Accession Number : ADA952515

Title :   Project SQUID: Effect of Boundary-Layer Growth in a Shock Tube on Shock Reflection from a Closed End.

Descriptive Note : Technical rept.,

Corporate Author : CORNELL AERONAUTICAL LAB INC BUFFALO N Y

Personal Author(s) : Rudinger,George

Report Date : JUN 1961

Pagination or Media Count : 43

Descriptors :   *Boundary layer, *Shock tubes, *Shock waves, Compressible flow, Ducts, Gas flow, Orifices, Pressure, Reflection, Time

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE