Abstract: An experimental investigation is conducted in a high speed wind tunnel to suppress the acoustic resonance and additional drag of a weapons bay for flying wing configuration aircraft and to improve its store separation characteristics when its doors are opened.Conventional leading edge spoilers are used to disturb the weapons bay free shear layer.Detailed static-pressure and fluctuating-pressure measurements are obtained on the weapons bay walls to determine the effects on weapons bay flow characteristics.Forces and moments on the aircraft and the store model are measured to determine the effects of the flow control method on additional drag and store separation characteristics.The results indicate that for a flying wing configuration aircraft, the additional drag of the weapons bay accounts for as much as 60%-110% of the total vehicle drag.The amplitude of resonant tones is measured up to 185 dB.Very large pitching moment renders store release difficult, and it may cause the stores to rise back into the cavity and collide with the aircraft.Using the flow control method can reduce the amplitude of the weapons bay tones by 5-8 dB and can reduce additional drag up to 20%.Meanwhile, spoilers can enhance the characteristics of weapon departure from the weapons bay effectively.

Key words: flying wing configuration, weapons bay, acoustic resonance, flow control, separation characteristic