Performance of External-internal Compression Inlet with Abrupt Internal Turning at Mach Numbers 3.0 to 2.0 PDF Download

Author: Leonard J. Obery
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 21

Get Book Here

Book Description
An inlet with combined external and internal compression, formed by spike and cowl oblique shocks, and an over-all length of 2.5 inlet diameters was investigated at Mach numbers from 3.0 to 2.0 over a range of angles of attack. At the design Mach number of 3.0 the low angle cowl, which turned the flow supersonically, generated two internal shocks and focused them on the centerbody surface. These compression waves, with their high pressure gradient, were cancelled by abrupt centerbody turning. This investigation showed that with proper boundary-layer control on the centerbody this method of internal compression did not adversely affect the high performance of the inlet.