Boundary layer analysis of a Centaur standard shroud

Details Boundary layer analysis of a Centaur standard shroud Boundary layer analysis of a Centaur standard shroud

Mar 1978

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1978stin...7821404h&link_type=abstract

Unknown

Computer Science

Boundary Layers, Centaur Project, Shrouds, Flanges, Fluid Flow, Mach Number, Titan Centaur Launch Vehicle, Transonic Flow

Scientific paper

An analytical boundary layer investigation was carried out in conjunction with an experimental wind tunnel test to determine the discharge characteristics of the Centaur shroud ascent vent system on the Titan/Centaur launch vehicle. This involved estimating the effect of the local boundary layers on the vent discharge for vehicle Mach numbers ranging from 0.8 to 1.56. The growth of the boundary layer along the vehicle was influenced by the interaction with flanges protruding into the flow and by the longitudinal corrugations in the vehicle surface. The effects of the flange and corrugations were treated by approximate techniques. In addition, boundary layer calculations were made for a 3 percent model of the launch vehicle compared with experimental results.

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