Journal
ACTA ASTRONAUTICA
Volume 151, Issue -, Pages 357-367Publisher
PERGAMON-ELSEVIER SCIENCE LTD
DOI: 10.1016/j.actaastro.2018.06.028
Keywords
Wide operation range rocket-based combined cycle; Variable attack angle; Wall shear stress; Boundary layer combustion; Skin-friction reduction
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Funding
- National Natural Science Foundation of China [91541110, 51676165]
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The skin-friction in a rocket-based combined-cycle engine operating from Mach 1.5 to 6.0 was analyzed in the present study. The friction proportion of different parts of the engine was investigated to offer a reference for the rearrangement of skin-friction reduction in the engine. The distribution and variation trend of the skin-friction in the flow path as well as its impacts on the engine performance were numerically compared. At three typical flight points, i.e. at 1.8Ma, 3.0Ma and 6.OMa, the change of the skin-friction with attack angle was studied. A special focus was placed on the reduction of the skin-friction by using boundary layer combustion. It was modeled when the airstream flowed into the engine at the speed of 6 Ma. The method of hydrogen combustion in boundary layer has achieved 57.7% skin-friction reduction effect.
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