NACA-RM-A50E02

Abstract

INTRODUCTION <br>Test were conducted in the Ames 16-foot high-speed wind tunnel to continue investigation, at higher subsonic Mach numbers, of NACA submerged inlets developed in the Ames 7- by 10-foot wing tunnels as discussed in references 1 and 2. For the tests in the 16-foot wind tunnel, the inlets were mounted at four longitudinal locations on a model of a hypothetical fighter airplane. Results of tests in the 16-foot wind tunnel for inlets in the most forward position on the fuselage and with boundary-layer deflectors were reported in reference 3 with the presentation of ram-recovery ratios, mass-flow ratios, and pressure distribution. Results for inlets at four positions on the fuselage (with and without boundary-layer deflectors) were reported in reference 4 with the presentation of ram-recovery ratios and mass-flow ratios. To expedite release, reference 4 presented ram-recovery and mass-flow ratios computed from pressure data averaged during the tests by an integrating manometer. The present report presents ram-recovery and mass-flow ratios computed from the data used in reference 4, but computed by the method of reference 3, which yields more precise values of pressure recovery and local mass-flow ratios in the inlet mounted in the rearmost position are also presented.