Force and pressure-recovery characteristics of a conical-type nose inlet operating at Mach numbers of 1.6 to 2.0 and at angles of attack to 9 degrees

Andrew Beke, J. L. Allen
Nov 1952

An axially symmetric spike-type nose inlet suitable for a nacelle power-plant installation was investigated in the Lewis 8- by 6-foot supersonic tunnel at Mach numbers of 1.6, 1.8, and 2.0 and at angles of attack from 0 to 9 degrees. The inlet was designed to attain a mass-flow ratio of unity at a flight Mach number of 2.0. Force and pressure-recovery data were obtained for two subsonic diffuser area variations and are presented without detailed analysis.

An Adobe Acrobat (PDF) file of the entire report: