A wind-tunnel investigation was conducted in the Langley 12-Foot Low-Speed Tunnel to study the low-speed stability and control characteristics of a series of four flying wings over an extended range of angle of attack (-8 deg to 48 deg). Because of the current emphasis on reducing the radar cross section (RCS) of new military aircraft, the planform of each wing was composed of lines swept at a relatively high angle of 50 deg, and all the trailing-edge lines were aligned with one of the two leading edges. Three arrow planforms with different aspect ratios and one diamond planform were tested. The models incorporated leading-edge flaps for improved longitudinal characteristics and lateral stability and had trailing-edge flaps in three segments that were deflected differentially for roll control, symmetrically for pitch control, and in a split fashion for yaw control. Three top body widths and two sizes of twin vertical tails were also tested on each model. A large aerodynamic database was compiled that could be used to evaluate some of the trade-offs involved in the design of a configuration with a reduced RCS and good flight dynamic characteristics. Fears, Scott P. and Ross, Holly M. and Moul, Thomas M. Langley Research Center AERODYNAMIC STABILITY; ANGLE OF ATTACK; ASPECT RATIO; FLIGHT CONTROL; FLIGHT STABILITY TESTS; LEADING EDGE FLAPS; LOW SPEED; PLANFORMS; STABILIZERS (FLUID DYNAMICS); TAIL ASSEMBLIES; TRAILING EDGE FLAPS; WIND TUNNEL TESTS; WING PROFILES; AIRCRAFT DESIGN; DATA BASES; FLIGHT CHARACTERISTICS; LATERAL CONTROL; LATERAL STABILITY; LEADING EDGES; LONGITUDINAL STABILITY; PITCH (INCLINATION); RADAR CROSS SECTIONS; SWEEP ANGLE; TRAILING EDGES; YAW...