simulated battle damage

et al. 2017

View full text Add to dashboard Cite

Particle Image Velocimetry (PIV) has been used to study the complex flowfield created by simulated battle damage to a two-dimensional wing. Computational Fluid Dynamics (CFD) predictions have also been used for validation of internal cavity flow. Two damage cases were selected for the study; both cases were simulated using a single hole with diameters equal to 20% and 40% of the chord, located at the wing half-chord. Wind-tunnel tests were conducted at a Reynolds number of 500,000 over a range of incidences from 0 to 10° with two-component PIV measurements made on three chordwise and three spanwise planes. The PIV data were analysed and compared to CFD data of the same damage cases. The PIV data have shown lower velocity ratios and lower vorticity in the jet compared to past Jet in Cross-Flow experiments and CFD was used to describe the flow features inside the cavity of the wing. It was seen that the wing cavity has large effects on the external flow features, particularly for the 20% damage case. Finally, the flow field data have been related to force balance data. At higher incidence angles, the larger force coefficient increments in both lift and drag can be attributed to the larger wakes and higher jet strengths.

show abstract

Section: Results and Analysissupporting

confidence: 62%

Section: Results and Analysismentioning

confidence: 91%

Section: Results and Analysismentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Investigation of the flowfield induced by simulated battle damage

et al. 2017

View full text Add to dashboard Cite

show abstract

Architecture design of four redundant flight control system

谢,

周,

曾

et al. 2024

First Aerospace Frontiers Conference (AFC 2024)

View full text Add to dashboard Cite

Redundant flight control systems typically have high flexibility and customizability, suitable for different types of highvalue drones. This article proposes a new architecture for a four degree redundant flight control system, which is based on the traditional four degree redundant flight control system architecture. By adding a CANFD bus to achieve signal interaction between flight control computers, the resulting voting values can be used as a reference for signal arbitration in the next cycle. This design can increase the reliability of the redundancy system and solve the problem of inability to distinguish faults when the signal voting is 2:2 in traditional designs. Finally, using the proposed method, a redundant flight control system was developed for a certain experimental drone, and its effectiveness was successfully verified through ground semi physical experimental testing.

show abstract

Analysis of Single Hole Simulated Battle Damage on a Wing Using Particle Image Velocimetry

Cited by 2 publications

References 9 publications

Investigation of the flowfield induced by simulated battle damage

Investigation of the flowfield induced by simulated battle damage

Architecture design of four redundant flight control system

Contact Info

Product

Resources

About