Abstract
Experiments on the effect of trip geometry, size, and location on the position of transition at local Mach numbers up to 8.5 are presented. The pressure drag of the trip is investigated at local Mach numbers of 4.7 and 5.5. Based on test results, a flow model was constructed which includes trip-produced multiple vortex filaments similar to those found at supersonic speeds that are assumed to be responsible for introducing the disturbances that lead to transition. The Reynolds number based on the distance from the leading edge to the roughness position as well as Mach number and wall-to-total temperature ratio should be considered in choosing the smallest effective trip size. The effect of trip shape on the position of transition at hypersonic speeds is small; however, certain shapes exhibit the advantageous characteristic of having drag coefficients which were relatively independent of roughness height over a restricted range of the variables tested.
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Morrisette, E.L., Stone, D.R., Whitehead, A.H. (1969). Boundary-Layer Tripping with Emphasis on Hypersonic Flows. In: Wells, C.S. (eds) Viscous Drag Reduction. Springer, Boston, MA. https://doi.org/10.1007/978-1-4899-5579-1_2
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DOI: https://doi.org/10.1007/978-1-4899-5579-1_2
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