Hypersonic transition studies on a slender cone at small angles of attack.

A numerical study of several parameters that influence heat transfer, drag, and shock-layer mass-flow rate at laminar and transitional (laminar and turbulent) flow conditions was conducted. The calculations were performed with a detailed computer code, which has been demonstrated to yield excellent comparisons with flightand ground-test data and with results of other detailed codes. The study focuses the attention of designers of future transatmospheric vehicles on fundamental parameters, such as bluntness and angle of attack, which can have an impact on even initial design and trajectory options. Although the requirement of a reliable transition criterion was not as critical in this study as it obviously would be in aeroheating design studies, the problem of selecting a dependable criterion for the present investigation was evident in this discussion. The effects and trends of the parameters, which also include influence of gas chemistry, are intended to be general in nature, but the information should be of practical use in the design of slender hypersonic vehicles for the ranges of body angle and angle of attack considered in this study. Nomenclaturenumber n = shock layer distance from surface p = pressure Q = integrated heat-transfer rate q = heat-transfer rate Re e = momentum thickness Reynolds number r n = nose radius 5 = surface distance £/", = freestream velocity X -axial distance a = angle of attack 7 = ratio of specific heats 0. c . = cone half angle = circumferential angle measured from windward centerline \l/ = flow turning angle Subscripts e = boundary-layer edge sh =shock ref = reference value w = wall oo = freestream condition Presented as

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Hypersonic transition studies on a slender cone at small angles of attack.

Cited by 6 publications

References 2 publications

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