Aerodynamic Characteristics over a Mach Number Range of 1.40 to 2.78 of a Rocket-Propelled Airplane Configuration having a Low 52.50 Delta Wing and an Unswept Horizontal Tail

A free-flight investigation of an airplane configuration having a low 52.5 deg. delta wing and an unswept horizontal tail has been conducted over a Mach number range of 1.40 to 2.78. At a fixed tail setting of -3.0 deg., the trim lift coefficient and angle of attack varied from about 0.12 to 0.04 and 3.8 deg. to 2.0 deg., respectively. The base drag was approximately 5 percent of the total drag at trim lift. Lift-curve slope, static longitudinal stability, and damping in pitch were obtained only at Mach numbers of 2.59 t o 2.74. Theoretical calculations of lift-curve slope and aerodynamic-center location were in good agreement with experimental results.