Abstract: With the performance requirements for high maneuverability, ultra-long-range strike and stealth of the new-generation advanced manned or unmanned combat-aircraft, the loading of internal weapons has become a necessary choice. When the mass-inertia load of the internal weapons is larger than the unsteady aerodynamic load, effective weapon separation is usually not a problem. However, when the mass-inertia load of the internal weapons is smaller than the unsteady aerodynamic load, it may lead to incompatible separation phenomenon, such as excessive pitch angle and rapid rolling in the aircraft-store separation. In this paper, the exploratory wind tunnel freedrop testing is carried out on the aircraft-store compatibility and flow control for the internal weapons separation. Passive flow control devices, such as sawtooth and flat-top spoilers, are arranged at the leading-edge of weapons bay and the influence of flow devices on internal weapons separation is studied by using the unsteady drop testing method combined with high-speed Schlieren technology in the high-speed wind tunnel. The criterion expression of aircraft-store separation compatibility of the internal weapons which have slender and rotational body is proposed. It is found that the leading-edge sawtooth and flat-top spoilers can generate spoiler shock-wave in the expansion region, which generates the high pressure on the store head reducing pitching moment. The leading-edge spoilers cannot affect the vertical positions, whereas it so greatly affected the pitch-angle (\theta ) motion of the store. The effect of flow control of sawtooth spoiler (STS) on the aircraft-store compatibility of the internal store separation is better than that of flat-top spoiler (FTS).