Analytical and experimental heat transfer and flow-field prediction on a rectangular reentry module

Laganelli, A. L.

doi:10.2172/6087747

Cited by 3 publications

(4 citation statements)

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“…In recent free-flight experiments of a cube in a hypersonic flow (Seltner et al 2019), the authors claimed the presence of a separation at the leading edge of the cube, but the resolution of the schlieren was not high enough to capture it in detail. In addition to cylinders, heating rates to cuboids have also been studied in the reports of Crosby and Knox (1980), and Laganelli (1980), who experimentally measured heat fluxes to a cube in a Mach 8 flow at discrete locations using thin-foil calorimeters. However, these studies only report results at one flow condition and at limited discrete locations on the model surface.…”

Section: Introductionmentioning

confidence: 99%

Experimental characterization of the hypersonic flow around a cuboid

et al. 2020

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Understanding the hypersonic flow around faceted shapes is important in the context of the fragmentation and demise of satellites undergoing uncontrolled atmospheric entry. To better understand the physics of such flows, as well as the satellite demise process, we perform an experimental study of the Mach 5 flow around a cuboid geometry in the University of Manchester High SuperSonic Tunnel. Heat fluxes are measured using infrared thermography and a 3D inverse heat conduction solution, and flow features are imaged using schlieren photography. Measurements are taken at a range of Reynolds numbers from 40.0 × 10 3 to 549 × 10 3. The schlieren results suggest the presence of a separation bubble at the windward edge of the cube at high Reynolds numbers. High heat fluxes are observed near corners and edges, which are caused by boundary-layer thinning. Additionally, on the side (off-stagnation) faces of the cube, we observe wedge-shaped regions of high heat flux emanating from the windward corners of the cube. We attribute these to vortical structures being generated by the strong expansion around the cube's corners. We also observe that the stagnation point of the cube is off-centre of the windward face, which we propose is due to sting flex under aerodynamic loading. Finally, we propose a simple method of calculating the stagnation point heat flux to a cube, as well as relations which can be used to predict hypersonic heat fluxes to cuboid geometries such as satellites during atmospheric re-entry.

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Section: Introductionmentioning

confidence: 99%

Experimental characterization of the hypersonic flow around a cuboid

et al. 2020

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“…In this region, the numerical results show a fairly smooth variation of heat flux, while the experimental results show significant noise and variation. Increased noise in the heat flux values on a planar hypersonic stagnation surface has been previously observed in the experiments of Laganelli [14]. The cause of these variations is unknown, and more detailed study of the flow in this region is warranted to fully understand this behaviour.…”

Section: Differences Between Cfd and Experimentsmentioning

confidence: 82%

“…Previous experimental studies of the hypersonic flow around cuboid geometries [13,14,15] have only focused on taking measurements of models at zero incidence to the free-stream flow. In order to build a complete understanding of the heat fluxes experienced by faceted shapes during Table 4: Summary of key experimental heating results from [15] for a cube at 0°incidence at M = 5.…”

Section: Discussionmentioning

confidence: 99%

“…The heating rates to cuboids were first studied in the reports of Crosby & Knox [13], and Laganelli [14], who experimentally measured heat fluxes to a cube in a Mach 8 flow at discrete locations using thin-foil calorimeters. More recently, measurements of the hypersonic heat fluxes to a cube were made using InfraRed Thermography (IRT) [15] so that the heat fluxes across the entire surface of the cube could be measured, rather than just at discrete points on the geometry.…”

Section: Introductionmentioning

confidence: 99%

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