A Low-speed Investigation of a Fuselage-side Air Inlet for Use at Transonic Flight Speeds

Low-speed pressure-recovery and surface-pressure measurements for a twin fuselage-side air-inlet arrangement intended for use at transonic speeds are presented. The model was developed by adding a canopy and nose-wheel fairing to basic transonic annular inlet studied in TN 2685. The results indicate shape requirements of fuselage nose, canopy, and nose-wheel fairing for maintaining substream surface velocities everywhere ahead of entrance.