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Erschienen in:
2006 | OriginalPaper | Buchkapitel
Analytically obtained data compared with shock tunnel heat flux measurements at a conical body at M = 6
verfasst von : J. Srulijes, F. Seiler
Erschienen in: New Results in Numerical and Experimental Fluid Mechanics V
Verlag: Springer Berlin Heidelberg
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This paper presents analytical methods for calculating the heating of a hypersonic projectile equipped with a conical forebody. Calculated heat fluxes are compared with data obtained from ISL shock tube experiments. Two theoretical approaches based on the classical boundary layer theory are described for the laminar as well as for the turbulent boundary layer formation. In both cases, a coordinate transformation is applied that enables flat plate solutions to be adapted to conical coordinates. The heat flux on the cone’s surface is measured with special thin film gauges. The heat flux measurements performed at a flight altitude of 15 km show a laminar to turbulent boundary layer transition. In contrast to this, the boundary layer at a flight altitude of 21 km develops fully laminar.