NACA-RM-A8I29

Abstract

INTRODUCTION <br>A research program was conducted in the Ames 16-foot high-speed wind tunnel which, in conjunction with work in an Ames 7- by 10-foot wind tunnel, continued the investigation of NACA submerged inlets developed during the tests discussed in references 1 and 2. Attention was concentrated on the inlet design found to have the most satisfactory pressure-recovery characteristics during the tests of reference 1. The effects of the following parameters on the pressure recovery at the inlets were investigated. <br>1. Aerodynamic parameters <br>(a) Mach number <br>(b) Angle of attack <br>(c) Mass- flow ratio <br>(d) Boundary-layer thickness <br>2. Model parameters <br>(a) Inlet location with respect to wing and fuselage <br>(b) Inlet lip angle <br>(c) Boundary-layer deflectors <br>Data obtained during the present investigation of the model without inlets and with inlets 16.7 percent of the root chord ahead of the wing-root leading edge only was presented extensively in reference 3. To expedite the publication of the pressure-recovery characteristics for the inlets in other configurations, the present report was prepared.