THE CALCULATION OF ADIABATIC LAMINAR BOUNDARY LAYERnSHOCK WAVE INTERACTIONS IN AXI-SYMMETRIC FLOW:PART I. HOLLOW CYLINDER-FLARE BODIES WITH ZERO SPIN

摘要

A method is described for calculating the overall properties of flare-induced laminar boundary layer shock wave interactions on axi-symmetric bodies at zero incidences, under adiabatic conditions.nThe method consists of an extension to axi-symmetric flow of the two-dimensional integral boundary layer method of Lees and Reeves, in the improved form recently developed by Klineberg. The relationship between the local slope of the displacement surface and the external Mach number is calculated by a suitable inversion of the second-order shock-expansion method of Silverton and Dennis.